19830008072 · A method to estimate weight and dimensions of small aircraft propulsion gas turbine engines: User's guide

/ ORIG I N f' _L - , . , OF P OORqUAL I "i _ 1 , Ilepmt N o . _ , G ovu r a m e n ! Ace mlig nN _I 3. Rec i pi o nt+ _ C _ tl l ogN o CR - 168049 4 , ' r ,t-----_, . . '_'-_,,mit ,o _. R. , _ ; _-o.,,, I_ , A mu t: h od t o mmtimate ++e i g h t a n d D i ma n a lon a A u gu _ a __ 190 2 .

o f S e al ,l . ._ ir o raft Pr o p u l s i o n G aa T ur b i ne 6, P a H o r m i ng Or_ n i l ' a t i on co d, E n al nee - F i na l Rep n rt Z A .t h _r ( s ) 6. Pa d o rml nu Organi_o t m 'n Rmmrt No. _ P. L , Ha le 21 - 427 0 -1.1 , 10, W 6 rk Unit No, 0. P e rformi ngO r g , n lzation Na maa ndAddr el t Ga r r e tt Turb i ne Eng i n e Company "_ 1. Contrac t or GrantNo, P.O. BOX 52 1 7 Phoen i x , A r izona 85 0 10 N A S A-2303 "/ i3. Type of R e port a ndPer i od C ov e r e d 12. S l_ nsoring , *pe nc y Name an d Address N a t io n al _ .e r ona ut ic s _. Spac e Adm in i s tr a ti on wa s h i ng to n , D.C. 205 4 6 14 . Sponso r ing Agency Code _ ' _ Sup p lement a ry Notes P in al Report P r o gr a m M a na g e r, Ge r ald Kni p , Ai r cr a ft Propu l s i on D i v i s i on Adva n ced P r o gr a ms Bran c h , NASA Le wis Re s ea rc h Cen t er , C l eve l and , Oh i o t 6. Ab l tr a et A m e t hod has been developed t o e stim a t e t he w ei g h t a n d m a J (. r e n velope di m e nsions of sm all ai r craft p r opul s ion g as t urb i ne e n g ines. The comp u t erize d m eth o d, ca l led W A T E -S (weig ht Analysis of Turbine E n g ines -Small) is a de r iva- tive of the B o e ing WATE-2 com pute r code . WAT E -S d ete rm ine s t h e we ight o f each m aj o r c om pone n t i n the engine I n c l u d \ n g c om p r esso rs , burners , tu r bines, he a t exchangers, nozzles , propellers , and acce s sories. A preliminary de s ign appr o ach is u sed w h ere t he s t r e s s level s , m ax imum press ur e s and t e m pe ra t u r es, m at eri a l pr o perties, geom et r y, st a ge l o a di n g , h u b / t i p r ad i u s rati o , a n d m e c hanical o ver- s peed are u sed t o d ete rmi ne t he comp o nent we ig ht s and di m ens io ns. The a c cur a c y o f the me th od is generally better than ±10 pe rc ent as v e rif ie d b y a n a lys i s of f o u r sm e ll a i rcr af t prop ul s io n g as tu r bi ne en gi nes Jo i n t ly se l ec t ed b_ th e N A SA P r o- g ram M ana g e r and G arr e tt .

--m 1 7 , Ke y Wor d s(S ug g e st e d bYA u thor ll ) ) 18, Ol l tr i bution S t a t e m e n t E n g ine We ight We ig ht A na l y sis G as Tu r b ine s T u r bi ne En g in e Unc l a ss i fl ed-Unll mlt e d A i rcra ft Pr o p ul sion P re d i c ti on Ana l ys i s Techniqu es Is . S e curi tyri ce |if. (of I hi l r a p o r t) 1 20 . S ecuri t y C la ss i f . (of t h i s page) 21. No. of P a g e s 22. Price" L Uncla ss i fi ed U,tcZa sslf i e d 1 36 .

' F or s a le b y th e Na l io,t a l Teeh m c al h)fo tm,_ t l o n S e t w c e ,Si) tm_ , fie l d VH _ , m ; b 22161 NAS A , C d f _i 'I (Ra y 1 0. 75 ) T AB LE OF CO N T E N T S SECTION I 1. 0 SUM MA RY 1 S E CTION II 2. 0 INT R ODUCTION 2

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2.1 C om pon en t M od u le s R e q u i r ing Mo d i f i cati ons 4 2.2 N e w C o m p onen t M od u l es 5 • 2.3 General Modi f i cati o n 5 SECTION III 3. 0 M E THOD O F ANALYSIS 7 3.1 C om p on ent We i gh t a nd Dimensi o n Me thodo l og y 8 3.2 O t her P ro gra m Capab ili t ie s 48 3.3 Progr a m Validati o n 52 S E CTIO N IV 4. 0 U SER'S GUIDE 54 4. 1 Input D e scr i pt ion an d F o r m ats 54 4.2 Output Descr i pt io n an d F o rmat 87 4.3 Sample Cases 9 0 4.4 Pr o gram Diagn o stic s 125 4.5 P rog r a m Str u cture 125 S E CTIO N V 5 . 0 CONCLUSION A N D R E COMM E NDATIONS 13 0 APPENDICES A SYM B OLS 132 E R EFERENCES 1 33 DISTRIBUTION LIST 134

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lii S E CTI O N I f .

i 1 .0 SUMMAR Y A me tho d h as bee n dev e l o ped t o e stima t e the weig ht and m a j or en v e l o pe d i m en s i o n s of s mall a i rcraft p r o puls io n g as t u rb i n e engin e s . T he c o mp u t er ize d me th o d, c a lled WATE-S (We i g h t A n alys i s o f T u r bin e Engi ne s - Sm a ll) is a de r iv a t i ve o f the B o eing WAT E- 2 c om p u ter co d e ( r ef. I) _ A s in WATE-2, WAT E -S deter m ine s the wei g ht of each maj o r c o mp o nent i n th e en g ine incl ud in g co m - pre ss or s , burn er s , tur b in es , he a t exch an g e r s , no z zl es, pro- pell e rs , and a cces so r ie s. A p r el im i n a r y des i gn app ro ac h is us e d _: where t he s t res s l ev els , m a x imum p r e ssur e s a nd t em pera tur es, m a te r ial pr ope r tie s , g eom et ry , sta g e l o a d in g , h u b / t i p r a d i us r a t io, a n d mechan i cal overspe e d a r e u se d t o d ete rm ine the c om - ponent weight s an d d i m ens io ns .

A re la t i v el y h i gh leve l o f d e tai l wa s f o u n d n e cessa r y i n o rd e r to ob tain a t o tal e n g ine weight with i n the re q ui r ed ±10 -p er c en t a cc ur acy. C ompo n en t w eig ht d at a from G a r r ett en g in es w as u se d a s a d at a b a s e to d e v el o p the m eth ods r eq uir e d fo r sm all gas tu rbi n e e n g ine c o mp o ne n t s. The s m a ll en g i n e wei g ht me t hod is i p robably va l id f o r o t he r m an u fa ctu rer s , howeve r , t hi s h as not be e n I v e rifi e d. T h e acc u racy of th e metho d is ge n e r ally b e t te r than ± i 0 p e rc en t , on the o r de r o f ± 5 pe r ce n t. T h is acc u racy w as v er i f ie d by a pplyi ng t h e met hod t o f o u r Gar re tt p ro pul si o n e n gin es , s ome of whic h w e re i n t h e ori g ina l dat a b as e. Engin e s u s e d in t he validation st u d y were Jo i ntly s e l e ct ed b y N ASA and Garret t .

SECTIO N II 2 .0 INT R ODUCTI O N A ir c r af t prop u l sion system st u di e s are freq u ently c o n duct e d by ind u stry a n d g o ve r n m en t . The s e s t u di e s m a y en c o m pa ss a w ide var i e t y of en gi ne concepts ra nging from r e lat ivel y si m ple tu rb o - p ro p an d tu rb o f a n eng i nes to c om pli c a t e d v a r i able cy c le e ngine s .

T h e ae ros pace indu st ry i n general h as a c q uir e d an adequat e com- p u ter ca p abilit y t o evaluate the th erm od y n am i c pe rf o rma n c e of t h e se diver s e engine co ncept s_ h o wever, until recently, accurate m e th o ds o f est imati ng engine weight an d dim en sio n s were n o t r ea d - i l y ava ila b l e.

The Boeing W A T E -2 (Weight Analysi s o f Turbine E ngines) com- p u ter p rogr a m wa s w ri tten p ri m ar i ly t o e s t i m ate the we i gh t an d m aj o r envelope di m ension s o f l arge, a xial-fl o w turb o f a n and turb o - Jet p ro puls ion engines. A pre limi na ry d esi g n ap pco ach is used where the stress level s , ma xim u m temperatures an d pre ss u r es , mate- rial pr oper ti es, ge om et r y, s ta g e l oadi ng, hub / tl p ra_ u s rati o , _ nd sh a ft m ech an ic a l o verspeed are us ed t o d eter mine c om p o ne n t weights and d i m en s ion s .

O verall , t h e basi c ap proa c h o f t he Boei ng WA TE-2 pr ogra m is val id for sm all gas t u r bi ne eng in es ; h owe ver , m aj or m odi f i cat io ns t o som e of t h e c o mp o nent modu le s were r eq u ir e d to i mpr o ve t he a cc ur acy an d f l exibilit y of this pro g r a m for sm a ll ga s tu r b i ne engin e s, A c o mp u ter p_ o gram speci f ically w ritte n t o _stimate t h e w eight a n d dime n si on s of small gee tu r bi n e e n gi n es w as derived f r o m the G ar r ett versi on o f t h e Bo ei n g W A T E -2 c o m p uter p r o gram.

T his pr o gram w ill be refer r ed t o as W A T E- S ( W eight A n alysis o f Tur bi n, : E n gi n es - S mall). I t w as c on fig u red on a sta n d-al on e ba si s , th e re q u i r ed i np ut be ing obtain a b l e f r o m m os t general pu r- p ose th er m od y n am i c engine c y cle p er fo rm ance c ompu t er pr o gr a m s. A sm all g as t u r b i ne e n gi n e a s defin e d f or WATE-S sui t ab ili ty is o ut - l ine d belo w l o C onv e nt i o na l an d u nc o nv e n tiona l Bra y t o n C ycle s (r eg en - eration, i nter co ol i n g , reheat, af t er b u r n i n g , c ombina- tion s) o Se p a rate o r mixed -fl o w t u r bo fan s o C o re -correc te d a ir f lo w s fro m 0. 23 t o 4 . 54 Kg / s (0.5 to i0.0 I b m / s) o C o mpress o r pre s sure rat io s f rom 5 t o 25 o Tur bi ne r o t o r i n l et te m perat u r e fr om I 089° K ( 1 96 0 0R ) to 1922O K (346 0 °R) o Pr opell er s an d prop f ans su i ta bl e fo r a i r cr a f t f l ig h t s pe eds up t o Mach 0 .8 o Ax i a l a n d r a di al f lo w t u rbom a c h i ner y co mpon e nt s wi t h in p u t speci f i ed s ta g ing a nd sh aftin g a r ra ng e men ts o G e a r ed o r ung e a re d pr opulso r dri ve.

W A TE-S d eter mi n e s engine we i g h t and dim en sio ns b y summi ng t h e we i g h ts a nd d i men s i o ns of each m aj o r co m p o nent in cl u di n g pro- pe l l e rs, f an s , com p r ess o r s, combue t or s , tur bl r l e s , a n d n o zzl e s.

_ao h in d ivi d ual oom p o n u nt sp eci f ied I n th e I npu t in i nd iv idua ll y mo de l ed u si n g _un d am e nta l p hy m l cal r e l a tio n s h i p s. Th e s pe cif ic t a s ks a cc o mp l is hed ar e s ummaris e d in t h e f o ll o wing s e c tio n s .

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2 .1 Component Modu _s R equiring Modifications Pans and Axial Con,pressure - The WAT E- 2 ax ia l co mp resso r m o d e l ass u mes t h e g enera l design p res sure-ra t io c ur=e r r e d t ip - s p eed r e l a t lonshlp is applicable to fans as well a s low- an d hi gh - pres s u re co mpre ssor s. Ga r rett e xpe r i e n ce ha s de mon st r at ed that thls a ss u mpti o n i s n o t v ali d f or m o st small an d Inte rm e di ate tur- bo fan e n g ine s . S e pa r ate f an a cco u nti n g is p ro v id e d in WAT E - S as w e ll a s a d e s ign pr ess u re - r a t lo c orre c te d t l p- sp e e d rel et lonshlp suitable f or sm all axial c o m press o rs.

Centrifugal Compress0r _ and Radial T urbi nes - The WATE-2 c ent r i f - ug a l c om p r e s s o r an d radial t u r b in e m o dels ar e no t c on s is t e n t with t he de sire d c o mp o n en t pre llmlna ry d e si g n p h ilo s op hy. T h ese mo d- ul e s h ave b een c o mpletely r ewr it ten s o t h at r a di al flo w c o mp o nent we i g h t s a nd dim en sion s a r e d ete rmi ne d o n t he b a si s of f u n d a m enta l phy s ical relati ons hip s si m il a r t o th o se use d f o r axia l fl o w com p o- nents .

Reverse-Flow Co,_ _ u s tor_ _ s- The WAT E -2 p r o gr a mt s c o m bu s t o r lo % Ic Is no t a pp li c a bl e t o reverse-fl o w c om b u et o rs. The me a n b u rner dl a m - eter I s u se d a s th e ge o metric d e si gn parameter . F o r rever s e-flow bur ner s , whe r e the b u rner Is p osi t io ned ar o un d the HP tur b i ne, the I nner d i am eter h as m o re g eo m et r ic s i g n i f ica nce . T h e ab i lity t o u s e either of t h ese d i am ete rs as the g e om etri c d e s i g n parameter Js i n co r p o rate d In WATE-S.

Engin e A c c e ssori e s - E n gi ne a cce s s ory wei g ht s a re c ur r entl y l u mped tog ethe r as s per c enta g e of ba re en g ine w e ight. S m all g a s t ur b i ne e n g i n e access o ry w eig ht data I n c l ud in g the s t a rter / ge ne r at or , battery, fuel pumps, oll Dumps, prop el ler pit c h c ontrol, fuel c oi_- ttol , et c ., was reviewed to d etermine if a more detail e d weight mode l was warra n ted. A n ew a c c e s so r y weight model has been deve l - oped a n d inGlu d ed i n W A T E-S.

2 . 2 New Co mp o n ent M odule s Gearboxes - T h e WA T E -2 pr og ram g e arb ox w e i g ht a cco u n t in g is spre ad thr o ugh a numb e r o f subr o utin e s. A diff e r e nt m o d e l i s u s ed f o r a x ial and c en trifu g al c om p r es sor ge arbo xes , an d no m e tho d is available for l inking a g ear b o x to a tu r bine for g ear e d fan or pro p e lle r fr ee-t urbine eng in e s. A n e w ge a r b ox c om p onent modu le w a s nec e s s a r y to provide the r eq u i_ e d fle xibi l ity fo r s m a ll g a s turbine e ngine s . I n thi s w ay , g ea rb oxes m ay be c onne cted t o a n y r o t a ting c om p onen t des ir e d and c onsi st e n t g ea rbo x wei gh ts es t i - m at e d .

Propeller and Pro pfan s - M et hod s o f es tim a ting p r o pell er and prop - fan w eigh t an d dim e n s ion s a re n o t i ncl ud e d i n WATE-2. A ne w pr o - p eller co m po n en t m o d ul e b a se d o n H a m il to n S t a n d a r d pr o pell e r d at a has been d eveloped and in c or p o ra ted in WA T E- S .

2 . 3 General Mod i fi ca ti o ns In a d d itio n to th e a bo ve , th e p r inte r plot o p t i o n of WA T E- 2 has be e n made o p erationa l fo r s m all g a s turbine e ngines. Cen trif - ugal c omp re s s or s , r eve rs e -flow combu st o r s, a nd radial turbine e l e m m e n t s we r e added t o the a xi al f l ow co m p on e n t pl o t ca pa bi l i t ies. A general review of the m a n y geom e tri c assum p tion s us e d in WA T _-2 f o r larg e turb o machinery co mponents w as com pl e t ed to d e term i ne their suitabil i t y to smal l gas turbine engine c om p onents.

_% d e fault en gi ne co nfiguration i s i nco rp o ra t ed in WATE-S. i T he default en gi n e is a two spool turb ofa n e ngin e c onsisting of a i £an, a x i - _e n _r_ Eu gal h{eh' _p r e ss u re a om p re , l m or , ax la l h|, gh- p _ es su_ e t u r bin e , and axi a l Ean t ur b i n e . F ouc _e Eece nc e e ng _ nee h ave been u ae d Eo ¢ c om p u t e _ progr am che c kou t an d v al id ati on. The acc u rac y oE WATE-fl in eBt_m_t in 9 en gL ne we £ ght and m a J o _ e n v e l op e d i m e nsion e _ s ± 10 pe r c en t o r b e t ter . Th i s h a s be e n d em ons trat e d b y a n al_e_ s o£ t he re E e_e n c e e ngin ee .

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i S R CTION I X !

Z .O M_ T _ OD O _ A XAL YBX B The m e t hods o f ana l y sis used i n WAT E -S a_ e ba a ed on a pr e li - mi na r y de si gn app ro ac h w her e t h e ae ro d y na mi c and m e c ha n ica l desig n v a r i a b les ar e t aken i nt o acc o u nt. In the c o mpressor, f or exa m ple, ro to r bl ade w eight is c al c ul ated as a fu ncti on o f the sp e c_fi e d ge om e t ric pa r a m et e rs. Blade ce n t r i fu gal s t ress i s then fo u nd, and th e d is k we i gh t t hat w i ll s uppo rt t he b lade r o t a ti onal f o rce i s d ete rmi ne d . T hl a t ype of p r e l i m ina ry design app ro ach w a s a ls o us ed for t he oth e r components.

The WATE-S method is i n t en d e d t o e s t im a t e t he weight o f a given en gi ne d e slg n t i t will not des i g n an en gi ne . This fun ct i on mu st be pe r f o r m ed external to t h e program. WAT E -S utilize s c o m - p o nent state co nd i ti o n s wh ic h a r e g en e r at e d in an external eng i ne therm o dyna m ic c ycle c o mputer pr o gram.

In th e n o rmal u s e o f WATE-S, the d e si re d en gi ne cycle i s s i m - u l ated at t h e engine design p o int. The use r o f WAT E -S m u st b e c ogni zant o f o t h e r c o nd i t io n s i n the f llgh t env elop e where m ax im u m c o mp o nent t em perat ur e , w o r k, s pee d, or fl o w o c c u r . I f the s e co n- d lt lo ns a r e gr eat e r than t he d e sig n val u es, t h ey c an size th e c o m- p o nent and have a sig n ifi cant i m pact o n t h e c o mp o nent weight.

WAT E -S a llo w s inp u t of sca l ar s to acc o u nt f or these o f f - desl gn con d i ti on s .

A m ore a cc u r ate weight e s t im a t e can b e a c h i e v ed b y d eveloping an a r ra y o f engine cycle data over t he eng i ne operating envelope.

T h e WATE-S pr o gram w i l l scan the input engine cycle d ata a n d sele c t t he maxim um c o n ditio ns fo r each c o mp o nent.

Th e engi ne c y cle _ i .mulati_ n ma y _s e campo n entB th a t are rQquired ma th ema t lcally , bu t ar e not de sir ed in t h e engi n e welgh_. Th ese c a n be eelec t l v ely elimi n a t e d by th e use o F t h e i, c o mp on e n t w e ig h t scalars.

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i 3.1 Ca m a ne n t Wei_ _ht a nd D ime n si o n Me t h o d ol o T he meth o ds o k a n alysie d es cri be d fo r e a c h c o mpo n e n t i n the _ ' F ollowi ng s e cti ons ha ve b ee n develop e d to achie v e an ove ral l I eng i n e a cc uracy of ± 10 per c en t . S i n c e t h e ro t a ti n g com ponents i com p ris e the major part of t h e to t al en g in e w eig ht, c ons ide ra ble d e tail wa s n ec e ss ar y in o rd e r t o a ch leve th e a cc u ra c y go al . No r - m al pr o gram u sers m ay not h ave s uffi c ient k nowledge t o a dequa te ly d efine all o f th e nece s sa r y inp u t s; h o wever, typi c al val u es a r e g iven in t he _e er ' s Guide, S ec ti o n 4 .

3 .i.i A x ia l F a ns..a.ndCompreesor_ Th e pr o cedure u se d f o r ax i a l f an a n d c o m press o r w e ight p r e.- d icti o n i s a stage- b y-stage a e romec hanlcal d esign a s il lu stra ted i n Figure i. R o t o r b l ad e v o lume an d wei gh t are d ete r m i ne d; th e n, b lade ce nt rif u g al et re_s , disk str ess, and dlsk we ig ht a r e cal c u - lat ed . C onn ect ing h a rd wa re , sta re r b la de s , a nd c ases are t he n es t im ate d an d s umm ed t o gi ve th e t o tal c om p o n e nt w eig h t. The f o l - lo w ing inp u t da ta is n e ces s ary: o T he n um b er of c omp res so r s t a ge s. S t age w o r k is hel d c o n s tant fo r m u l ti stage a xi al c om pr e ss o rs . Alte r n a - ti ve ly , a max imum fir s t- s t a g e pr e ss u re r a ti o , whic h re f le c ts the de si gn a p p r o ac h and techn ol ogy le ve l , m ay be i n pu t o In le t and ex it M at h num b er s of the com pr e s s o r Inl_t hUb / tlp radlu_ _atlo _ f th_ flrst-at_g_ bl_d_ o C om p ress o r d e sign m o d e : i , e . , c o n e tar:t m_ n ] . in_ , co n - - e ta n t hub , or c _ n _ta n t t i p dia m et e r d , o E£ _ e o ti ve d e nsit y o f b lade mat e r ia l ; defined as t he i r ati o o£ t o tal b la d e wei gh t a nd vo] . umc _ o Ma x imum Inlet a nd e xi t t e mp e ratur e s , if n o t at d e sign o A s p e ct r a ti os f o r th e fir s t a nd t he las t s tag e b l a de s o RPM m ax / RPMdc s o ve r e p e e d f a ct o r o B la d e ti p s o l idi t y , ra t io of bl a d e t l p c hord a n d s p a cing I I o De nsi ty of disk m a t e ri al o Bla d e t aper ra tio o Bla d e v o lume f act or; ra tio of bl _ s v o l _m e a n d t o tal annu l us vo lum e .

T he t ot a l e_ha lp y c h a ng e f or t he c o m pon en t i s a v ailabl e f_og the e ngi ne cycle dat a. Equ a l wor k f o r e ac h s ta ge is ass um e d , and the nu m b e r o f s ta ges r eq ulr e d is fo u nd b y ite r at io n un til t he flr st-st ag e p r es s u r e rat io i s equa l t o or l es s t ha n t h e sp e c ified m ax imum . W hen th e n u m b e r o f s tages is s p e c i f ied, f i rst- st ag e p r es s ure ra tio i s ca lc u la te d b ased on t he e q ua l w o rk pe r s t ag e as su mpt io n an d t h e m axi m u m a llo wa bl e p r e ss ure r a t io i nput Is ignor ed . Sha ft s p e e d is de t e r m in ed from t he ax ia l f a n a n d co m - p r essor ti p speed c orr elat ions g i ven i n F i g ur e 2. T h ese co m - pr ess or ti p spe e d c orre l ations ar e b a sed o n c urrent ( 1982 ) te c h- nol o gy le v el s. Th e r p m o f a dd itio n al c ompresso r s dr i v en on t h e s ame s haft w ill b e s et by th e fi rs t u ps tr e am c o m pr essor.

I0 ORi _t l , ,,, _+ OF PO01 _Q_ J A L. t] ¥ , Ut - 2 11L? _ n h / t) (P R -1 . 2 11BI AXIAL FANS ' ..._ 35;I, + ( 2 4,6 - WH | RE U _ . . OORREO'rED Ti P SPEED , m / | h i t - HUB / TIP RADIUS RATIO P R - FI RS T 4T AOE P R E8 8 UR R RA T IO ?O0- a " _ eoo.

i ,.m O o .

20 0 J e e _ , 1. 0 1.2 1.4 1 , 6 1, 1 1 2, 0 FIRGT.,STAOll AXIAL COMPRE88O R PRESSURE RATIO Figu r e 2. Ax i al P an an d C omp r en m o r T i p-Sp e ed C or rel a t i on.

1 1 I-: I n th e ev en t that a n ex isti n g compressor Is being we ighed , or the shaft speed is already know n, a speed scalar can be applied t o the sh af t s p e e d f o u nd f r o m Fig u re 2 t o ac h ieve t h e de sir e d v alu e.

Th e s p e ed scalar can also be u se d t o m od i fy the estimate of sh aft sp eed f or hi gh-pr e s s u r e com pr es s ors , w h e re the i n let tem p er a tu r e s i g n i f i c an t l y aff ect s the press u re r a tio capa bi lity, or for e x t e r nal iter a tio ns o f a n engine desig n .

_ / T h e f i rs t- stage flo w area is d ete rm i ned by t he sp e ci f ied M a c h n u m b er and t he c orr e ct e d i n le t a i rf lo w f r om th e c ycl e d a ta. I nne r an d o uter di a m et e rs o f t he f lo w path a r e c alcul a te d fr o m the spec.- r_ i f i e d ra di us ra tio: _ / 4Linlet D t = IT.- ! - h

' ( 2 }

D h = Dt F: _ C om p r ess or RPM i s d et ermin e d b y d iv i ding t h e t i p s p e e d ( f o u nd f r om F igu r e 2 ) b y the p r od u ct of _ and t he t i p diame t er ( Dt) .

St a g e le n gth i s f ou nd i n t h e following m ann er. Axi a l blade c hord (C) , as sho w n in Figure 3 , i s th e quotie n t of the blade hei g ht and a sp e c t ratio: hB C _ -- ( 3 ) A R 1 2

r

o R tC _ , r ' _ _T -. P_ _, , ., ' _ ; _

i OF pooi_ qu, " , _ - _; ' ¢

ASPE C TRATIO - ' _ h - MEAN HEIGHT AN CHORD

±

_ t TH I CKNES S RAT I O - _ -

T

Figure 3 . B lade Sc hemat ic .

T h e stator le n gth was assumed to be equal to the rotor le n gt h (or blade chord) , and 1 7 per c ent of the rotor l ength requlred for clearance between r otor and stator and the same clearance between the stato r and the next rotor.

T he total number of b l ade s is calcul a ted f rom the specified tip solidity (C / S ) and a sp ect ratio (A R ) , and previously ca l c_1- f ated ti p diameter ( D t) and blade height (hB) Z NB R_

- )

T hi s val ue i s trun ca ted t o an i nt e g e r numbe r o f b la d e s, and the sam e va l ue is used f o r the stator.

T he tota l v o l ume of meta l in the c om pr e ss or b l ade s i s then c al c u l at e d f ro m ; K " hB 3

I

vB - 1

where K i s a vo l um e f act or w h i c h a c c ount s f o r firtree moun t v o l - ume , t ap er ratio , and thi c kne s s-t o - c h o rd v a r ia t ion s in t y pi c a l 1 blade s . F or the d ata bas e en g ines , K was found to be 0.06 fo r fan blades and 0.1 2 for c ompressor blades with hub / ti p radius ratios l e s s than 0 . 8 . For co m p re s so r b la des with hub / t lp radius ratios _] gr e ate r t h a n 0 . 8 1 K = 0. 12 + 0.04 (h / t - 0.8) (6) The rotating b l ad e weight of each stage is dete r mined from the blade v olume and material de ns it y . M a teria l d e n s it y autom a ti- c a lly c hanges from titanium to stee l when the s tage inlet temper a - tu r e ex c eeds a s p e c ified maximum , no r mall y 6 44 0 K (II60° R ). StaTe tem p erature is determined from the engine cyc le d a ta , the e qual work assum p tion , and the spe c ified o v er-tem p erature ratio. Stator blade weight and dim e n s ions are as s umed equa l to the r otor blades and in c lude the inner shroud.

i

F

'_h o m ax imum b la d e centr i f u q al stress occu r s at th e b lade r o ot and i_ a funetl on o f tip sp e ed , bl a d_ heig h t , ta p p r rat io , a n d i i material density. E xpressed in te r ms of the nondim e nslonal blade ge a metry, th e e q uatio n fo r blade r oot ce n trifu g al stress is: ¢r = _._ kS + "i' 2 -- 11 - h / t) (l + 3 h / t (7) g .TR wher e U t is t h e p r odu c t of the design tip s p eed and th e o v e r s pe ed fact o r, R PM m a x / R P M de s. An i n s e r t e d blad e i s assum e d , a n d th e di s k , mate r i a l is assumed to be tit a nium or st e el fo r gings with ultimate s t rengths of 82. 7 RN / c m 2 and ii0. 3 RN / cm 2 r es p e c tive ly . T h e r i m ' of the di s k IS a ssumed to b e i 0 p e r c e n t o f the b l a d e h u b r a diu s or 1 .91 cm , whi c hever is gre a ter. T he remaining di s k vo l ume is a ssu m ed t o be a tr a pe z o id a l sect ion r o t a te d a bo u t t he a xis. Th e thickness of the tra p ezoid at its outer radi u s is sized fo r 75 pe rc en t of t he u lti mat e st r ength. T h i c kness of t he t rapezoid a t the inner radi u s is ba s ed on 50 per c en t of u lt ima t e s t r e n gt h for t he tangential s t ress. T his value was s e l e ct ed based on an experimentally determined burst speed m a rgin.

If the average tangential stress can be satisfied with a con- st a n t thi c kness disk , the bor e r a diu s i s in c r ea s ed u n til the lowest weight disk is a c hi e ve d th a t just meets the design c rl- teria.

Disk stresses a r e c a lc u l ated bas ed on th e tot al b l ade force a c ting o n the o u te r c ir c umf er e n ce o f th e d|sk , a nd a r e th e refore se n sitive to c hanges in blade a s p e ct r a tio a nd so l idity , as well as blade centrifugal stress and hub radius.

Dimensions of suc c eeding stages a re based on the design mode selected (c o nst an t me a n, tip, or hub r a dius). I n the co n stant mean llne method , for ex a mple , the mean radius is based on the mean f low area of the first st a ge. T his mean radius is held c onsta n t for s u bsequent stag es . Corre ct ed ai r flow at t h e entry of ea c h st a g e is d etermi n ed from the cal c u l ated st a t e c onditions d e ri v e d f ro m t h e equ al w o r k p e r sta_e a ssumption. St a g e inlet Math numb er is a ss u m e d to var y p ro p ortio n ally to the numb e r of sta ges w h en dif fe r e nt i nle t a nd e x it M ath numb e r s a re sp e c ifi ed .

T ip speeds for the d o wnstr e am stag e s are then ca l c u l at e d from t h e st a g e d i me nsions a n d sh a f t s peed . Bl a de a s pect r at i o is de t e r - m ine d by a ssum ing a p ro p or t io n a l c h a n g e fo r e ach s ta ge i f inl e t an d e x it as pect ra ti os a r e d i ffe r ent .

F i g ure 4 ill ustrat e s the st a ge c ou pl ing m e tho d th a t was dev- elo p ed by Boeing and used in WA TE -S. The s p a c er, nu t s, and bolts are assumed to be steel, with the s pac er being a 0.191- c m thick c yl i nde r lo c ated at 7 5 p er c en t of blade hub r a dius. T he c onne c - t i n g hardware weight (Whw) is esti m ated by the follow i ng equation: Whw = 2 _ (0.75 R h) 0.191 LS T G . @ (8) where R h is the b l ade hub radius, L s tg is the stage length , and @ is the mat er ial densit y .

T he outer c a s e is the l ast item of w e i g ht in c luded in the c om p ressor weight buildu p . Average c ase t hi c kness in the d ata b as e engines was 0. 25 4 -c m e quiva le nt thi c kness , in cl uding fas t eners and flanges. Cas e w e ight is c al c ulated stage by stage, and the s ame mate r i a l u s ed in the di s k is al s o assumed for the ca s e: W c = _ D t . LST G 0. 254 . p ( 9 ) w here D t i s the stage ti p diameter.

Total stage weight i s th e sum of the r o to r blade s , starers , d isk , c onne c ting hardwa r e , and c ase. Stage w eights are summed to 1 6 ORI G INALPAGEIS Q F POORQUALITY , COMPR EE GOR CA S ING J BLADE BTA TOR BLADE STATOR hB SEAL ' iN N E R SHROUD L SPACE R n h R HARDW A RE L DISC DISC i ENGINE i - Figur e 4 . Typic a l S t a ge C o m p on e n ts .

i _ : i _ . _ . _ ; _ i - ._, _ _ __-- = = ' _ : ._ i , _i :_ ................... .............. L .......... ' _ "_ 7 ; _ ....... T : _7 ........ .......... : i give t he total _ompo ne nt w e ight. Th e sum of all st a g e le n gt h s gi v es t he total co m p ress o r leng t h. Znle t g u i d e v a n e_ are n ot i n clu ded i n t h e c o m p re s so r weig h t , but ca n b e a cc ou n t e d fo r wit h a i" fr a m e ( s ee S e cti on 3 .1 . 9 ) .

Rotati on a l i n ertia o f th e o o m p r esso r is de t e r m i n e d by fi nd i n g t he i n erti a o f ea ch s t ag e o f t he c o m pon e nt. It is a s s u m ed th a t b l ade s h ave un if o rm we i gh t / a r ea and t he d i sk i s of unifo rm t h i ck - ness. T hi s m e th od had bee n a pp l ied t o s eve ral e x i s tin g eng i nes a n d th e results showed good a gr ee m en t . T he f ollo wi n g eq u a t ions are used f o r the b l ad es an d d i s k i ne rti as:

lg kT N S

WD 2 I D - _ - _ R h ( ll ) Th e t ot al stag e in er t i a is the s u m of b la d e a n d di s k i n erti as i stg = I B + ID (1 2 ) T h e c o m pon e nt i n e r ti a i s th e s um of th e i ner ti a of ea c h st a g e .

3 .1 .2 Rotating Splitter A r o ta ti n g spl itt er , s ee Fi gu re 5 , i s a c i rc umf ere n t i al s eparat o r of t w o fl o ws w i th i n th e sa m e com p o nent. T h ese f l o ws no r m a ll y h ave di ffe re n t pre s su r es an d t e m perat u res , a nd t h e s p li t- tee m u st pe r f o r m a s e a l i n g f u nct io n. Sta g e s t hat inc o rpo ra te r o t a t i n g s plitters ar e tr ea te d the sa me as com p r e ssors; a ro t o r- sta tor pa i r compri se s o ne s t ag e , st a to r w eight a n d s i ze are ass um e d t o be t h e s a me a s t h e ro t or b la d e, an d ro t o r-st a to r sp a c- i ng i s 17 percent o f r o to r l e ngt h .

ORIG Ii ' , iAL k. hG _ I L _ OF pOO R QUALIIN ' SPLITTER

t

B L ADE RSp L TYPICALSECTION Figu re 5 . R ot a tln Q Spl itt e r .

1 9 T he rot_tl n _ _plltter a d ds weight to t he bla d e a nd I n erease_ the ce n trifugal bla d e fo r ce. C o n seque n tly , t h e d isk must b e heavie r t o carry t h e a dd e d loa d . S plitter w eight per b l ad e is estimate d by: 2 _S pL C 2 . 0.i 0 . # WS p L - ..................... ( 1 3 ) N B +, wh e re C is the blad e c hord f oun d fr o m E qua tio n (3) a nd R Sp L is t he r ad ia l l oc at io n of t h e splitter . Th ic kn ess of t h e s p l i t t er Is a s su m e d to be i 0 per c ent of the c h o r d , h o weve r , thi s c h o i c e was b ased o n o nly o n e engine, the General El e c t ri c CJ8 0 5-23 . Th e CJ8 0 5-.23 a ft. -fan b l a de ha s a r ot a tin g s p l itt er which h as a box sec tion . T he s oli d e qui va le nt t h i c k ne ss of _,e hollow bo x w a s appr oximat ely i0 per cent o f the c hord . A mor e ac cur a t e e st im a te c o u l d be m a d e b y a ct ua l d e sign of the cant i l e vere d platf or m t o th e d esire d d e flect io n an t / or s tres s lev e l s.

T h e c e n t r i f u g a l fo rce c on tri b u tion o f th e ro tat i ng s plitte r i s : FSp L = M r_ _ 2 WSPL 2 _ . R P M 2 ( 1 4 )

g - " "T 6 • R S P L •

wh e re RP M is the s haft spee d d et ermine d i n the s ame m ann er a s f o r a co m p r e s s or, B lade r oot c ent r ifu g al st re S S (E q u a ti o n 7 ) is in cr ea s ed by the a mount _c r= FS P L F SPL ( 1 5 )

% - : J

w he re t / C i s t h e th ic kne ss / cho rd r a tio of t h e b l ade ( whic h is a s s umed to be i 0 per c ent). Disk weight is determined with the i nc r e a sed s t r e s s l e vel using th e p ro c e d ure s d esc ri b ed for a x ial fans and c ompre s sors (Section 3 .1.1).

2 0

8h aft spe e d d etermi na tio n (as d es c r i b ed i r m S e c tio n 3.1.I ) a_sumes t h at blade-r o ot str o s_ is sub a rltl a a l . U se of a rotati ng splitter wi ll _aus e t he b l ade c entrifuga l s tress t o i nc r e ase slg - n ifi a a n t l y , a n d t h e W A T E - B ot _tp u t s hould b e i n s pec ted t o d e t e rmi n e whether or not the , tress le v el is accep t a bl e. R e d ucti on of sh a ft sp ee d ma y h e req ui r e d t o redu ce th e st r ess l e vel .

_f sh af t s peed i s dec re a se d , ad diti ona l c o m p r e s so r st a ges m a y be r e_ui re O to accom p lish t h e same w o rk . Al t erna tively , th e r ad i u s r at io o f t he c o m pre s s or c an be incr ea se d t o res to re wo rk c a pacit y ( d ue to high er t i p sp ee d). Dis k we i g ht of ea ch s t ag e will i nc re ase for this c o m pro mi se , how ev er . T h e f i nal choic e must be i t er ated ext e r nal t o WAT E -S an d may depe nd o n w h ether or n ot the fl o w path i s r eas o na b l y well matc h ed t o co nne c t i n g c o mp o nent s .

Th ese seconda ry e tf e ct s m a y ha ve a mu c h l arger im pa ct on th e e ng i ne w e igh t than t he we i g h t o f t he sp litt er m a t e ria l , a nd th ey sho ul d no t be i g n o red.

3. 1 . 3 A x ial T u r bi ne s T h e methods us ed f o r a xial tur bin es a re ge n e r a l ly t he same as tho s e pr e viou sly d es c r ib e d f o r ax ia l co m p re ssors. T h e f ollowin g i np u t da ta is t eq u i r e dz o T h e n umb e _ o f st age s o r th e m ax i m um m ean di a m e ter of th e fir s t st ag e o Inle t M a ch number (a xi a l ) o f th e fi r s t st a g e , a n d ex i t Ma c h number (axial) of the last stage o Ro t or bl a de a s pect ra t ios o f th e fir st and l as t st a g e s o Bl ade ti p s olidit y 2 1 o R e fer en ce disk str e ss , 0 .2 p e rce n t y ield poi n t nf the mater_al selected o C ooll n g I n dicates , to modify t h e blade volume calcula- , ti on _or cooli n g pass ag es o T ur b i ne d es i gn m o d a _ i .e. , cons ta n t h u b 4 1 a me_e r , con - s ta n t m e a n li ne , or c on st a nt tip di a m e t e r o S haft ove r a p ee d f ac t or , _ P _ax /R PMdea o M ea n wo r k c o efficie n t , Am • Um 2 whe r e 4 H / N = en thal py ch a n ge p et s t a ge a nd U m = m e a n b la d e s pe ed o B l a de m ateria l d ensity o Bl ade t a pe r rati o o B l a d e v olum e f a c t or; r at io of b l ad e vo lu m e a n d t o t a l ann ulus vol u me .

Tw o a lt e r native p r oc e dur e s m a y b e us e d to si ze t he t urbin e: (i) specify the number of stages, an d a s s umi n g equal w o rk pe r s t a g e , c a lc u late t he me a n d iameter o f the first s ta g e ba s e d on the inp u t turbine m e a n work c_ e f f l c l ent ! or (2) spec i fy t h e m ax imum m ean di a m ete r o f t h e fi rst stage, a n d a s su m ing e qual w o r k pe r s ta g e , cal cu la t e the n u m ber of s ta g e s r eq u i r e d to sat i s f y t h e i nput t u rbine mean w o r k co ef f i ci ent. T o t a l c o mp o nent w o r k an d J state co n di ti o n s a r e ta k en from t h e engine cycle d ata. i !

T h e flow area r e quir e d to pa ss th e c or r ec t ed ai r flo w a t t he 1 spe c ified Mach number is cal c ul a ted at the i n let of ea c h s tage.

For t he fir s t st age, th e hub a n d ti p r a dii a r e c al c ula te d from 1 thi s a ra a a nd th e p r e viou s l y de t e rmin ed t ur bin e m ean ra di us . S ub - I seq uent s tag e dime n sions ar e c alc u la ted based on th e d e sign mode i d e o l_tQd ( _ o natant moa n, hu b , or t ip diam e t er) . Wh en the firs t- ,rage inl e t Ma_h n u mb e r a nd aape u t rati o are diff e r e nt From t h e last s tage valu e s , a proportlona_ a h a n ge le assum e d for t he int e r - mediate stag e s , Rot o r b la d e s h a r d a nd n um be r of bla de s are de t e rmi ned b y th e same met ho ds use d f o r a xi a l c o mp re ss o rs, _ l a d e v o lum e _s als o de t er m in e d b y t h e same met hod, _q u ati on (5), ex cep t t h at K - 0 , 1 55 fo r h ig h-p r e ssure t u r b i n e s e nd K - 0, 1 9 5 fo r lo w - pre ssu re tu r - b i ne s, Whe n t h e blade Is a c ool e d blade , the c alc u la t ed v olu me is red uc e d 2 0 perce n t t o co m p en s at e for cooling -ai r p a s sages. Blade we i g ht is the1_ fo un d fro m t h e spe ci f i ed m a te rial d ensit y. Bl a de roo t ce nt ri fug a l s t r ess i s c alc u lated by Eq u at io n (7). Th e disks a r e c alc u lated b y t h e preli m i n ary des ign pro ced ure already di s c us - s e d for axia l com p r e s so r s .

Eac h s t age of th e tu r bi ne is tr ea t ed a s a st a t or- r o t o r p a ir (as opp os ed t e r o t o r-stat o r pa i r in the c o mpressor) . St a t or bl ades are ass ume d t o have the same num be r and v o l u me o f ma te ri al a s the ro t or b lades. The s tat or we i ght i s c alc ul ate d by Equat ion (5), w i th K = 0.1 55 f o r h lg h-pressure t u r b ines an d K = 0 . 195 f o r low-pr e ss u re t urbi ne s . Stat or -r o t or spac i n g i s the sa m e a s c o m - press o r s , 17 per c ent o f the r o t o r length . St a t or AR i s taken t o be 83 p e r cent of the r o t o r b l ade AR.

C onn ect ing h ardware an d case w e ight ar e also de t e rmin ed b y the same m e tho ds u sed in th e comp ress ors . T he t ota l we i g ht an d le n g th o f t h e t u rb i ne co m pone n t i s t h e sum o f d is k , blade , etat or , c o n ne c ting h ardw a r e , a n d ca s e . No exi t g ui de van e s (E G V ) ar e a s sum e d i n t he t ur b in e c om p on e n t. EGV ' s , if r eq uire d , c an b e c on - s ld er ed a p art of t he e x i t f r a m e we ig ht. R o tati o nal i n ert i a i s deter m ine d I n th e sa m e man n er as the c om press o r.

2 3

r

3 . 1 .4 Centrifugal Compressors The pr o c e du re us e d f o r u e n trlfuga l c o mpr e s s or s iS a pr sl lm- I n ary d esig n ap p r o ac h si milar i n pri n c ipl e t o t ha t use d for ax i al c om p r e ssor s. Sl a d e v ol u m es an d w ei gh ts e re d etermine d a n d a d isk is s ize d t o su ppor t the b la d e s f o r all o wa b le st r ess l e v el s b a sed o ll i nlet an d exi t flow p at h tem p eratur e s . The followi ng in p uts er e r eq uir ed fo r c en t r i f ugal c o m p r e es or sl o I nl e t Ma t h n um b er o Ma xim u m flrs t -s t age pre ssur e r a t io, which r ef l ec ts t he des i gn appro a ch and tec h nology lev _ l. S t a g e w o rk for thi s s t a ge w il l b e h eld c o nstan t f or th e sec o nd s ta g e.

A l t e r nativ e l y , t he nu mbe r of s t ages can be specif i ed.

o In l e t hu b / t i p rad iu s r a tio o Num ber o f bl ade s and spl i t t ers o Exit Ma th nu m ber o RPMm a x / RP Md e s ov e rspeed f ac tor o H ub i n l e t / ti Pex it r a d ius ratio Only a one- or t wo-stage c en t r ifug a l co m press o r m a y be u sed in a W A TE-S engine simul ati on. T h e t otal e nt hal py c h ange for the c om p onen t is av a ila bl e from th e engine cyc l e d at a. Eq ua l w o r k f o r each s t a ge i s a ssumed , a nd t he n u mbe r o f s t ages i s c a lc u la t ed to sa ti s f y the ma x imum first- s t a g e press ure r a tio r e quir e m en t. W hen the n u mbe r of s t a g es is in p ut , fir st- st a g e p r essure r at io i s cal- c u lated b a _e d o n equal w o r k pe r stage an d t h e i np u t m a ximum p r es- s u re r a tio is igno r ed.

q ' h o tn l o t flnw ar,,_ is dot o rm t n o , d fro m th e _ j) _ c t fi ed Maeh n L llllh_r _llldinl o t e oi? [o Ot e _ fl O W fr o lll the, enclillt_ c2Ft_}_ e dAt_l . _ll,_ inlet hub ( I_ 1 11 ) and sh r oud ( R1 8) ra dii a r e oal . c ul a t e d from th e slm ci fi,_d In let / h u b tip r ad i u s ra ti o ( s ee Figur e 6).

r r .... .. li I ....

M tH

I

R| i!_. m _ - _ _ _ -- _ -- _ . _ J - _ __ Fiqn, , , _ . . t' , ,ntr i f u qal Comp r essoi : / Ra d lal q ' urb in e Soho m atlc.

Ills V n' [1- (h / t.) 2 J lib ) Rll I " h / t R i . s (17 ) The exit tip radiua ( Rt ) i n then ca l c ul.at o d from the i np ut hUl_lnlet / tllle x lt i;adiua r a tio. _'ll e exit f l o w ar e a is d e t e rmi n e d from the :ipe c llTi e d e x it M at h num b er and c orr ec ted flo w f r om the en_l i n t _ i ' ycl t )d a ta, fbe ¢ . 'o m pr e i _ao r e xit blade l e n qt h ( I L L ) I s ¢_al- c ul.ated f;rom this a rea e n d litz A e x i t ilL = 2 rrR t (1 8) OIilGIN / Xt- i , _ ' ". 7 : 7 , 2¢i O f I , Ol',l¢ _,tiat I [hf i

t

d ................... ; ; '; 77;7;7_ Z '_ ;__777 L 7 L.];T LZ _];;;7;772 7];;L]T L _7_ __i__.;__;7_ The ratio of a x ial length to radia l height o f the blade at the shr o u d (Dz / DR ) , i s a ssum ed t o be 2 . , a n d the flo w p a th is a ssum ed to be co mprise d o f t w o ell i p s e s . Bl a de vol um e is compu t ed a s s u mi n g th e b l a de t h i c kn ess at th e shro u d is 0.076 cm an d t he t h i ckness at ! t he h u b r esul ts in 15.- p e rce n t blo ck a g e j

0 . ls( 2 =RI . _

_ , thu b = ..........

NB (19) _ w he r e N B is the nu m be r of b l ades. T he c om p r essor m a t e ria l and ! a ll owab l e b l ad e a nd disk st ress l eve l s a re se l e c ted b a sed on th e maximum tem per a t ure condition s f or th e c om pr e s s o r.

T h e c om p re s sor s p ee d is de t e rmin ed fr om t h e c urr e nt ( 1 982 ) t ec hno l og y d e s ign p r es sure - r a tio c orr ec t ed tip- sp ee d c o rr e l ation ill u s t r ate d i n F i gure 7. O n ce t h e m at eri a l is s e lect ed an d t h e rpm is c a lc ul a ted , the b la de w eight, stress , and natu r a l fre- qu e n c ie s are c al c u l ated.

§_"

I -

! ! I m m 3 § ? 9 11 FIRST-STAGE CENTRIFUGAL COMF R E U OR PftE U UR E RATIO Figure 7 . Ce ntrifugal C o m pr es s or T i p- S p ee d C orr e l a t i on .

26 O R I GINA L F_ALi ; _bE ;

oFP OO R O u ^u r 7

k=i ..... --_ : - _ ._ _= _ _ i_ . _ i _ _ _.. ; _.. =__ _ _ _ . _± ...... _ a

"!

T he c ompressor d isk is size d b y a n Itera_I v e prelimi n ary d esign pro c edure t o sup p ort the bla d es a nd min[ml ze the st a ge wei g ht , while maintaining t h e maximum allowable stress level s t th e bo re. T his is d o n e b y va ryi n g t h e b ore ra di u s an d b a c kside geometr y of t h e d i sk.

Total s tag e w ei ght is t he s u m of the blade, d is k, s h r oud, and diffus e r w e lg hts _ a nd cr o s so ver d u et w eig ht i f a tw o .- s t ag e c en t rl- f u g al c om pr essor is m o deled ( s e e Seetl o n 3. 1 .6 , E qu at io n 32).

RIS + R t Ws hroud = 0.1 673 p ---- _ ....... ( 2 0) W d i f fuser = 0. 2845 p R t 3 ( 2 1) T h e diffu s er radiu s i s a s s um e d to b e 1. 6 tim es t he e xit ti p r ad ius ( R t) and the l en g th e qual to 7 p er ce nt of its diam e t e r.

T he total s ta g e in e r tia i s estimat e d from the fo ll owin g expressi o n :

(22)

Ie en t - 0. 1 0 86 p R _ w here p is the materia l densi ty s e l e c ted.

3 . 1 . 5 R a _ _dial T u r bines 'I T he method d e s c ribed for ce ntrif u g al c om pres sors i s g ene r a l l y the same for radial turbines. T he i np ut data required Is_ o I n let Ma eh n umb e r

g_H / N

o T urbine w o rk c oeffi c i en t , A t = 2 U t o Number of bl a des a nd splitters o E x it M a ch n umber o R P Mm ax / R P Md e s ove rs peed factor.

Only a sin gle-s ta ge r a di al turb ine is all o we d. T h e t o t al en th alpy c h ange f or the turbin e is k n o wn f r o m th e en g ine cycle da ta . The i nlet tip ra di u s ( R t) o f t h e t u rbine is c al cu late d f rom t he inp u t t u rb ine w o r k c o e f f i c i ent an d t h e p r evi o u s ly c a lculat ed s haft spee d . T h e inl et f l o w a r e a i s d ete rmined from the s pec ifi e d Ma ch n umb e r a n d t h e c or rect e d flow f ro m the eng i ne cycle d a ta . T h e in let bl a d e le n gt h i s ca l c u l ate d fro m: A i nlet BL = 2 _ Rt (23 ) The exit sh roud r a d iu s (RIs) o f the tu r b i n e i s a s s u me d to b e 7 0 pe r cent o f the in let ra d i us (Rt) an d the exi t h u b r a diu s (R I E) i s c a lcu l ate d kno w in g t h e e xi t c orre cte d fl ow a nd M ach n u mbe r .

R 1 B = _ R _ s2 _ -Ae_ _i t (24) T h e r at io of a x ial l e ngth t o r a d i al h e igh t of the blade i s ass umed t o b e 2 . 1 , and th e fl ow pa th i s ass umed t o b e c om pr ised of two e ll i ps es. Bl ade v o l ume i s c om p uted the same a s for c entrifu g al c ompres s ors . T he turbine mate r ial i s assumed to be a ni c k el -based s upera l lo y w ith a densit y of 0.007 92 kg / c m 3 and al lowab l e stres s le v els for the b l ade and di s k of 5 1. 7 KN / c m 2 a n d 86. 2 KN / c m 2 , res p e c ti v el y . D i s k w eight is calc u l ated the same a s for the c en- trifug al c om p ressors.

Tota l c om p onent wei g ht is the sum of the blade , di s k , a n d shr oud we i ghts.

2 8 OF pO O RQ UA L Ilnr.

W s hro u d • 0,1 755 p 1251 I_ T he t o t a l iner ti a of t he r a d i al t u r b ine i s e s timate d fro m t h e f o ll ow lng exp r e s s i o n: Zr a d t u r b " 0.1687 p R_ (26) 3.1.6 Du c ts The des i g n c ri ter i a u s e d t o s ize th e d u c ts i n WATE-S is a ss u med t o b e the i nte rn al press u re. S t r u c t u r al l o ads cann o t be add ress ed in the pre limi nary design pr o ce ss whe r e WATE-S is intended t o be u sed. Fi gu re 8 ill u s tr ates the typ l oa l duct ge o me- try a ss u med. Generally, t he ou te r s u r fa c e of t he OD d u ct wall i s e x p o sed t o am b ient p r essu re or f an du c t pr ess u r e . Th e i nner s u r- face of the Z D d u ct wa l l can b e s u b jected t o f an pr e s s u r e , LP c om press o r pre s sure, or HP c om press o r exit pr ess ur e _ etc. F o r these reas o n s , a m b ient pre ss ure is as s u m ed f o r t h e calc u lat io n s o f d u ct wal l thickness, th is a s s u m pti o n re s u l t s I n c on se r vat i v e wei g ht est im ate s .

AREA• A PT2 Ro RI J - 4 I J .

Fig u r e 8. Duct Sche mati c.

T h e eq uation for str e ss on a lo ng itudinal s ec tio n o_ a thin - walled cylinder subje c ted to i n ternal p ressure is (ref. 2): PD c r = _ (27) Or sol v ing for th e min i mum th i c k n ess , t m in : PD (28) trai n = _ ]F whe re (r is t he al low a b l e s t r e ss le v el , P the inte r nal tot a l pre s- su r e , a n d D t he du c t wa l l diame ter. A m i nimu m g a g e thi c kn e s s of 0 . 1 27 c m is a s s u med fo r al l ducts. T h e as sum e d ma t eri al s are t i t ani u m ( or = 34.5 KN / c m 2) b e lo w 6 44 °K (I I 6 0 °R) and s ta inl es s ste el (( r = 48. 3 KN / c m 2 ) above 644° K ( 11 6 0° R). T h e m ate rial i s s e l e c t ed b a s e d o n t he to tal te m pe r at u Ee of the d uc t a i r flo w. T he w e i g ht is cal cLl late d as a fun cti on of t he du ct l en g th (L), the inne r di amete r (Di) , t h e o u ter d i am ete r (D o ) , a n d the ca l cu l a te d w a ll thick ness es ( tmin , i and tmin , o ) _ W du c t = p _L ( D otmin , O + D itmin , i) (2 9 ) D u c t Ma c h numbe r i s sp e c ifie d as a n in p ut , and c orrected air- flow is determined f r om the en g ine c y c l e data. T he inner and outer diam e t e r a re determined as a fun c tion of the requi r ed flow area and the dimensions of the conne c tin g u ps tream c om p onent.

C are should b e t a ken to a s ce r tain w hethe r t he s e a ss um p ti o n s a pp l y for s peci f i c engine c onfiguration s . F or exam pl e , a thin- wa lled c yl inder subjected t o an external c olla ps ing p re s sure w ill fail at a mu c h l ow er p ressu r e than it would if i t were subje c ted to an internal bursting pressure , a s a ssumed in the du c t wei g ht c al- c ulation. If both I D and O D walls of the du c t are ex p o s ed to ambient p r essure , the I D wall should be s i z e d to a v o id collapse , su c h as dete r mined ex p e r imental ly b y S tewart (ref. 2 ) for lap- welded stee l tubes: 3 0 OF POO R QU A LI TY .

Pm a x " 689 . 5 1 - ( 1301 or expre ss ed in t e rms o f mi n imum w all t h i c kne ss: tml n " _ 0 V _ 68 § ,5 ) (3 1 ) WATE- S d oes not pe r for m the above ca l culat i on t o determine whethe r co l lap sl n g p r e s su r e sizes th e I D wa l l.

Cr o ss o ver d u ct s a re r eq u i r ed t o j o in t w o ce n tr if u g al c o mpres- so rs, and a r e calc u late d I n a di f f e r ent m anner. The cr o ss o ver d u ct di a meter i s assumed t o b e 1.6 t i mes the e x l t t l p ra di u s of t h e u p str e a m c e n tr i f u g a l c o m press o r. Th e d uc t l e n g th i s a s s um ed t o b e 20 p e r c ent of the d iam et e r an d t he we i gh t i s est im ate d f ro m th e f ollo w l n 9 expr e ss io n : Wo rosso ve r duct = 2.283 Rt 3 (321 w h ere Rt i s the exit ti p dia m eter of the u ps t rea m cent r ifu g a l c om - pres so r .

3. 1 .7 Burners The m eth o ds u se d f o r b u r n ers a r e ba s ed on a c a l cu l at ed v o l um e o f mate ri a ls , s i m il a r t o the p r e vio u sl y des cri b ed m eth o d s f or d u cts. H o weve r , wal l li ne rs , fuel m an i f o ld s , and f u el n o zz l e we ig hts a r e a l s o ca l c ul a t e d a s sh o wn I n F igu re 9. The meth od described is u se d for primary bu r ner s , b o th ax i al an d r everse- f l o w, a s well a s duct hea ter s an d a f terb ur ner s .

The requ ir e d i np u ts I nclude t o Bu r ner r es i den c e t im e " _ ¢ _ n _ l S i _ h _ ml¢ l l 4_ _ n _ l _lm_ _ ...... i I IIII I I -- - i I I I i1 " I :: ORIG INA L P A C_ S 13 OF PO O R Q UALIT Y o Th r ou gh-flow v e locit y o Bu rne r mea n ra d ius fo r a x i a l p rimar y burn e rs a n d d u c t he a te rs , a nd _,nn er radius f o r rever s e -f l o w p r imar y bur- ne rs .

F i g u r e 9 . Bu r n er Sc h em a t ic.

Th e diffe r ences in burner types an d c o nfigur a t io n a r e r eflecte d in the i np u t v a lue s. When a pri m ary bu r ner is speci- f i ed , a f r a m e weig h t m ay be a dd e d. Pr im ary b urner s an d d uct beate r s re qu i re a r a di u s i np u t , while t h e a f ter b u r ne r i s a s s u m ed t o h av e n o i n ner w al l.

B u rn e r flo w area i s d e t er min e d fr o m th e in p ut th r ou g h fl ow v e l o c i ty, th e m ean rad iu s , a nd th e i nlet-c orrec t ed a irflo w fr o m t h e e ng i n e cycle d at a . B u rne r l engt h i s f ound t o g i ve t h e speci- f ied r es id ence t i me b ase d on th e inp u t vel o c i ty an d ent r y con di - t io n s. Fl o w a r ea is use d t o ob ta i n th e i nne r an d ou ter dim ens ion s of the b u rn er (R i and R o ) from th e s pec ified m ea n radius. I nne r i and out e r c ase thi c kn e s s e s ar e de t e rmined from E quation (28). T he a ss um e d mate r ial is s t e e l with a n a ll o w abl e s t r es s of 48. 3 KN / c m 2 . The we ' ght of the inner and outer c a s e i s det e r n _ined from Equa- tion ( 2 9) usin g the burner len g th L .

OF pOOR Q U AL I TY _iner w e i ght is d e t e rmin ed in a s imi la r m a n ne r , as s u mi n g O. 1 40- cm t h ick st ee l walls , lo ca te d at 20 perce n t o f p a ssa g e h e ig h t fr o m th e i nn er a nd ou t e _ ea s e. The b u r ne r do m e , fu e l m an i- f o l d , fuel no zzl e s , an d o th e r c o mpo n e n t s a r e estim a te d by th e f o l - l o wi n g e quation de v el op e d b y Boei ng .

W dom e ,, 0 . 1508 ( R o 2 - R i 2) (3 3 1 Tot al b ur n e r w ei g h t i s th e sum of th e inn er an d o u ter c ases and l iner s , b u rner d om e a nd f u el n ozzle syste m , an d fr a m e w h en spe c i- fied.

3 .1. 8 Sh a f t _ _ s A sh a ft i s a ss um e d to b e t h e p o wer co n n e c t i on c o mp on ent b etwe e n c o mpr e ss o r s a nd t u r bin es , o r pr o pellers / pr o pfan s an d t ur - bi nes. Fi g ure i0 i ll ust r a te s th e s haf t g e om et r y an d nom e n c l ature.

• CLEARANCE Do DI ENLARGED SECTION OFC O N C ENTRIC SHAFT Fi gur e 10. Shaf t S c he matic .

i Mu l tip l e co n centric shafts can also be specified , and wil l be sized ar oun d t h e i nn e r s ha ft w it h 0 . 38 1 - cm radial cleara n ce , Dime n sion s of t he inne r s h aft a r e d ete r mi n e d t o p ro vi d e t h e n eces- s a ry t or que c a pabilit y a t t h e speci f ie d a l lowab l e stress . T o ta l s ha ft p o wer Is t he s u mmati on of w ork f o r a l l turbi n es on t he shaft. T or q u_ is c al cu la te d by : 1 05 T = ...... Z PW (34) whet6 _ i s t he s haf t r o tational s peed , S h ear st r ess du e t o t he t o rqu e lo ad is def in ed by ( ref. 2 ) 16 T D O T = O i _- ) (35) _ (Do4 - or i n t er m s o f t h e i n put d i a me ter ra tio (D i / D o ) = 16 T --

o [ t ) J

S o lvi n g f or D O in ter m s o f a llo wa ble str e s s D o = ............ T I J --_ - (37) ? r T - The s ha ft w e igh t is t h en f o und b y II = L p _r- - _ - - i - _ - 7 (38) O f p OOll QtIA L I T f A sim il ar pro c e du re is u s ed f o r c on centri c shafts . T he ou ter shaft's i nn e r d iameter is f o un d by a d di ng 0 .7 62 em t o D O , and Equ a tion ( 3 7 ) is solve d b y ite r ation to s a t i sf y the desired allow- [- a b l e st re ss.

W hil e it is a s sum ed i n th e s h aft we ight estimate t ha t t o r q ue d etermines t he sh aft di m en sio n s , it sh ou ld b e r e c o gnized t h at oth e r de si gn con si der ati ons m a y dic t a t e sh a f t d i mens i o ns . S ha f t critica l s peeds or l on g i t u dinal s t i ffne s s m a y a c t u ally des i gn th e s h a ft , bu t this is a fun c tio n o f b earing a r ran g e m e n t , mo u nt s t i ff- n es s, l o cat io n of a n d sti f fne s s o f ro tat i n g m ass e s. Th e cal c u- l ate d s h af t wei gh t s h o u ld b e co ns ider e d t o b e an a bso l u t e m i ni m u m , a n d c an p o ssi b ly b e mu c h larger when t h e s e o ther c riter i a a re c o n- side re d . The r o tati o nal inert i a o f the s h a ft i s n o t calc u lated , s i nce it is a ne g ligi b le q u ant i ty c om pa red t o the c o mpress or s an d tu rb ines.

3.1.9 F ra me s A s truct ur a l f ra m e i s no r m a l ly r equ ired to sp a n t h e e n gi ne f l o w pat h f r o m t h e o ut e r engi n e case t o t he sh a f t , u s ua l ly t o sup- p o rt a b ea ri n g (as s ho wn in F igur e ii for sev e ra l typ i ca l e n g i n e s). M ec h an i ca l de s ig n of t h e f r a m e w ould r e quir e a d e fi n i - t ion o f a ll l o a ds i m p o s e d o n the f ra m e un d er n o r m a l o perat i ng c on - di t io ns , t r an s ients , an d a d ve r se o perat i n g c o n ditio ns , s u ch as a h ar d l a nd in g . Th i s l eve l of d eta ll i s no r m a ll y no t av ail a ble at t h e pr elimi n ar y desig n s tag e for w hi ch WAT E -B h a s b een d eve lop e d .

B oein g h ad f o un d , ho wever _ th a t t he fr a m e w eigh t co r r e la t es w ell with the tota l frame- p roj ec ted a rea. T hi s dat a is s ho w n in Figu r e 12 for five t yp e s of fram e s c ommon ly used : slng l e-be a tlng frames with and w ithout p o w e r takeoff ( PT O) , turbine exit , a nd inte r mediate. Frame wei g ht i s determi n ed from thi s dat a , based o n the lo c al diameter and the t yp e of frame s p e c ified.

ORIGINAL P AG E I g O F POOR Q U A LITY /* '% _T YP e , . , . . _ , T YP[i 4

..."tYp e 2 , "r _P e 4 /.. _ , , 'rY ee 3 A,O

Fig u re i i. Fra m e Typ e s. !

3 6 J O RIGINALi , , . : i : _ OF POORQU / _ .I'! Y _ , _ IN Q_I_I ARINO P R _R WI TH OUTPy Q |, I IN QLU_| ARIN _ FR _| W I_ P _ I , T W RNINR FR _ [W A TK , I _ R a l I N _ lN|l 4, INT R RMR _ IAT | I , N_ AfllNQ _n _ flN _ fl FR _ i _, | , TUR N IN| F A_I (WAT| , | N A b k |NRINRI 1 _ . | |0° o,_ 0 3 0 o _a o _ _ TIP RADIUB8 F i gu re 12. Frame Wei ght.

3. 1 . 10 Nozzl es and Thr u st R e vers e rs Un l lk e t h e r o tating comp o nents, th e lo a d s an d lo a d paths o f n o z zl e s (partic ul arly v a riab l e ar e a C-D n ozzles ) a r e n o t rea dily d e f i ne d o n a ge n era l ba s is. A s e l e c te d typ e o f n o zz l e c o u ld be s u b jecte d t o a d e t aile d w el ght-est im a tl ng p ro ce du re , h o weve r , th e tr a d e- el ls of i n ter n a l an d e xternal pe r f o rmanc e with n o zz l e l eng t h and diamet e r w o u ld a l s o be necessary t o opt imi ze the d es ig n. T hi s type of data is n o t lik ely t o be avai l ab l e a t the l ev el of d ev elo p- m ent f or which WAT E- S i s i nten d e d .

A pr oc e d u re has been d e v e lope _ that sho w s pr o per t r e n d s f or mu lt i ple-strea m n o zzles a n d f o r va r i able ge o metry an d f ix e d - ge om e t ry n ozz les. N o zzle length Is spec ifi e d a n d sh ou l d be s e le cte d t o be r e p r es e ntat i ve for t h e typ e of n ozz l e . A n e ff ec- t i ve surface area I s c a l c u late d b a sed o n the di a m ete r o f t h e co n- nect i ng c o mp o n e nt an d the s pec i f i ed len g t h. Only cir c ul ar, c o ni- cal no z z le s a r e a ss umed , an d c o ann u la r n o zzles c an be re p r esente d by s peci f y in g a o lr c u l a r n o zzle for each fl o w p a th. P l ug n ozzl e s c a n b e r e p r esen t e d b y sp e c / fy l n g a la r ge r e f f e c tive l e n g th; e.g. , fr o m nozzle entry to e nd o f p l u g.

ORIGINA L pA GE | _ OF pOOR QU A L I T¥ Wall tl , lcknees ie assumed to be a 0.1 6 2 6 -0m compnelte of titanium f_. 3 Cl 3 . - cm ) a n d stai n less s t eel (0. 08 1 3 -_m ) below 64 4 " K (II 6 0'R ) and 0.0 8 1 3- 0m stai n l e ss steel nb o v e 64 4 " K (II 60"R) .

V a r iable no z z les a r e ca l culate d i n the came m a n n e r ex c ept th a t the effe c tive wa_l thick n eH Is 2 . 7 5 times t h at of the fixed n ozzle , A wei g ht estimati ng method for th ru st reversers prevlo u sly developed for al rc raft p r elimi n ary desi gn at u dl e e by Boei ng wa_ based o n the wei g ht of 1 8 differe n t thr u st r eve r se r s that are i n current u se. I t had been fou n d in co r relations o f this da ta t h at r eve rs er weight (W) is a f u nc ti o n o f c orr e c t e d m ass fl ow (_ ) and nozzle pressure r at io ( P R) , a n d is d e pen d en t o n whe th er the s t rea m is ho t (pr im a ry ) or cold ( r an). T he follo w i n g i: e la t l o ne h i p is in c l u ded i n WA TE- S : Hot (p r r. 0. 52 6 3 1 191.87 1 .00 3 6 -0. 5 0 54 [ _ q g _ _ _ i_o n d ar _) 2.2222 5. 0 348 0 .23 01 4 0 .56 0 9 1 T h e WAT E -S me t hod will apply th e c old s t ream e q u at ion t o a fan s tre a m whether or not it is h ea ted b y a du c t bu r ner. T h e hot s tream equation is used fo r turbine exit or mixed-flow exhaust s tr e a ms.

3 .1.11 Mixer s A mixe r i s a me c h a ni c a l de v i c e p la c e d a t t he c o nf l uen c e of _ two co a nnu lar s treams to i ncr e a se t h e mi x i n g boundar y s o that thermal mi x ing takes p la c e in a mi ni mum length. Fi g ure 1 3 i l lus - tra t es a t yp i c al e x amp l e o f a _ ' xer. Th is t yp e of mi x er is k no wn as a dais y mixer or fo rc ed mixe r .

38 t t OR I G IN AL p . _,, J_ OF POOR QUALITY Figure 13. Da is y o r F or ced M ixer The re quir ed i n puts in c lu de: o Mixe r s pecific length , Lsp -_ o N u mb e r o f l ob es or pas s a g e s , N o E ngin e co r e a n d b yp a ss flo w areas , A II and AI O

E ngine c o re a nd byD as s annular f l o w a r ea s a r e taken from t h e

engin e c yc l e d a t a , a nd t h e Inl et r a d iu s ( R I ) of t h e upstrea m c o m- ponent i s us ed a s a s t a rti ng p oi nt fo r lo ca t in g R m an d R O , a s shown in F i g u r e 1 4. R i n or m a lly w i l l b e t he hub r a dius o f t h e fln a l tu r bine stage.

. S9 OF pOO R Q UALI ' P / Rm i s b ased on core f l ow area (AII) and R i A - ( A IO + A Z l) / 2 where AIO and AII a r e input s Ls p = L / _ 4A _ - i s an i nput, c a lcul a t e L N = is the num ber of lobes o r pas s a g es input W ml x = 1. 25 N ( R o -R m) L K 1 Wplug = _ R i L n+' 6 _ - _"[_ , K 2 I _ R i 2 K 1 and K 2 are p r o d u cts of m ater l a l den si ty a nd th i ck n e s s l K 1 - ( 0 . 1 27 c m ) ( 0 . 00 7 7 5 k g / c m 3) = 0 . 000 98 k g / e m 2(stee l ) K 2 = (0 .0 813 c m) (0 . 0 0 775 k g / c m 3) = 0. 00 0 63 k g / c m 2 (steel) F ig ure 1 4. M ixer S c he m at i c.

Th e m i xer i s a ssu m ed t o con sist of two c om p onent s , t he m ec h - ani c al m i xe r s e c tion a nd the m ix er c or e p lug , both fabri c ate d f r om stainless steel with a densit y of 0.007 75 k g / c m 3 . T h e average flow 4 0 area of the mixer t e u se d with t h e i n p u t s peci f ic le n gth t o d eter- mi n e the l en gth of the mec h a n ical mixer secti on . The mechm n ical mi x e_ s e c tio n is assume d t o be c o n structe d of 0 . 1 2 7-cm mate r ial and the weight estimated from the following e xpressio n : W ml x - 1 .2 5 N ( R o - R m ) L p (0.127) (4 0 ) T he mixer core pl ug I s a ssumed t o be con s tr uc t e d of 0 . 08 13 -cm m a terl a l a nd h a s a cylind r lcal section a s w el l as a conic a l s e c - ti on . Th e mixer plug we igh t is est im a t e d fr om t h e f ol l o w i n g ex p res s ion : W plu g = _ R I L + i_10.0 8 1 3 1 1 4 1) T h e t o tal mi x _' .we ig ht i s th en: W = _ix + W plug (42 ) 3. 1 . ] .2 Annulus Inverting Valve (AIV 1 Th i s d ev i ce ha s b e e n u s ed in som e va r i ab le-cycle en g ine s t o _n v e rt th e annula r p o s ition o f tw o con ce ntric flo w p a t hs . It acc omp l i shes t he flo w i n v e rsion w i t hin a c o ns t a n t di a m e t e r en v e- l o pe , a nd w i t h c o n s ta n t-ar e a duct p a ssage s. F ig u r e 15 s ho ws a typi c a l ex a mple o f a n AIV, T hi s AIV w a s de s ign e d to v a ry t h e b y p a ss ra tio in a JTSD en gi n e .

T h e A IV weig ht m e thod a ss u m e s a c ons t r uc t on s imi l a r t o t ha t sho w n in Figure 15 , ex c e p t th at in s t ea d of s he et- me t a l , the m a ter - ial is as s ume d to be a titanium hone yc omb a t 5 . 37 kg / m 2 belo w 644"K (II G 0° R ) a nd s teel hone y c omb at 9 . 13 k g / m 2 a bove 644"K (II60 ° R). If d e s ired , d iffe r ent mater ia ls can be sp ec ified.

4 1 O F POOR OLI ALII¥

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rFOR W ARD HALF O F AIV ' Figure 15. Typical Annulus In v erting Val ve : JT8 D Variable-Bypass Engine Test.

ORI C . , I, _ , I . t _L | _ , ' , .. . _ : _ OF P OO R QUALI'I Y A n e mpi_ ' i cal re l a ti on s h i p , similar t o t ho mi xer m e t hod, had been dev el oped by Boein g for estim a ti on of t h e A IV wei gh tl F ', W AI V - L • _ W [ 2 T r (R i + 2. R o / +, 3.93R M + 1.25N(Ro-R i ) ] ( 43) wher e R i is the h ub rad i us o f t he ups t rea m c onnec ti n g component , a n d Rm a nd RO a r e f o und to s at is fy t he i npu t M a cl l nu mber w i th t he i nle t correc t e d a irfl ow ( s ee F i gure 16) . T h e n u mber of passag es ( N ) i s an i np ut , and m a t er i al we i g ht pe r u n it are a (W / A ) i s s e le ct ed d e p endin g o n t he s t r e am temp e ratur e . L e n g t h (L) o f t he AIV is c al c ul at ed from t he i np u t spe ci f ic l e ng t h , LSp : L = L ep x f 4 n/ _ _ (44) I" t :' LSp- L / V; _ ' _ " INPUTA- (AouTER+ AINNER) 2.

FROMMACHINPUT A I NNE R ANDACUTE RAREFOUND L ISDETERMINED WTIC-2 RI L WTSI WT O C'2 R o t W l "SO WTWALL- { K! RM+ K 2N(R o -RI) ) L WTSW WTSI , WTSOANDW T SW ARE MATERIALWEI G HTPER UNIT AREA R M - K1-3,927 K2-1.25 [,'iguI : e 16. An n ulus-Inverting V a lve Sc h e mati c.

Spec ifi c l eng th te p r e f er r e d as an In p u t b_ca u s e it i s non- dim en si on a l, a nd I t l ea maj or vari able t h at de t e rmi ne s A ZV p res - su r e lo ss . A r e lativ el y good co mpr om is e be tw een si ze a n d p e r E orm- ante is ach i eve d when N- 8 an d LS p -O.6 t o Z .O, wh i ch r e sult s i n a pr ess ur e lo ss be tw een 2.5 and 1. 5 pe r cen t .

If th e AI V is o f t h e sw i tc hi ng type, where on e half i n dexes i n • ro t a ti ona l dir ec ti on re la t i ve to the o t her h alf t o change fl ow-pa t h or i entat i on, an actua t or we i ght i s e s t i ma t ed a t 1 0 pe r - c e n t o f t o t a l AIV we ig ht . A ddi t i o n a l s tr uc t u re to s u pport t h e r otat i n g n_i f is n o t included a n d sh oul d be represented as an a d d i t io nal frame.

3. 1 . 1 3 Gearboxes and Transmissions A m eth od o f e s t im at i n g the weight o f vari o us types of g ear s yste m s has been prev iou s ly d eve lo ped b y Sch mid t ( r ef. 3). Th l s m eth od has pr o ve d appl i cable fo r e stim at in g the w e i g ht of t u r b of an en gi ne g ea rbo xe s , such as the o ne I n the Garre t t TFE73 1 . T h e eq u at i on u s e d f o r t o tal gearb o x weight is PW (4 5 ) Gearbo x Wt - 1 5.5 . _ . ( I . + GR) 3 PW whe r e GR-'R _ R P M_ de fine s the m a x i m u m t o rque t r an smi tte d and GR - g ear r at io (> i.)

The g e a rb ox used i n turb o pr o p engines i s we i ghe d with a d l f - r e c ent m eth o d.

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Gearbo x Wt - 471.86 _ Pr op . R PM (46) 3. 1 .1 4 Heat Exchangers Bot h r o t a r y a n d f i xed heat e x ch a ng er we i ght s ca n b e e st i - 1_ ated . M et hod s prev io u s ly d evelope d p r o du ce adequate re s ult s for p reliminar y d es ig n purp o ses , see Fi gur e 17 .

4 4 For rot a ry h e at e x c h a ng e r s, a ce rami c c or e is a s s u me d .

W e i g h ts o f t h_ s typ e of h e a t e x c h a n g e r h ave be e n de ter m in e d b y th e C omi ng G l a ss C o m p a n y (r e f . 4 ) a n d a r e r e p r e s e n t e d I n T a bl e I f oe v a r io u s l eve l s o f e f f e c t iv e n e ss a n d pr e s s u r e l o ss. T h is da t a is d e v e l o p e d fo r a t o t al c o rr ec te d a ir f lo w o E 9 0 .7 kg / 8 . F o r o t h e r s i z e s , t h ese we i ghts ar e s c a l e d dir ec tly w i th c o r r e c t e d fl o w.

TABLE I. CE R AMIC ROTARY R EGEN E R ATO R WEIGHT 9 0. 7 k g / s c or r e c t e d w e ig h t f l ow BPR 3 7 i0 &P / P (t) 5 1 0 5 I0 5 I 0 We i g h t (k g ) • = 80t 305.7 245.8 284.9 201.8 272. 2 191.9 85% 440 .4 342.0 414.6 290.3 378.3 279.9 9 0 % 735.7 538.9 64 7 .7 4 9 2. 1 595.6 450.9 l _i Fi x ed-tube heat excha n gers are e_timate d by a heat - tra n sfer i' analysis (ref . 5 ) wh ere t he re qui r e d tub e surfac e area is found t o _ giv e th e ep e o i fi e d e ff e cti venes s . F low ar e a of t he tub e s i s fou n d _. fr o m a n i n put M a c h n um be r , n um ber o f t u b es , a n d c o r r e ct e d fl o w .

A n estimate o f t he p r ess u r e d ro ps i s ma d e fo r t h e i npu t nu mb e r o f t ube s ba se d on i npu t rel ati ve rou g hne ss valu es f o r each f lo w p a t h.

The flo w Re y no lds nu mb er is cal c ul ated an d t h e M oody di a g ra m is u se d to estimate t h e fricti o n f actor , and th u s t he p re s s u r e dro p .

The s e calc u la t ed _ P / P 's c a n be use d to a s ce rta in whether t he n u m - b er o f tu b es sel e cted is reas o nable. Wall t hic kn e ss o f t he t ubes i s d e te r m i ned b y Equati on ( 28 ) t o s atisf y an a s sumed all ow a b le stres s o f 3 4.5 K N / c m 2 and a d e n sity o f 0.0 0 4 65 Kg / c m 3 b el ow 6 44 ° K ( II6 0 ° R ). A s tress o f 48 . 3 K N / c m 2 a n d a density of 0 .007 92 Kg / c m 3 is a ss u m e d a bo ve 6 44 ° K ( II60°R ). Minimum wa ll thic kn es s o f 0. 0 2 5 4- c m is use d f or th e tu b e s. The leng t h of th e tu b es i s d ete r - mined t o sa t is f y th e sur fa c e area re q uire m e n ts . F ixed -tu be h e a t e x c h ang e r t ube w_ig h t (Wtubes) , is t hen f ound b y Wt u b e s = p L = ( R e 2 - Ri2 ) ( 4 7 ) w here R o an d R i are t h e tu b e ra di i an d L i s the t o tal l e ng th re qu ir ed. A w r ap- u p f act o r o f 1 . 8 5 i s u sed t o acco u n t f or th e w e i g ht of the c asing s , m o u n tin g har d ware , m a ni f o l d s , an d ot her eq uipmen t that m ay be necessary.

WHTEX = 1 .85 . Wt u be s (48)

3 . 1 . is

Tb _ fo l l ow ing ex p ress ions for es tim a tin g t he w e igh t an d diam- eter of ad van c e d t ech n ol og y p r o pell er s and pr opfans we re d e rived from m e t h o d s d evelope d by I I a mi lto n S t a nd a r d (r ef . 6 ). It i s noted t ha t t h e s e expr e ssion s a r e based u p on a con ve n t iona l blad e of t he s t ate d materi a l s w i th a g ene r ally re c t a n g u l a r p lat f orm s h ape , an d •...... • , 9 ORIGINAl., _ ' ."' ' _ I : O F poo f t Q U . _' ' " _ a standard l_lan_e_ sha nk . Th e blade w e i g ht relations are for o o m . - mon propeller m_teria l sl c om p osite a n d aluminum. If othe_ materlals are desired , a d e nsity ratio c an be used t o estimate the weight. H o wev e r , a l lowab l e working stresses and blade stiffness may v ary an d considerable j u d g e ment is r eq uir e d t o a c co u nt f o r thes e effects.

Th p express i on used i n WA T E -S f o r double acti ng, advanced t echno l o gy p r ope ll er s is

P ro p . t - K _ _ 100 / 3 z 9_

wher e K = 42. 6 f o r c o m po si te m a t e ri a l s 57.6 f o r a luminum D = d iam e ter (m) N = num ber of b lades w bl ad e ac ti v it y fac tor PW = ma x imum s h a ft powe r ( KW att) M n = des i_ c rui se Math num b er U t m 10 0 - p _r c e n t d e sign ti p s_ed (m / s ) T h e expr e ss io n for pro pf a ns i s

. . 4 6 + 2 . o o 5 t

15 0 1 Th e i nput qu an tities a re ti p sp ee d , PW / D 2 or D , the n um be r o f bla d es , acti vit y fa c tor , an d d e sig n c r u i s e M a t h nu m be r. The cal- cu l a ti o n pro cedure de t e rmines t he diameter if n ot i np ut , t hen th e p ro p eller R PM is ca l c ulated fr o m the ti p sp ee d , 60 U t RP M - (51) n D end fina ll y th e prop e ller or propf a n wei g ht i s calculat ed f r om th e ab o ve ex pr e ssi o n s.

3.1.1 6 Accessories Access or y weight data was c o l l ected from twelve gener a l avi - a ti o n airc r aft manuf a cturers an d was sup p le me _ , te d with Garrett da t a for sev er al e ngine s . T h e dat a is presen te d i n Tabl e II and i n clu de s 22 v ari o u s turbofan , tu rb o p ro p , an d turbosh a f t e ng ine s ra ngi ng in s e a l eve l s ta ti c th r u s t s f rom 2 .67 KN to 22 . 46 K N an d m a xi m um s h a f t h or s e p o w ers f r om 0 .373 m Watt t o 1 .163 m Watt.

A tremen do u s mnou n t o f s c at te r e x ist s in the da t a , an d h ence , se p arate c orre l atio ns for e a c h ac ce s sor y we r e not p o ss ib l e. B at- tery we ights var i ed and we re g ener all y t h e he avies t access or y.

F or t he se re as o n s , t he sta r t er / g e n e r at o r , h y dra ul i c p um p, oi l p u m p, and fu e l p u m p w ere l u m p ed t ogether an d a s ing l e corr e l at ion deri v ed for t he se acce ss o ri e s (n o te that the b atte r y i s n o t i nc lu d e d ).

A CCS W t = 1 8 . 2 + 0 . 02 ( ba re en g ine weight ) (52) I f th is calc ul at ion r e s u lt s i n an acces so r y we igh t f ract io n l e s s tha n i0 percen t of the b are engi ne wei g ht , th en i0 p er c e nt of th e , I b a re engi ne we ight is us e d for th e a c c e sso rie s. T h e ba r e en g in e w eight w here this bre a k p oi n t o cc ur s is 19 8.4 kg.

3 . 2 Ot her P rogram Fun c tio n s a nd C _ e s 3 .2.1 F l i___._t Envelope M aximization In the normal u s e of the W A T E- S p ro g r a m , a f li ght en v e l o p e of engine cyc le dat a w ill be generated. S in c e the w ei g ht of ea c h 4 8 ORIGI N AL PAG E r ,_ OF POOR QUA_{ I " !

com p onent Is af£e c te d b y its maximum work , flow , temperat u re , a nd speed! t h ese ma x imum va lu es are st o re d f o r u s e i n t h e d ime n sio n

a nd w ei gh t c el c u l atl ons . The flig h t c on dlt l o n i s g iv e n i n t h e

o utp u t d ata wh ere t h e m a x imum cond iti on occu rs for ea ch com p onen t .

3.2.2 Deal_n Limits A s a n ai d t o assist t h e us e r i n ac h i e vi n g • re as on a bl e e ng i n e d esi gn , the ou tp u t w I Z 1 pr o vi d e a war n i n g a nd s uggested c o rrective a ction t o br ing th e eng i n e desi gn w i t hin re aso n a b Ze li m i ts . Thes e limits can be sp e cif ied , o r default v a l ue s w ill be used i f no t s p eci f i ed. Tabl e S ZI s h o w s a ll s t of wa r n in g s an d correc t i v e a ctions, 3.2.3 Automat ic Ai rflo_ • Scaling T he W A TE -S p_ o _z a m w i l l a u t om a tic al l y sc a le th e eng i ne ± 2 0 per - c en t of t h e size t h a t is d ef i ne d b y t he ther mo dyna m i c i nput .

Up to s i x s el e c te d scal e fa c tor s c an als o b e spe cifi ed. A s ca l i ng e xp o n e nt ( _ ) i s ca l c t ,late d f o r ea ch scal e d eng ine base d on the f o ll o w i ng e x p r e ssio n:

w - " R r \ a R E / ( s3 )

Ii T h e s c al ing exp on e n t (_) fo r each eng i ne s i ze i s pr o v i ded in th e ou tput d at a .

3.2.4 Engine Center of Gravlt_ The cen t e r o f grav i ty o f ea c h c o mpo nent, e x c ep t th e ro t a ti ng com p on ent s, i s a ss um ed to b e th e mi dp oin t of its le n g th. T h e mo m ent rel a t i v e t o the f ro nt fl a n g e of the eng i ne is d e termi ne d a s a f un c t io n of t he p osi t io n of e a c h com p o nent.

5 0 I P ORIG IN A L P AGE IS TAeL_ ZIZ . DE S I a N L I M I T S OF P O O R QU ALIT Y ' De fau l t V a lue ' Warning Message Acti on R e oo mm ended T est e d Aga i n st , , i Bla d e C entrifu g a l R e d uce s h af t s p ee d _r - 34.5 K N / cm_ psi H PT

S t r es s Ex cee d ed ( b y rpm sc a l ar| or c r - 4 1.4 R N / cm ; psi LPT

i nc r e a se ex it Ma th cr . 55.2 KN /o m " p a l num b er fans an d ax ia l co mpr e sso r s h / t T oo La rg e R e d u ce h u b / tlp h / t - 0 . 93 HPC e xl t r atio i np u t i ii i h / t T o o S mall Inc r eas e h ub / tlp h / t = 0 . 32 fa n , LPC, H PC r a tio i np u t i n l e t ' h / t - 0.5 0 HP T , LPT ex it T ur bi ne W o r k Add tu r bine _ tag e s _ = ] .39.6 K J / k g To o Hi g h dec rea se A m i np ut A m. . H PT , LPT . , i l St ag e PR T o o Red u c e s tage pres- PR = 1.8 f a n Hi gh s ur e r a tio input PR = 1.6 5 HPC , LPC i Flo w Velo c it y D e c r ease s t age M nex lt = 0 . 6 0 all T oo High in l e t Mac h n u m ber c o mp o n e n ts i np u t ,i Bla d e Size T oo C h an ge o ve r all h B - 1. 0 1 6 c m all axial S ma l l p ressure rati o o r com p r es sors r ed u c e h / t in p u t C o m press o r W or k A dd co m press or _ = 0 . 9 a l l ax i al C o e ffi ci e nt T oo s t ages or i ncrease c om p r ess o r s High hu b / t ip r a ti o Pe r r o t a t i n g comp o n e n t s , t he w eig ht of ea c h a tage is asB ' _m e _ t o ac t a t mi d - le n gt h of t he stag e . _ o me n ta ar e s u mm ed a bo ut t he f ront f l a nge f or e a ch s t a g e. The cen te r of grav it y of e ac h r o t a t - i ng com p on e n t a nd t h e t o ta l en g i ne l a c a l culate d. CG locatio ns a c e s hown i n t h e o ut p ut d ata f or t h e t o ta l e ng i n e a nd eac h c o m - po n e n t, 3 . 3 Program Val lda t i? _n A verificati o n o f the a c c u ra cy of t he WATE-S me th od can only b e do ne b y a pp l yin g i t t o v a riou s types o f en gi ne s en d com p ari n g the re s u lt s with t h e act u al m e asured engine w eig ht a n d d i m en s i o n s , or with t h o se e st im ate d by the m an u fa c t u re r f o r propo sed e n gi n es .

Since t h e man u fa c t u rer 's e s t im ate of p r o p o s ed en gin e s al so i ncl ude s s o me err o r, the real devi a t io n or err o r o f the WAT E -S m ethod c an o nly b e fou n d by c om p a r i n g e n g ine s that h a ve been built i n prod u c t io n q u al ltiti e s .

In o r d er t o d e mon st r ate th e acc ur acy of WATE-S, the NASA P ro - g r a m Manager and Gar r ett J o intly s e l e c ted fo u r Ga r re t t p ro pul sio n en g ines for c om par is on . T h ese in cl ud e d b o th pr od u ct io n a n d pr o - posed en gi nes. Res u lt s of this co mpa ris o n are p r esented i n Fi gu re 18 . As can be seen, th e pre di cte d engine w eig ht a nd o ver- all dim en sio ns of the se l ected en gi ne s are w i th i n the ± i0 percent acc u r a c y g o al . i ORIGINAL pAC E | S OF pOOR QUALITY D WEIGHT Q DIAMETER

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5 .5- TPES31-10 TPEIO§3-2* TFE76-1 ETFIO§0-20* •I0 *PROPO S AL ENGINE S Fi g ure 18. W AT E - S P r o g r a m Re sul ts C om pa r ed t o Gar rett We i g ht D at a.

! : 53

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4. 0 U B EN S M AN OAb T h is s e c t i on c o nt ai n s a d escrip t i on o f the WATE- B i n put a nd ou tp u t d a t a, valu e s of ty pi c al i n pu t s, sam p l e oas es , an d p rogram st ruc tu r e d e fi n iti o n . WAT B -S is d esig n e d t o fu nc ti on wit h a r um - .

pon ent t y p e th e rm odyna mi c e n gi ne cyc l e a n aly s is p rogr am. The t herm odyn am i c eng i ne desig n p o int may b e u se d to g en e r a t e t he WATE-S inp u ts, or ad di t io n al o f f - d e sig n p o ints can b e used and the m a x i mum co n di ti o n s of com p one nt w o rk, fl o w, t em p er at ur e, and pres- sure a r e used t o size the turbom achiner y c o mp o nent s. I n o rder to achi e ve t h e m o st ac c ura te engine we i ght esti m ate, the off -de s i g n c a se s s h ou ld i n cl u de t he m ax im u m pe rforman ce le v els r e quire d of e ac h c om po nent.

WATE- S w i ll a ls o ac cep t input w ei g ht sca la rs fo r e a c h c om- pone n t so t h a t c om p o nents m ay be se lec tiv ely e l imi na t ed , i ncrea se d , c r d = _ c _e d in wei ght to d e te rm ine s ens itiviti e s , e t c .

I n p ut and out p ut unit s ma y b e e ith er Engli s h or S I.

4. 1 Input Description and Formats Th e inp u ts of WAT E - S a r e a rr ang ed i n t h r ee N AZ4EL I ST gr o u ps : $ C for the c o nfi g u rati o n d at a , ST f o r the the rmod yna mi c d ata , and SW fo r t h e a er o me c h a ni cal d e s i gn d at a. The conf i gurati o n d ata i s inpu t o nly o nc e p er W A T E -S ex ec u t io n, w h ereas t h e th e r mod yna m ic a nd aer o me c h a nica l desi g n in p ut s are g r ou ped in pa i rs. T ab l e IV pro vi d es a su _ n ar y o f t he i np ut v ari a b le s. Figure 1 9 i ll u s trate s a t ypical ca r d st ac ki ng a rr ange me n t to ex e c u te W A TE-S. Th e fol l o w ing sect io ns di sc us s e ach of t h ese NAMEL I ST g r ou p s in d et ail and prov ide typ i c al a nd de fa ul t va l ue s w h ere appr o p r iat e .

5 4

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_ . P mO _ i ' _ M a. I ' _ Q J _ . _1 r-I i ' , _ ,,-* 1 . 4 _r-I I _ U _ I _ .1 II n II 4 J 4 ,J 4 J * u ) u} v} I ! !

0 '_ U . r _i I _ .r.I 0 0 0 of pOOR QUAL I TV END IWT • 2 , ILBN G m S ,ri J So6,? _ , 10 W END ;.271, 3 .149,3,149,3.101 S T :ARD - THE R MODYNAMIC INPU T ; END NO S TAT - 13 , NCOMP - 11 , TITLE CARD - CONFIGURATION JOB / USER CONTROL CARDS Figure 1 9. Deck St a cking.

4.1. 1 Configuration Inputs Th e engine conf i g ura t io n i np u t is c ontain e d in th e $C n a m e- li s t . Zt is prece ded by a titl e card d es cri b i n g t he en gi ne con - fi gu r a ti on o r a n y o th e r d e s c ripti on th e user might d es ir e. T h e con figu ra ti on input s fully de sc rib e t he co mp o n en t c onn e c ti v ity an d d ef in e t h e f l ow s tati o n s t hro u g h o ut t h e e ng i ne. Th e fo ll ow i n g varia bl e s were or igi n ally su pp l i e d b y NNEP (ref. 7 ) i n WAT E -2, bu t i n W&T E - S ar e requ i re d i np ut .

"N COMP" is an i nte g er varia b l e d ef i n i n g the t ot a l n um b er o f i com p o nents us e d i n the WAT E - S engine simulati o n.

"NOSTAT" i s an i nt eg e r varlab l e d ef i n i n g t he t o ta l n umber o f fl o w stati o n s u s ed fo r the the r m o d yna m i c sim ula- ti o n o f t he en g i n e.

"JTYP E " i s a o ne-dlmen s l o nal integer a r ray c o ntaining t he type o f c o mp o nent.

1 I nlet ' INLT' 2 D u ct 'DUCT' 3 Water Inje c t io n ' WINJ ' 4 C o m press o r ' C O Mps 5 Tu r b i ne ' TURBO 6 Heat _ xchan g er ' H T E X' 7 Splitt e r e SPLT' 8 Mi x er 'M IXR' 9 N o zzle 'NO ZZ' i 0 P r opel l er e P R OP' (thi s com ponen t known a s ' LOAD ' i n N N E P) ii Shaft ' S H FT ' " JCON _ " iS a t wo-d i m en si on a l i n t e g e r array d ef i n i n g the c o mp on ent connectivity usi n g the _ low st a ti on numbers. I t i s o f th e f o rm J CON F( M, N ) wheze M Is the co mp o nent num b ez , and N is the variab l e n umber a s des c ribed be low .

Location 1 is th e p rimary u p stream ai rflow st a ti on n umb er fo r f lo w oo mp one nt a _ o r th e fir s t oor _p o n en t h oo ked o nt o a s haft , o r th e s haft h oo k e d on to a propel l er .

2 is the s econ d a r y up s t r ea m stat io n n u mb e r , or t he s e c on d c o m p o nent hoo k ed onto a s h af t .

3 i s th e pr im ary downs t r e a m s t a tio n n u mb er , o r th e thir d co m p o nen t hoo k ed on t o a s ha ft .

4 i s t h e secondary d own st re am s t a tio n nu mb e r , or the f o u r t h c om p o nent hook e d o nt o a s ha ft.

A d ef a u lt en gi ne con f ig u r a tio n ha s be en i nc lu d ed in W A T E -S .

F i g u re 2 0 illus trat es this en gl ne _ a tw o - s p oo l t urb o fan w i th ax i a l single -sta ge f an, ax i - c entr l f ug a l HP c om p re s sor (t hr ee- s t a ge ax lal ) , a x ia l s i ng l e-sta g e HP t u r bi ne, and a x ia l t w o - s ta g e LPT.

The d e f a ul t $C na m el l st da t a corr e spo n di n g t o t h i s en gi ne co n fig - uratio n a re sh o wn i n Ta bl e V.

5 8 O R IGINAL I: _ A , ( / E iS OF POOR Q U ALITY ORIGIPlALP A GE t _ TABL _ V. DEFAULT $ C VALU B B OF POOR QU A LITY N COMP - 17, NOSTAT - 19 Comp o nen t JC O NF N u mber JTYPE 1 2 3 4 1 I I 0 6 2 2 4 2 0 3 0 3 2 3 0 4 0 4 9 4 0 5 0 5 4 6 0 7 0 6 2 7 0 8 0 7 4 8 0 9 1 0 8 2 9 0 1 1 0 9 4 11 0 1 2 1 3 1 0 2 1 2 0 1 4 0 11 5 1 4 1 3 1 5 0 1 2 2 15 0 1 6 0 1 3 5 1 6 10 1 7 0 1 4 2 1 7 0 1 8 0 1 5 9 1 8 0 1 9 0 1 6 II 5 13 0 0 1 7 II 7 9 11 0 t 4.1.2 The r mo dy nami c Input T he t h e rm od y n amic i npu t is con tai ned i n t h e $T na me l _ ,at . Z t l e p re c e d e d by a t i t l e car d d escr ibi ng the en gi ne b e i n g weig he d o r a n y oth er des c r i p t i on t he u s er mig ht d es i re. T he the rmo dyn amic i nput f u ZZy des c ri b e t he p r ope r t i es fo r ea c h gl ow st ati on i den ti -

Ei ed in t he c onf i gu rati on in pu t. These p r op e r t i e s i no l ude m a s_

gl o w r a t e , t o t al p r e ssur e , t o t a l te m pe r a tur e , and fuel / ai r r a ti o.

These i npu t s a r e u s e d as co mp o n en t u pstr ea m gl o w cond iti ons.

"WTF" i s a one-dimens l onal a rr ay c o ntai n ing t he physical m ass f lo w r ate a t each st at io n (i bm / s ).

" T O P R E S" is a o ne-dlmenslonal a r ra y c o nt a i n i n g the t ot a l p r es s u r e a t each s tati on (p si ).

" T O T E MP " i s a o n e - dlm en slo nal a rr a y co nta i n i n g t he t o tal t e m p e rat u re at each s tat io n ( ° R}.

"FAR " is a o ne- dim e nslon a l a r ra y co nt ainin g th e f u el a i r rat io at each stati o n.

I n a ddi t io n t o th e abo ve, _hr e e a d d itio na l arrays o f d a t a are requ i re d . These a rr ay s we r e originally f il le d b y the NN E P c od e I n 1 J WATE -2, however, s i n c e WAT E -S is no t co n fi g u r e d with a n e n g ine !

cycle code, sep a r ate input variables we r e nee ded. !

"P E RPF " i s a o ne-dimenslonal a rr a y c on t ai n in9 t we l v e val u es which de sc r i be g eneral performan c e para m - ' ete rs fo r t he engine.

Location Description 1 I n l et t o ta l f lo w ( l b m / s ) 2 g r oss thrust (Ibf) 3 rue 1 f l ow ( I b m / h r ) 4 net thr us t 5 TSFC 6 1 J

0 0 0 0 0 0 01 - TSE09

6 n et th r ust / inl et tota l f l o w 7 t o ta l i nl et d ra g 8 t o tal b ra k e shaft p o w er (hp ) 9 inst alled thrust 10 installed T S F C l l s p i ll ag e a nd l ip drag 12 boa,, a ll dr ag Th is da t a is used for i nfor m a ti on p ur po se s only, and hence, i s con si de r e d op t ional i n WA TE -S.

" DATINP " is a t wo-d im en si onal array c on t aining severa l mis- cellaneous c o m ponent pr ope rt ies. I t is of t he f o rm DA T INP(N tM ) whe r e M is t he component nu m b er, and N i s t he v ari ab l e number a s de sc ribed i n Table VI.

Th e only r eq uir ed in p u ts in t his ar ray ar e t he s haf t gea r r a t ios. Th e remainder of t he inputs a r e opt i onal. The bleed f r a c t i on s will be cal cu la t e d f ro m t he "WTF" arra y in put and t he M a t h number an d al titu de are fo r i nfo rm at i on p ur po s es only.

"DATOUT" is a two -d lm ens lo nal array c on t a i n i ng several o th er ml s c e ll an eo u s c o mp o nent pr op er ties . I t is o f th e f o r m DAT O UT(N , M) where M i s th e c o mp o nent n u m be r , an d N i s the variabl e n u mb e r a s described i n Table VII. The requ ir e d inputs i n this array i n c l ud e t h e t u rbine r p m , i f the t u rbine i s n o t c o n- ne c ted to a c o m pre sso r ( f ree-t u r b ine turb o pr o p an d turbo sh a ft engines) , s pli t te r bypass r a t io , and mixer pri m ary an d s e c on d a ry fl o w areas. The r e m ain d er of th e array i s c al c ulate d fr o m the "WTF" , "T O PRES", TOT E MP" , en d "FAR" arrays, i f n o t i nput.

OF p OO R QUA L I ' I '¥ 4 4

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i 4 . 1 .3 Ae romechanical Input T he aeromec h a n lca l i np ut is c on tai n ed i n the $W naaelist .

These v aria ble s con t rol t h e a e r o dy n amic a n d m echan ica l si z i ng o f th e c o m po n e nts . T h e f ollo wing sectio n s desc ri be t he n ero - m ec ha n ica l in p ut a n d gi ve th e d e fa u lt val u e s w h er e a p p li cab le.

4 .1.3.1 Miscellaneous Variables "A CCARM " i s a var i a b le t ha t con t a i ns t he val u e o f t h e cen- t r oi d dis t a n c e f o r the a cc es so r i es co mp o nent i n the CG ca l c u la- t io n s . If n o val u e is inp u t , acces so r i es are not i n c lu d ed in c ent er -of- gra v ity calc u l ation s.

" DIS K WI " is a var i a b le that i s u sed a s an i nd ic at or fo r th e axial comp re ssor disk we i ght m eth od. (Default - i . ) 0 - D o d i s k w e i g ht calc u lat io n s u s in g th e B o e ing WA TE-2 m eth o d.

1 - D o d i s k we ight c a lculat io n s u s in g the G a rrett WATE-S met ho d.

" A CCS" i s a o ne-d i m e ns lo nal a rr ay co n t a i n i n g t h ree val u es wh ic h c o nt ro l t h e acces so ry w ei g h t c a l c ula t io n s . (Defa u lt - 4 0 ., 0.0 2 , 0.i0) ACCS (1 ) _ F i xed ac c esso ry we i g h t ( i bm ) A CCS(2) = A ccess or y w eight fra c ti o n o f b are eng i n e w eigh t A CCS(3) - M i n _ , um to t a l a cc es sory we i g ht fra c tio n 6 5 " 1 8 CA LE" is a o n e -d imensio n a l i n teger arra y c ontai n i n g thr _e values whioh control t h e eng in e scali n g logio o f t h e p rogram , (D e fault = 1 , 3, 1 ) I, ISC ALE(1 ) O utput indicat or f o r scale d en gi ne s, Un s ea l ed en g in e o ut p ut ae t by "ZOUTC D ".

0 - Sh or t form eng i ne w ei gh t , length, a n d m ax im u m ra di u s .

1 - Lon g f orm c o mp on e n t w e i gh t s and d ime n si on s .

2 - Deb ug op ti on .

ISC AL_( 2 ) Number of s ca li ng point s .

ISCALE(3) No t us e d .

" SCAL E" is a o n e -d i m e ns io nal array c o ntaining 81 x values.

The va l u es c or r e sp o n d t o the en gi ne s c a li n g fact o rs des ir ed. T h e n um be _ of "SCALE" val u es must be eq u al to t h e val u e of ISCALE(2).

Fi rs t value must always equal i. (D ef au l t = i, 0.8, 1 .2, 3*0.)

"ZHT" i s a i n teg e r va ri a ble t o co ntr ol the e xec u ti o n of the c o m p o nent we ight c a l c ul a tion s. (Defau l t = I ) 0 - Do no t dO weig h t ca l c u lat i on s .

1 - D o we i g ht c a lculat io n s w ithou t th e t her m o dy n ami c par amete r m a ximi z ati on f e a t u re o f th e W A TE-S c o d e .

T hi s is u sed for desi gn poin t p a ra mt er l c we ig ht ana lys i s.

2 D o we i g h t ca l cul at io n s u s i n g ma x imum t hermodynamic [ , p a r a mete r maximi zat io n f eat uc e.

_ J 3 - Do w eight calcul a tion wlth airflo w sa_ling w ithout th e therm ody nami c param e te r maximization f e ature.

!--- .

4 - Do weight Qa lc u l atlo n with airf l ow sc al ing usin g the th e rmod y nami c p ar ameter ma x imization f eatur e .

"I PLT " is a loglaa l v a riabl e to c o nt r o l the gas p ath pri n te r plo t op tio n o f W A TE - S . (De f a u l t - T) T - G a S pa th lay out F - N o gas pa th l a y out " ISZ I" is a l ogic al v a r i a b l e to sp e c if y the uni ts of the $W na melist va ri a bl e s. ( Defa u l t - F) T - S l u n i ts i nput F - E n gl i s h u ni ts i np u t "ISIO" i s s lo g lc a l v a r lable t o sp e c i f y t he u ni ts o f t he o u t p u t of t h e w eig h t ca l cu l at lo ns. (D ef au l t = F ) T - S I un i ts ou tput F - E n gli sh u n i ts " IOUTCD" is an in te ge r v ar iab l e t o c o nt ro l t he am ou nt of o u tp u t gen er a ted by t h e componen t a n d en g ine w e i g h t ca l c u l a tio n s.

(D ef a ul t • 2) 0 Sh o rt f o rm e n gi ne we ig ht , len g th , an d ma xim u m r a diu s , i 1 - L o ng fo_1 . , c o mp o ne nt we ight s an d d i mens ion s.

2 - Deb ug o pt ion.

4. 1 ,3.2 _ength Contributing Ve ctor "Z L_ NG" is a one-d im en si on al in t e o e r array spe c if y i n g on ly t hose c o m ponen t s wh i ch c on t r i b ut e t o t h e tot al a dd iti ve e ng i ne l e n gt h. T h e c o mp onen t nu m be rs ar e s p ec i f i ed i n t he o rd er t h at t h e co mp onen ts w ould a d d i n l e ngth t o a c h i eve t he t o t a l en g ine leng t h.

This m u st start w ith th e i nle t a n d e nd wit h t he f u rth e st d o w n- str e am n oz =l e. Th e d e f a ult "IL EN G" values f o r th e d e fa u lt engine c on fig u rat i o n i ll u s t r a ted in F i gu r e 2 0 ar e : I LE N G = i , 5, 6 , 7 , 8, 9, l l, 12 , 1 3 , 14 _ 1 5 p T h e d e fa u l t " ILE N G" i np u t do es no t in clud e t h e byp a s s f lo w c o m p o - nents (COMP 2 , DUCT 3, NOZ 4), re v ers e-f lo w b u rner ( DUCT 1 0), o r shafts (SHFT 1 6, SH F T 1 7) s i nce th e se c o m p o nents d o n ot c o nt ri b u t e t o th e t o ta l e n gi n e l en g th.

4. 1 .3.3 Mechanical Design Indicators _ IW M EC" is a tw o - dime n sio nal i n t e g e r arr ay co n t a i n i n g the m ec ha n i c al d e sign i n d i c ators. I t is of th e form I W _ 4 E C (N , M), wh e r e M i s the c om p on e n t n u m be r, and N is t he va ri able numbe r as d e scri bed i n t h e foll o w i ng se c ti o ns fo r ea ch com p o nent type. The m ech a n i cal d e s i gn in d icat ors must b e s pe cifi e d f o r each co m p o nent.

Table VIII i l l ustr a te s the d efault "IWMEC" value s , which are r epr e sentat i ve o f the d e fa u l t engine (see F ig u r e 2 0 ).

i i t t ,, 6 8 TABLB VIII. IWMEC DE L '_AUI,T VAI_UI_IB ( S ee l.'Igur e 2 0).

Co mp on e n t _o g Bt_o r W um bar i 2 3 4 5 6 I 'INLTt 0 0 0 0 0 0 2 'F O r 1 0 0 5 0 1 3 ' DUCT ' 2 0 0 0 0 0 4 t NO _l i 0 0 0 0 0 5 'F I' 1 0 1 2 0 1 6 ' DUCT' 2 0 0 0 0 0 7 ' LPC ° 1 0 0 0 0 3 8 'DUC _' 2 0 0 0 0 0 9 'HPC W 2 0 0 0 0 1 10 ° PBUR ' 1 0 0 0 0 0 II 'HPT ' 0 9 9 1 0 0 1 2 ' DUCT ' 2 0 0 0 0 0 13 'LPT ' 5 5 0 2 0 0 1 4 'DUCT' 2 0 0 0 0 0 15 'N OZ ' 1 0 0 0 0 0 1 6 ' SHAF ' 1 0 0 0 0 0 1 7 ' SHA F ' 2 0 0 0 0 0 OR IG I NA L PA_ E _ %

O F POORQ U A LIT y

6 9 4 . 1 . 3 . 3 . 1 C ompressors L oc ____iol___ D es c ription 1 Ty pe o f c o m pr ess or be i n g w ei g hed ( 1) 'F AN ' - T_pi o a l fan (2) 'PO' - Ou te r port ion of nonrot at l ng s p J . i t- te c fa n (3) 'FI' - Inner porti o n o f nonrot a t i n g split- ter fan (4) 'RSFO' - O uter p o rtion o f r o tat i n g s plitter fan (5) ' R SFI t - I n n e r p o rt i o n o f ro t a t i ng sp litt er fan (6) 'LPC ' - Low-pre ss ure c o m press o r ( 7) ' HPC ' - H igh -press u re c o m pres so r 2 T h is i nd i cates if the c o m press o r has s tat o r s o r i f th e compre s s o r is a centrifu g al c omp res so r.

0 - Stat o r weight is n o t calcu l ated 1 - Stat o r weight i s ca l culated 2 - Centr i fu ga l c o mpress o r 3 T hi s i s t h e i nd i cat o r for 'fr o nt' fra m es i n c o m- press o rs . This input m ay be : 0 N o fr a m e 1 - S i n g le be a r i n g frame wi th o ut P o wer Ta k e o ff (PTO) 2 - S i n g le b earin g frame with PTO 4 - Tw o bearing frame , s uc h as t h e frame i n fr o nt o f t h e HP C i n t h e JTSD _ r JTgD , wh i ch e x tend s o utwa r d t o the f a n o u ter cas e an d h o lds t w o be a r i ngs with PTO 7 0 Lo ca tion _io n 4 T his is t he i n d icator fo r the 'rear' frame in a c om p ressor 0 - No f r ame 1 - Si n gl e bear i ng f r am e wi t hou t P owe r Ta keo ff ( PT O) 2 - Si n gle be ari n g fra me w i t h PTO 4 - Tw o be aring f ra m e, such a s th e f r a m e i n fro nt of the HPC i n t he JT8D or JTgD, w hi ch e x ten d s ou twar d t o the fan o u ter case a nd h ol d s tw o b ea ri ngs w i th PTO 5 This is the c o mp o ne n t n um b e r c o n ne cti n g t o this c om p on ent f or sp l lt f lo w c om p re ss o r s o n l y. I f t h is i s t he Fa n O u te r , t he F an I nn e r m us t b e speci f i ed. I f t h is i s t h e R o tating S plitte r O u te r , the Inn er Splitter m ust b e s pecif i ed , an d v i ce ver s a . If ( - ), a du mm y com p r e sso r is as su med.

6 Gear bo x ind icat o r . I n p u t i s c om p onen t numb er of s h a f t , 0 f or n o gea r b ox .

7 Num b er o f st age s ! if 0 , will ca l c u late n umbe r o f stage s ass u m i ng equ al w o r k b ase d on th e ma x im u m fl rst-sta g e p r ess u r e rat io i np u t [ DESVAL(2, M )].

4. 1 .3.3.2 Turbines Location Description 1 This i s the type o f t u rb i n e (8 ) I HPT ' - H i g h- pr e s sure t urbin e (9) ' LPT ' - L o w - pr ess ur e t u r bi ne 2 I n d i cat o r f o r t urbine exi t fr a me 0 - N o frame 3 - S ing l e bearing turbine exit frame for large engin e s 5 - - S ma ll t urbine exi t frame 7 1 Location Description 3 Com p ress o r nu mb e _ f ro m wh i ch t he rp m is det er - m i ned ; i f 0 , D ATOUT(2 , M ) i s u sed f or t u rbi ne t pm t_ (ax i a l tu rb i nes only ), 4 Co mp on ent nu m b e_ f r o m wh ic h t h e mean radius li m it f or t h e t ur bi ne i s d e te r mine d. If the co m po ne n t n um be r i s p o siti ve , th e ou t l et o u ter d im en si on is used. I f nega ti ve , t he i n l e t ou t er d i mens i on is used . If O , it w ill u se t he ou tl e t o f t he feed i n g c o mp o nent.

5 N umb e r o f s ta g e s; if 0 , will cal c ulate n um ber o f st age s ass u ming eq u al w ork b ased o n t u r bi ne mean r ad iu s limit an d mean w o rk c o efficient.

6 Indi c a t or f or axial o r ra d i a l t u r b ine 0 - Ax l a l t u r b ine 2 - Rad i al turb i n e 7 N o t used.

4.1. 3 . 3 . 3 Burn er s Location Description 1 Th is is the type o f b urne r b ein g we ig he d ( i0 ) ' P BU R ' - Pr i m ary bu rne r ( ii ) 'D BU R' - D U Ct b u r ner (a mean ra d ius is spec i - fie d ) ( 1 2) 'A U G' - A u gm ent o r (n o inner w all } 2 Th is i s the i n di c a t o r f o r frame wei g ht , n or m a lly only for p r ima ry b u r ners . T h is fra m e i n clud e s a be ar in g .

0 - N o fr a me 1 - F r a me 3- 7 No t us ed .

7 2 4.1.3.3.4 DU O t_____ _ LO C_t!on 9escrIptlo, 1 (20) I D U CT' 2 I n d i c at or a_ t o t y p e o f d u u t 1 - Du mmy - i .e., n o we ig h t o r le n gt h 2 - L e ng t h i n put 3 - Len gt h d e r i ve d a s in a d u c t u onn e c t - in g a s plitter an d a mixer 4 - Cr o s so v e r duct f o r centrif u gal com - p r es sor s 3-7 N o t u sed.

4.1 .3.3.5 Shaft_____._sss Location DescrIptlon 1 ( 1 3) I SHAF' 2 Shaft number from inner to o uter.

3-7 N o t used.

4 . 1 . 3 . 3 .6 M i xers Lo ca tion Des c ription 1 Type o f mixer (14) ' MIX ' - The coannula r emergence o f tw o s t r eams w i th ou t m ec h an ic al m ixe r (15) 'FMIX' - Forced m ixer, mechanical, i.e., Dais y I lo bed mi xer !

2 Z nd l cat o r f or primary input n o de 0 E ngine c o re i s inner (pri m ary) 1 Engine c or e is o ute r (se co nda r y) 3-7 N o t used.

4 . 1 . 3.3 . 7 No zzl e __ _ s Louation Desorlption l (16) I N OZ I 2 N ozz l e typ e 1 - C onverge n t 2 - C -D va ri a ble a re a 3 Co mp o n e nt nu m ber f ro m w h i c h t h e n ozz l e inle t di a m- e te r c an be de t e rmi ne d . If t h i s di a m e t e r is taken f rom t h e I n l et o f th e compo n e n t , a (-) com p o nen t n u mber mu s t be en t e r ed. If (+), th e e xit s tati o n w ill be u sed. I f the previ o u s com p o nent d eter- mines the diameter, this loc at io n m ay b e ze ro .

4 Th r u s t r ev e rs e r type 0 - Non e !

1 - Pan 2 - Pr im a r y 5-7 N o t used.

4. 1 .3.3.8 Heat Exchangers Location Des crip tion 1 ( 1 9) _H T E X I 2 Heat ex ch an g e r type 1 - F i x e d t u b e 2 - R o tary 3 Fl ow Di r e c ti o n 1 - Pa rall el f lo w 2 - C o unt e r fl o w 4-7 H o t used.

4.1 .3 . 3 . 9 Splitte _ Loaa_ion DescriPtlo_ 1 ( 1 7) I SPLT ' 2 0 - Inn e r st re am is pri ma r y 1 Inn e r stre a m is n o t primary 3-7 N ot u se d.

4. 1 .3.3.1 0 Annulus Invertin_ V , l ve L o c a._..__ _ t _o nn Description 1 (18) 'VALV' 2 L o_ at lo n o f Valve 1 - Inner 2 - O u ter 3 C o mp o nent nu mb e r of o pp o s i te d uct 4 0 i f fixed , 1 i f m ova bl e 5-7 N ot u sed.

4. 1 .3.3.1 1 Pro pellers and Propfans Location 1 (2 1 ) I PROP ' 2 Pr o p e ller t ype 0 - Ham i lt o n St a ndar d d o u b le acting, ,_ a d van ced t ec hn olo gy a lu m inu m p ro pel- l er .

i - H a mil t on Standard d o u ble act i n g , advanc e d tec h no lo g y c om p o s i te pr o pe l - l e r.

2 - Ha mi lt o n Stan da rd pr opf a n .

3-7 Not u sed .

?5 !

4. 1 . 3 .4 _eromechanlcal Design Variables " D E BVAL " is a two-d lme n sl ona l a rr a y c o n t ai n i n g t h e a er o- dyna m ic a nd m e c han i c al d es i gn i np u t s . Z t is o f t he f o rm D E SVAL(N , M) , where M is t h e compon e nt n u mb e r, an d N is t he varl- ' 1 q able nu m ber as des c r i b e d i n t h e foll o w i n g se c tion s fo r e ach co m -

I

p o nent type. The de fa u l t val u e s a re s tored i n a s eparat e arr a y (D E FAUL) wh ic h cann o t be a lt e r e d by p rogr a m WATE-S i np u t. A s u m- m ar y o f the s e array s is con t a i ned i n Table IX. The defa u lt val u es o f t he " D E FAUL" array a r e i l lus trate d i n Table X. The " DEFA U L " array value s are used when t he "DESVAL " inp u t is n o t sp eci f i e d fo r a g i v e n c o mp o nent. Table XI c o n t a i n s typ l ca l ranges o f t h e "D E SVAL" i np u t var ia bles f o r eac h com p o nen t type.

7 6 ORIGINAL P A GI" . _ . _ i OF pO O R QUALI ' l r Y _ _

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W . . p._ , _ _ _ , , ' . _ , ._ I ' , , ' OF po01_ lqU / ',Li 'i Y ?9 k_ 4 . 1 .3 . 4 .1 Com p_ps so+ t Lo catio__ n Description 1 Co m pres s o r i nle t M a th num b e r.

2 Ha x im u m _ i rst-stag e p re ssur e r at i o , r equ ir ed i f I WME C (7 , M ) e q u al s 0 .

3 Com p r e sso c inlet hub / tlp rati o .

4 A x ia ls B l a de t i p solidi ty, ratio o f bl ad e t ip ch or d a n d bl a d e spaci n g.

Cen tr i - N u m ber o f b la des . If (-), s plitt er wei g h t is £uga lz c a lc u l a t e d .

5* Bla d e a s pect r a ti o o f f irst q ta g e.

6* B l ade aspect rati o o f last stag e.

7 C o mpressor exit Ma t h nu m ber.

8 Maximu m c o mpress o r inlet te m perat u re. ZER O i f d es ig n p o int temperature is to b e u s e d for material s ele c ti o n. ° R ( ° K) 9 Maxim u m c o mpressor o utlet temperature. Z E R O i f d esi re d p o int temperature is t o b e us e d f o r i m at e r i al selecti on. ° R (° K )

i

i 0 Ma x i m um spee d rat io - RPM m ax / RPM d e s.

1 1" _l a d e ma te r ia l d e ns i ty. _ Z E R O i_ WATE-S i s t o se l e c t m ate rl a l , i b m / in _ ( Kg / cm _ ) 1 2 A x i al : C o m press o r d e sign type i. C o nstant h u b ra d i us design.

2. C o nstant mean r a d i u s de sig n.

3. C o n s t a nt tip r adius d e s i g n.

Cent r i- £ ug al : HU bl nlet / t l Pexl t r a di u s ratio.

*N o t us e d f or c en t ri f ug a l c o m pr e ss o rs.

J L oo . _a_i o. . _ ._ n .Description 1 3 RP M sca l a r, n ormal in p ut is I . - u se t o ma t ch known rp m or modify t i p spe e d o or r e latl ons.

14' T em p e r a t u r e a t w hic h a change o f m nt erl al is re qu i r ed . ° a ( °E ) 15 Co mp r esso r w e ig h t sc s la r, in p u t ZE R O i£ n o sc a li ng i s d es i red .

1 6 " Blade taper _ ati o .

17" Bl ade v ol u m e fac t or .

_o-_ / -_ c e n t r i fu ga l c omp ress o rs.

8 1 4. l , 3 • 4.2 Tur b._._ __I n e . _ .

1 T u rb i n e i n let M a ah n um b e r.

2 Axial " Fi r s t-etage mean wo rk coeffi c i en t - k m = _ ,.

U m ! Ra d ial: Ra d ial t u r b i ne wor k co e f ficie n t - A t = __ J _ H_ / N [ U t 3 . Axial: Bl a de tip solidity , bl a de tip ch or d / bl a d e _ spac i ng.

Ra d ia l: N umb e r o f bl a de s. If (-), spli tt e r weight i s i calc u l at e d.

4 * B lade aspect r at io of f ir s t s ta ge .

5* Bla de as pect r a tio of last stage .

6 T u r bi ne e xit M ac h n u mb er .

7 Disk r e fere n ce _t res s - 0. 2-pe rc e n t y i el d, i b f / in 2 ( N e w t o n / c m 2) .

8* T u r bin e d e s i g n type I . C ons t ant ti p r adi us d es ign.

2. Cons t ant mean ra dius de s ign.

3 . C onstant hub ra dius d es ign, i 9 Ma xi m u m s pe e d rati o - RPM max / R P Md e sig n.

i 0 ' Tu rbi ne contro l radi us , i nc h (c m ) - b lan k i f tr ans f e r r e d f r om a c om p o ne nt. T hi s o v e rri des I_ EC in p u t if n o nzer o .

TN-_-_ ra dial tu r bines.

L o c ation Description i i D e n eit_ o£ materia l in tur b i n e bl ades , ib m / i n 3 (Eg / om ) .

12' Blade vo l um e fac to r .

1 3-14 N ot us ed .

15 T ur bin e we ig ht s ca la r. I np u t ZERO, i f no s c a l - i n g i s des i red.

1 6 ' Turb i ne bl ade taper ra tio .

1 7' Stat or bl ade v olum e fact o r.

* Not used f or _a d i_l t u r bi nes.

4.1.3.4.3 Bu r ne rs L_ o _cati o _______n Desc ri ption 1 Bur n er th roug h-f lo w ve lo c i ty, ft / s ( m / s ).

2 B u rner airfl o w re si dency time , s.

3 Burner mean di a m eter, inc h (¢ m ) . If zer o , diameter i s calc u lated t o mat ch a c on nec ting co mp o nent (see belo w).

4 C om p o nent num b er f o r calculating b ur n er refere n c e di a m eter, if o ther tha n u ps t r e a m co mp o ne n t. N o t u sed _y hen d i ameter i s s pe c if i e d. If g re at er t h an zer o , co_ ne c tin g com p on ent me a n diameter i s u s ed f o e b urner mea n d i a m ete r . If le s s than ze r o, conn e c t i n g c o m- p o nent o uter d iameter is u sed f o r b urner i n n er di a m - eter (rever s e-fl o w b u r n er s ).

5 Nu mb e r o f c a n s for c an b ur n ers .

5- 1 4 No t used.

15 B u r n er w eigh t sc alar. E nte r ZERO , if no sc a ling i_ des i red.

1 6- 1 7 N o t used.

8 3 r 4. 1 . 3 , 4 . 4 D u o t. _s L oc at io n De sori pt io q n 1 D u c t inle t M aoh n umbe r.

2 L e ngt h to h e ight r a t i o o f d u u t , re q u i r ed i f IW M E C( 2 , M ) e q u al s 2.

3 D u c t me a n d ia m e t er , In ch ( cm ) . If 0, d u ct d i a me t e r is c al c ula t e d t o matc h a conne cti ng component.

4 Co mp on ent n u m b er f o r cal cu latin g m e an duc t diam ete r.

Not used when mean duc t di a m ete r is s p e c ifi e d .

Enter - i , if upet r ea m c o nnecti n g c o mp on ent is t o be u se d .

5-14 Not us ed .

15 W e l g h _ s cala r . ZE R O, i f no s caling i s de s i red .

1 6 -17 No t u sed .

4.1.3.4.5 Shafts L o cati oT ___.__ / _ Descrlption 1 S h aft a llo wab l e st r e ss , lb f / in 2 (New ton / c m 2).

2 Shaft ma t er ia l d en s ity, I b m / in 3 ( Kg / c m 3).

3 D iam et er rat io o f shaf t , D inn er / D ou t s r , n o t u s e d f o r o u te r s h aft s .

4-14 N ot u se d.

15 Shaft we i g ht scala r . Z E RO if n o sc a l in g d e si red.

16-17 Not u se d .

8 4 4.1.3 . 4.6 Mi xer.._.._ _ s _ o a a ti o n Description r_ 1 E ffec tiv e _ n gth - t o-d i a meter ratio o f m echa ni ca l mi xe r , L / _ A / _ , w he r e L is t he m i x e r len gt h inle t t o e x i t, h is th e t o t a l fl o w area. E nt er 0, i f not a m e c h a n ic al (f orc e d ) m i x e r.

2 Nu m ber of passages (or lobes) i n mi x er.

3 -14 N ot used.

15 Wei g ht sc ala r . E nt er Z E RO, i f n o sc al ing d e sir e d.

1 6- 1 7 N ot used .

4. 1 .3.4.7 Noz zle_______% s s Lo g atlon Description 1 Le n g th t o diam eter r atio o f n o z zl e.

2 Bypa s s rati o f o r m i x e d f lo w n oz z l e f o r t h r u s t reverser we i g ht .

3-14 No t u s ed.

15 W e i g h t s c ala r . Ze ro , i f no sc al i n g d e si re d .

16-17 N ot used.

4.1.3.4.8 Heat Exchangers Location Descriptlon 1 N um ber o f t u bes i f "F i xe d" type.

2 Ma c h n umb e r i n primary stream ( cold s i d e).

3 Ma t h n umb e r i n se c o ndary s tr ea m (h ot si d e).

4 E n g i n e bypass r a t io i f " R o t a r y " type.

5 E / D f or p r im a r y stream if " Fixe d " type.

6 E / D f or s econ d a ry st r ea m if "F i xed " t ype.

7-14 Not used.

15 We i ght s c a lar . Zer o i f no sc alin g d e si re d .

16-17 N ot u se d .

4 . 1 . 3 . 4 .9 er_ s

i Onl y input if firs t calcu l ate d c o m p on e nt in flow path. In l et M aoh numbe r .

2 I nlet hu b / tip ra d ius ratio.

3 -14 N o t used.

15 W ei g h t sc alar . Z E RO , if no sc al i n g d e s i re d .

16- 1 7 N o t u s ed .

4.1 . 3.4.1 0 A nnu l u s Inverting Valve Location D e scri ptio n 1 Sp ec ific l e ng t h -. r ati o o f l e ng th t o e f fec ti ve di a m - eter o f th e AIV , 5 / 4Av / 4- _ - _ - _ 2 Numb e r of pas s a g es.

3 Mach n umb er o f in ne r pa ssag e.

4 Mac h n um be r o f o ut er passage.

w hi c h h u b ra diu s is t aken; o r b la nk , i f f e eding co m - 5 H ub r a dius i n i nc he s (cm ) ; o r c o mpo nent numb er f ro m p onent determin es the hub r a dius.

6 Inne r c y l inder we i g h t - i b / f t 2 , ( K g / m 2) .

7 O uter c y l inder w ei g ht - i b / ft 2 , ( Kg / m 2 ) .

8 Wa ll w ei g h t l b / f t 2, ( Kg / m 2).

9 - 14 Not u sed, 15 Weigh t scala r. ZERO , i f no scal ing desired.

16-17 Not u s ed.

8 6

k_ _ _.............................................. _ a

Lo c ati o n D eec rI p tlo n n

_ - 1 De si g n c ru ise M a oh nu mb e r of aircr aft .

2 Nu m be r o f blade s .

3 Activ i ty fa c t or .

4 T i p sp eed - ft / s (m / s ).

5 R a tio o f pr o p _ lle r s h aft p o we r to di a met e r sq u a r e d - hp / ft 2 , ( K W / m ') .

6 - 1 4 Not u s ed .

1 5 W eigh t s ca l ar . Z e r o , i f no sca l i n g d es i red.

1 6 -1 7 Not u s e d .

4 .1. 3 .5 Desig n Limits " DESLIM" i s a o ne-dimensl o nal a r ray c o ntain i ng t he d es ig n l imit s f or WAT E -S. Tab le XII desc ri bes t h e des i gn l imi ts a n d t h e def au lt values c u r r e nt l y in t he c o de . T h e s e c a n be cha n g ed as de s i red t hro ug h th e n a me l i st SW in p ut. I f t he se l imit s a re e x cee ded , t he c om p on e n t we ig ht and dimen s io n calc u lat ion s c o nt i n u e a nd a w arni ng m e ss a ge is p ri nt e d o u t.

4 . 2 Pr o_ / a m Output The o u t p u t of W AT E-S i s con t a in e d i n t h r ee sec ti ons, c oi n c i d - ing w ith th e in p u t : c o n f igur a tio n , therm odyna mi c , and a erome c h a ni - ca l . T he c o n figuration out p ut contai ns the $ C na me l ist in p uts a nd i a sim p le confi g uration lay o u t. T he the r mody na mic o u t put c ont a i ns i th e $T nameli s t inpu ts .

T he ac rom ec h an ic al o u tput ma y b e s el ect e d i n e ith e r En g l ish o r S I unit s. Th e un it s u sed a r e prese nted i n T a bl e XIII . T h e typ e OF POO R QUALII _ t' I • e l , _ , _ or 4 m,] I e | 8 8 TABLE XII I . OUTPUT U NI T S .

V A R I ABL E S I UNITS EN GL IS H UNITS i Ll V e l oa It y m / s f t / e T em p e r at u r e ° K °R Press u re N / m 2 ibf / ft 2 A r ea m 2 ft 2 Stre ss N / c m 2 Ibf / In 2 Density E g /¢ m 3 i b m / in 3 W e i g ht K g ib m L e n g th cm i n E n t halpy J o u le / K g Bt u/ Ibm P o wer K Watt hp Wei g ht f lo w K g / s l bm / s W ei g h t fl o w / unl t a r ea l( g / m 2 s l bm / ft 2 s R a d iu s cm i n o f u z_it s i n u se are no ted i n th e u n i ts sectio n of t h e se r o - mec ha n i cal ou tput . The l ev el o f out pu t i s c ont r o l le d by th e SW na m elist Integer variab le "XO UTCD " a n d has three out p u t optio ns .

E xa m p les of t hes e ou tput f o r mat s ar e sh o wn i n S ec ti o n 4.3, Sa m ple C as e s for tw o di ffer e nt e n g i n es.

A flo w p a t h pr in t er plo t i s als o ava i la b l e wh e n SW n a m e li st logi c al v a ri a ble "IPLT" is t ru e. This pl o t is a utom at l cal l y s c a led t o fi t on o ne page o f o utput. Ex a m p l e s o f t h is o pti o n are a lso co ntain e d i n Se c ti o n 4.3, Sampl e Ca s es.

4.3 Sample Cases Tw o s a mpl e cases a re in cl u d e d h ere i n to i ll u strate the exe c u t io n and o utp u t o f WAT E -S. Th e f i r s t is a s l n gl e- s p oo l tur bo pr o p an d t h e s ec o n d a l o w b ypa s s-ratl o mlxe d-f lo w tur bo fan.

4.3.1 Turbo prop E nqlne Fi gu r e 2 1 illu st r at es t he c o nfi gura ti o n s e lec te d for the s a m ple tur bo pr o p t es t c a se. T h e e n g i n e h a s s s i n gle sp o ol co n - sisting o f a tw o-s ta g e centrifugal com pres s o r an d thr e e - sta ge a xi al t ur b i ne . A r e ve rse- f l o w bu r uer a nd g ea r box ar e al s o in c lu d e d .

F i g u r e 22 i ll u st r a tes th e WATE-S i n p ut n e c essary t o e s tima t e th e w eig ht an d d ime ns io ns o f t h is en g i ne . Th e f ir s _ t i t l e ca rd _s f ollo w e d b y the c onfig u r a t io n inp u t cont a i n e d in t he $C n a m e llst .

Th i s en gin e ha s Ii c o mp o n e nts a n d Ii th er m o dyn amic f l o w sta tion s, th u s "N CO M P" an d " NOSTAT " a re s e t t o Ii , Th e com p o n e nt typ es a r e d efined b y t he " JTYP E" a rray an d th e compo nent conne ct ivi ty is sp ec ifie d b y t h e "JCO N F " a rray .

9 0 OH iG IN / _L Q U A LI ' I_ O F po 0_

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,I _4 O F pOOR QUAI . ITY 4 , 3 , 1 1 TU RB OPR OP ENG I NE S AM PLE CASE $ _ _ CON h lL w N Q S T AT m LI,JTY PEm l w Z _4s2 , _ * Z , S p z p g _ Io pL I p lO*O P J:ON¢lZ i l l. l t 2 _3 e 4 , _ e b p S e g e lo e 11 _3. 10*O , J _ QNF(I o Z |I b*OJT J 3tO pSD XO*O j JCOq _ (I w 3i -Z e 3 _4_* 6 _ 8 * g e lO P ll * O P T p lO*O p J C OMF(l ,4 )e 4 *O o ? , X b *O e 4,'3,1 TU e BOPR _P ENGINE SARPLE CASE S T W T F - _ ?,650 Z ,?, 2 6 s ,390 Z ,T,41 5Z_I *?, TZ L3, T _ P R E S s _ *I4,696*Sqo45 2p sq,155 p2_ , _ BO77J _ 48,?O _ 9 _ *14,696 _ T g TENP-)*S18,688e2*BZ6*B * 2*I1)S*zsg _ 2 _ 6 _ ,T _ ISST*$19 _ Z*lS4t*50 b _ _R tTtO _ , I O214 _ 3**O Z 05 _ P _ PF(31-SS8,1,4*O, _ lO00,, SfN*) S W I _ EC(l*3l-b e _ e l e S *O e l_ DSSV&L(L*5|' _ 30*S, _ , § Gl _ L S * _ ZeO* _o 208 p 2*O* _ I _ *O* _ *31B _ *g 6 9 _ DESV&L _ I _ 6)' _ O***OZ2 _ tS* _ _ ESV _ L(I _ ?I mo lgb _ IeSZ3 _ I*O _ Ze2 p 2*Z* , ZS _ I _ SOOOe _ 3* _ |* _ OSSV _ LII _ IOt'*S*4, _ I:O, _ bOO* _ le,* Figure 2 2. WA_! E - S T urbo p ro p S a m pl e C ase In p ut.

F o l l ow i n g t he se cond tit l e c ar d, t he t h erm od y n ami c in put i s specifie d in the S T n ame l l s t . T he m a s s fl o w rat e , t o tal p ress ur e an d temperat u re , a nd fue l / elf rati o are _e£1ne d f o r ea c h f low station. No te that the fl o w st a tions r e p r ese n t u p stream com p one nt co nd iti on s . T he fuel flow a n d b rake sh a f t ho rse pow er a r e e n tere d i n the " PE R PF " ar r a y b u t thls d at a is f or i n fo r m a tive pur po ses only and i s no t u se d by th e W A T E -S c ode .

Th e a er o mec han lc a l inpu t Is n e x t , c on t ain e d i n t he $W na me- li st. D e fa u lt val u es er e u sed for al l but th e "IL E HG " , "IWMEC " , an d " DESVAL " a r ra ys . Ba si cally, the default value s s et both t h e i n put a nd outp u t uni t s t o En gli sh , tu r n on th e weight es t i mat io n co d e a nd p r int e r plot opt i on , a n d p ro v i d e a comple te d e bug print - o u t . T he l e ngt h co nt r i bu t i ng ve c t or "I L E NG " do e s n o t c o n t a i n DUCT 6, PROP i 0 , a nd S H FT 1 1 s i n ce t h ese co m po n ents d o n o t con t rib ute t o th e t o tal engi n e l e ng t h.

T he " IWMEC " valu e s foll o w t he "IL E NG " ar r ay . The i nlet , c o m - p o nent i , i s n o t ente r e d since inlet c alc u lati o ns are n o t per- fo rme d i n W A T E- S. Co mp onen t s 3 and 5 a re specif i ed as one - stage c en trifu gal compress o r s w i t h a f r on t f r a m e a ss o c iated w it h c om- pr e ss o r 3. C om p o nent 4 i s a c r ossove r d u c t, I WM E C(2,4 ) =4 an d c om - p o nent 6 is a bur ne r. T he HP tu r bine , c ompon e nt 7 , d e r i ves i t s rpm from c om p r es s o r 5, IW M EC(3 , 7) = 5 1 an d i s a t h r e e - s ta g e ax i al t u rbine, IWMEC(5 , 7) = 3 an d IWM E C(6,7) - 0 . T h e pro p ell e r type is a H a mi lt o n St a ndar d double a cti n g , advanced t e c hnology al u minum pro p e lle r , IWM E C(2 , 10 ) • 0 .

T he " D E SV A L " va lu e s f o ll o w the " IWMEC " i nputs. "DEF A UL " v al- ues a re u sed f o r a ll but the co m press o rs , b ur ner , t u r bine , an d p rop e ller . Co m p r e s sor 3 ha s an inlet Ma th nu m be r o f 0.49 , i n l e t hub / tip r adius ra tio of 0. 356 , a nd ex i t Ma th n umbe r o f 0, 3 0 3 . T he number of bl a de s is 1 7 and n o s p l itters are used. D ES V A L (4 , 3 ) • 1 7 . T h e d es ig n p oi n t pr es s u r e- r at lo ti p-spee d co r relat i o n is b e i n g mo d ifi e d 1. 6 perc e nt t o m a tc h a k nown comp r e s sor r p m .

D I _ ' _ t h[ , ( _ 3, 3 ) - 1 . 0 _6 . [ _ u r n e_ 6 h as a n air f l o w ve] .o oi _ y o f 5 0 .

L L / S , r o _l d _ll c y tim e of 0.0)2 se c on ds , a nd a m ean d i a meter o f 15.0 i n ch.

T uCb lne 7 ha s an i nle t Msoh nu m be r of 0. 1 96, a m e a n wo r k o o e_ -

fi c l en t o f 1 ,5 2 3, and an exit Ma t h nu m be r o f 0.25. The tip so ll d-

it y is 1. 0 a n d t h e as p ect _atl oe of the _i_et an d last stages a_ 1. 2 and 2.2 , re s p ectively. A co n st a nt h ub r a d lus d esi gn is s p eai - fl ed , D _S V A L ( 8 , 7 ) • 3. Th e d i sk m a te r ial is a hi gh stre n gt h su per all o y wit h a r efe r ence str e s s of 125 , 0 0 0 psl.

T h e des i gn c ru i se M ath nu m b er o f pr o pe l l e r 1 0 is 0 .5 a nd t h_ p ro p e l ler ha s 4 bl ades . The a cti v it y £a cto_ is 1 3 0. and t h_ t_ speed is 600 . f t / s. The propel le r lo a d i ng i s 18 . h p / _t 2 , DESVAL(5, 10 ) = 18.

Fi g u r e 23 illu st rat e s t h e complete _ebu q _ut_ u t _ o r t h e tur- bop rop sa mp le cas e . T his inclu d es the con£i g ur a cio n , .he r n: Pd T - na mlc , a er omech an i cal, an d p rl n t e r p _o t aec tio n _. Fi gur es 2 _ a r i d 25 illu s tr ate t he l o n g a nd s h o_ t f,_ m o u t p u t s of th e aero _ c ha r - i ca l c alc u l at ions of W AT E -S.

, i _ 4 O _: C ! H / _ . P A G E 13 OF P _O R QUALITY $¢ NCDMP ,|I o N DS TAT m ll p JTYP E_ l , 2 ,kp 2 ,_p 2 pSp2# D p IU _ 21 p lO*O J J C 3NF(Z p l | "l m 2 * 3 * 4 e S o 6 p_mQ* 10 * 11 * 3 _ IO*O * JC _ N ¢ (L J_ I'b*O J T*3*G * _ * L Q *O * ..............................

J Cq N F fl _3 )'Z plp4pSp 6 *B_ D p IO _ II p O * 7 _ IO*O _ J C 3 N F(I _ 4),4*O, ? ,16*O _ S _ M 0 .................................................

4,3,1 TU R B OPR O P E NG I NF S AHPL E CASE CONF _ GU _ AT X ON DAT A 11 STATIONS 11 COHPO _ (NTS C _ N P ON _ NT N _ INO C O MPONENT ........... _ P , S TRE A N ....... DO W NSTREA M NU _ BER TYPE , STATZONS STaT Z DN S -- 1 1 ZNLET .............. 1 ................ O , 2 0 ~ 2 2 DUCT B 2 0 3 0 4 CO H PRE SR 3 0 4 0 .......... k ............ _ ..... _ UCT B _ _ ......... 5 ............... 0 ..........

5 4 CO _ PR E S R S 0 6 T 6 2 DUC T R 6 0 8 0 T _ .... TUR B I NE , _............ 7 ......... g 0 2 OUCT S 9 0 _ O 0 q _ NQ _ L E tO 0 It 0 ...... 10 10 .. . PR O_......... .- - - .1L _ ......... _ ..... 0 • 0 11 11 SHAFT 3 5 T 0 ) ZNLT 1 DUCT 2 .............. ¢0 _ P--.-3-- ..........

DUCT _ O N P S CO _ P 5 6 T T UPB T DUCT 8 N O ZZ _- * _ ............................

SHAFT (111 IS C_ qqECT E D TO CONP(Z) A ND ¢ONP( _ 1 AND TURB(7) &qO FLgure 23. WA'L'_ -STurb o p r op Sa mpl e Cas e Debug Output.

OR IGINAL,p ,_ ;, ii ' _ t 5 OF pOOR QU I _ , LI'|'Y sW T L _ N _= t _ Z p3_4 e 5 e ? e B _De lO _ U e T W N _ C(t p Zl , Z OP2_ 5*O p ] W_ EC(l e 3 ) , 6 t ZP l o3 * O e l e .............................

T W_ EC(t,4I- Z O P4J S*O p l W qSC(l p SI - 7 _ Z p4 *O w l _ .I W_ EC(I,6t R I O, t . $ = O . ...........................

TW_E C(1 p TI - e p S P S p O p 3 p O _ O , I W_ EC(l p_ )- ZOp t , 5*O _ ; q _ E ¢ (l _ 9) a 16 p l _5 *O J .................................................

; _ qEC(l _ IO )- Zl p 6*O D t W qE C (1,II)-13 . 1 pS *O p OESV&L(1,3I . .4 _ , S***3S O el? t_ Z S O _ -e.&G3* Z *O*.*I* _ O- * *ZSS*I*O16 p OE _ VA L il, SI = .33,Se _ ,SbI _ lSe e 2 _O . _ *20 5_ 2 _ O o_ I**O.**318 _ *9 _ 9* DE _ V& L (I*6) = S O. _ . O t2 _ 15* _ DE$VAL(I _ T)..196.1.S23 _ l.0 _ I* _ *2.2*.2 _ *12500 0 **3* * l . _ OSSV _ L(1,1 0 ) = ,5 _ , _ 130 . * b OO* _ lS* P SEND _ ig u_ e 23. WATE-S T u r b oprop Samp l e Case De bu g O u tp u t (Co n t d ).

9 8 O R IGIH A LpAGEiS

OFpOOR qUA U TY

¢4_E Z _E_ IT ZF ZCAT _IN 4 ,),1 T U R BO P RO P § N G t fil[ SA M PL E C A S E * G E NC S * , o (4, _ , _ $ tt l, 2 I qAx C _ NI) I T[ r J N S O C C UR AT ******** ** *********** * ****************** _ LT NN VALUE _ TqT O* OeO00 14 e? LB t SQ][q TT '_T O * O * OOO 5 1SeT O EG R C N Zq O * O*O OO 7,7 LB I S E G *************** *** *********** * *** * ****** 01. ) ¢ T H N " 3 VEL T T O T P TrJT R ST A T kR E k G A N ,490 _ t4. 5 t9. '_116, L Tqb, ,:)10 t.401 _ Oq E R_ Ot US LZq IT ST4 GE 1 WO Z _K W RLD W SHRO W OZFF eL RHO 5,1 ,6 2 * ? 4 J 6 3*06 ,t34 _ ; _ R RR _ R T[P N B UTZPC OSTR 8STR WE I GH T STAGE Z 4 ,0 _ ,' J 4172 _ * 4,59 17 ].322*? 222 6 3 , 4517E, 5 *? 29, 5 I: RP .r4 _ N T • 5 ,t0 _ N ST' _ ' 4 ,EZG H T LENGTH C _ NGRA Z _ IE q TZA I 1 1 .32 4 ,?P E,68 Z9, 5 n_ J*.T N _ qQ VEL T TO T P TOT P STAT 'UREA O A R * SO_.l _ .EE* EZT*I _ J S bl* 50 3 6* * 09 _ 1,391 = R _ 1 _ EP _ 0 TO "-IP 4,0 _5 ,82t0 _g 61, 827, 80 5 * q! _ q W [ CW [ 121,¢)6 1c) _ , 35 ?* b S 7 , 6 _ (.**e************* _ * TO T A L CO _ IP NE Z G HT _ S 17,1 F i gur e 23 . WA TE-S Tur b op r op S am p l e C as e De b u g Out p ut (Co n td) .

I00 * O F PU OR Q _ % L Ii' Y e s M A _ ¢_[T|N NS _CCU R A T O eoee*eee* _ e*eeooee*ee* A LT _ PT1T Q * 0,000 TT q T U* 0.000 _ *ecq _ ss n V ER O t JCTeee L_ qGTq= _ , _ _ IGHT= 6.I * C E qC 5 • t e * _* *e****e**2 H A X CONO | T |n N S O CCU R AT _ LT q N VALUE RT _T O* O*OO0 5q, 2 L R I S O t N TT _ T O , 0.000 E 2 6*0 O E g R C WIN O, O, _ O0 2 ,4 L_ / S E ¢ OUCT M N _ VEL T T q T _ T O T _ ETAT A R E A _ AN *300 4 _ 8, 8 2 7,. 8518, BOO6* _ 09q _ 392 ***** RE C A LCULATE UPSTRE AH OUCT CONO [ T I ONS, SP E C _ F _E O RP H _ UCT N O V EL T TOT _ TOT P STAT AREA GA_ * _ O? _ T, OZT* B518, Tg8 2 * *og? l* _ g _ q O R _ _An [ l J $ LZ _IT S TA G E 1 _ OZSK _ qL _ _S HRO M R| FF CL RHO O.O . _ 1 .2 4* 2 A* _ 6 * _ 3R $0 _ RP q R T I P _ UTT P C _ STR RS T R _E I G_ T STAGE l _ ,5 _ 4 _ 72 _ 4*50 1 5 1106, 5 _ 1462. _ 0691* Be4 2 607 N STG _E|_ HT LE NGTH CEN GRA X NE RT I A 1 1 _. 01 6, _ 4 _ .3 _ 2b*?

OtJ:T N _ VEL T Tq T P T O T P STIT A R E A G Aq , _ 0 _ 3 _ q* 11 _ 22436* 217 _ 3, *06 2 L * _ ?2 _ R _ q E F P _ TO _ 2 ,63 _ , _2_ 7 _2_ 36, 113 5 , _2 9.

_ l _ 0 _ l C_ I *****,**********te* TOTAL CO c o _E I G qT 1 5 14,0 Figur e 23. WATE-S T ur bop r op Sampl e Ca s e Debug O utput [Co n t d).

I 0 1 O R IWH A Lp A& Z | g O F pOOR QUALITY * HaT T m e • •oeeee • e*eeez ALT qN VALtJ E PT_ T O* U * OOO L A_ *7 LS I S g rN T T_ T O* O * OO Q 2 465*? D E E A ¢ _ U T O* 0,000 IE* _ L O l SEC O UCT N N q V _L T TqT P TOT P $T A T AR E A Q A _ *l q 6 Aq _ * _A6 A* ! 1 4 1 9, l Oa O T* ,101 1, I 0 0 U T IOqAX S T • (S S O E N _ G H T t A TR N I T _E ZE*4 3 Z a _ q* .2 _ 6 * Z O Z 1,00 080_ T_ qTqE ? HEC _A N|C A L D E Sig N _ I T N ST G _ W qK C A R EA , _ 0 _ 1 .0 I*SE_ *101 _ IT R T[ P _H U R _E L H qPq MA X R P _ TORE 1 _ 23, _ _ ,6 _ 2.93 2 _ 0* _ _ L? E Be 417_ 8. 41 E B * ST A G E 1 O r S < _L_E V _ E H _ ¢ _ S E AR _ .7 .4 . _ 1 . 4 1*0 1, _ 0 S o R O E L 4 _ A C4 A R_ A R HU _ R t |# HS UT[ _ AX STR _E ZGH T L E ng TH S T G Z* _S O _. 1 *l qb .101 _* qS _ * _ S _S _ 32 _ *4 _ 8 _ qe ?cO b _ e _ _ gl _ T _ O| S K _ LA _E V _ E H_ O CASE A R $o _ OEL _ _C 4 AR E R R H U _ R T | P _ UT _ qAX STR _ E _ GHT LENGTH S T G Z _LA OE R O _ T _ T R E S 5 Z S 55081,T _E S LZ H ZT Z S 5 0000,0 *q _ T RE S _ _S T _ t _G H R EO _ C E SH A FT $R EE O _R _ MCR E AS E EX|T M A CH MUMQE R ** _* T _ R E. R ,2 _ 4 *LTO _ *g _ 4*04 _ 8 1 _ T _, 6 _ 508 _ * 9, E 1 _ *6q _ 6 , S T _E _ qL _ E V A_E q _ O CA SE AR SDR OE L _ flAC _ AREA R MU R R TZP N _ UTtPMAX STR _E | _ HT LE N G TH 5T G **•* _A Rqiq _ _ L L_| N _ ST A G E O E S _ L_ ZT E X CE EDED *** _ * 8 _ &nfi R _ qT _ T e E _S I S 101?Yo,g OE S L I _ T I$ 50000,0 *R_ Tq E S S _5 TOO 4%G H RE OUCE S HA F T $ REE O OR | _ CR E ASE EX i T MACH NUHSER•* 2 . 4R _ • E* _ *23 _ 03 _ 4 2.g3 4.7g 3 _ l? _ A*E _ O1Tgg* 15.64 E*_ q 4g* S T _ LE q _ TH d EZGHT CENGRA _ NERT| A 3 5 ,_ 0 53*A _ 4*g _* O U S T q _ V_L T T _ T P T _ T • STAT AREA _ A _ * ZSO 4 h 9 . 1 _ 7, 2116 . _ 03 g * . * 666 1, _ 3 _ OR TR 4 0 E F _ Q TO T_* L lO*ll; 1. _ 03 .86 _ 3 'lt16* _ I SE_ *I 15 _ 7. _ _ 4 _U T ANOZ FL _ 4 R Figur e 23, WATE-S T u r bop ro p Sa m p l e C a se Debug Outpt _ t (Contd), 1 02 eeoeeeeeeee*seeeoee T O T A L TU nS W E | G H T |S EI,4 ii+D *llilii $ il o • * * OF POO R QIJALI| y o, e s e,eoeeee* 2 _ A N CqNOtT| n NS O C CUR AT do * S ill*m,lOO S e S *IS***** A_ T qN PT _T O* OeO00 TTgT O* 0.©00 ******* * ** * * * ********** R_ " _ , 3 0 R T, E * 5 7 L E NG m | . 2 7 AREA* *44G R H O n *2 Oh CAS W T | NC W T W TOT 1.14 e67 Z *DL * NO Z 9 * M A X C ON O|TZONS OCCUR AT *********************** ALT _N I T _ T O* O*OOO TT O T _ , 00000 ****** * ** * ****** * ****** VE tGHT" 3 *50 LENGTH m 11.15 T R W T I 0000 *•****** • • • ** M AX C nMOZTI[ O N$ OCC U R AT ALT qM VALUE _ 'TI1T re O,OO0 155 ,0 LB t SQL _ YyrJT O* 0,000 1135.3 D E S R C W [N O* 0*000 1.0 Lq l S E C qI_ t s_ ' _ UT L E NGTH HA C _ I dS _ EC , b, _a _ 1.08 ?, 2 0 ,0 E L E * 5 0 7 CAS W T LZN W T NOZ W T |qC l i T FRA I_ E W TOT , ' _ .5 11, E to4 40 ? 5_ 1,:m 0 2 ,0 l ••Q015_ 1_1111• * p_ r 3• 10 *

I " ' '

_A_ CO N t rI T i ONS . OCC UR _ T Figur e 23. HATE-S Turboprop Sample Case Debu g Output (C o n t d).

10 3 CA S E I_E_TI_ICAYI_ 4,3,2 TUR _ QP R g? ENGINE SA M PL E CAS E

)

_EY G H T _N PUT OA T_ | N E N G L U_I TS WEIghT O UT P UT . fl _ TA IN EN G L UN I TS C q q _ W T C _ qP A CCU U P STR E_ RkOZUS DO _ NSTRE& _ R4DZUS q _ s sr L EN L E N R I R Q _ I RO RI RO q[ Rq NST _G E 2 * _ Z*4 3*4 O*O _ .4 O,O O,O O*O _ *A 0.0 OzO 0 3 17.1 A *? S.I 1.2 3t _ O*O 0.0 1. _ 4*6 0o0 0.0 1 4 _ , _ Z* _ 11.0 4.6 ? ,$ O*O O,O 4.6 ?.3 0.0 O*O O 14.0 A * _ 15.4 1.4 2.5 O _ O O*O 104 4. _ b *O O*O 1 6 t2.0 702 22. b 6*9 _ *L O*O O,O 6,9 6,1 O.O O,O O ? 53*4 6 * _ 21.? Log 3 o6 OeO O*O 2*9 6:2 O m O 0. _ 3 t* _ E ,3 23.9 3.3 5. 6 O*O 0.0 3e _ 5, 6 0,0 O,O O 3,5 tL,l 3 _ ,1 O,O _ , 6 0.0 0,0 OoO _ ,0 0,0 O,O 0 LT _ .5 3,0 1 _ .4 1,2 _ .! l*4 E * _ O _ O 0.0 0.0 O*O 0 q_ qE E_I N E _ E I GHT * 1? 6 . _ T _ Tk L ENGINE L E NGTH • 3501 _ ¢ _ ESS _ RY W E I G H T • 38*5 NAX |_ UH RAO I U S • 801 _A T E _ CH dEI G HT _ O*O CENTER _ F GRAVZTY • 8.1 E X4AU S T 5YS T_ W T * S , _ G E4R _ flX ' _ E[G H T • _ 4. _ =ROPELL E R WE IGHT • 1 _ qoo T1T4L E_ G[NE _ E[ GH T • 433*4 Fig ur e 23 . W A TE- S Tu r bopro p S ample C as e Debug O u t p ut (C o nt (_ ), OF POOH QU / _ U1 Y I I

/

L , t _ !

_. g , o J ,- , _ B _ : m & 1 0 5 ORIGIN A L _'*_, Q . _ I _:. ; OF POORQUALI Y Y (iA |i [ DEN '| I F I_A II _N A,I, L Y UREQPnO P riNG | H i | ANPL i C E il W E IG H T | NPU T O n t A XN 6N OL U NI TE H || O HT OU T PU T D A T A | N ING j- UN ITS ¢ONP li T CQ R P A CCU UPS T R EA N RAO|US OOIIN S TR E AR RA DIUS NO E | T LI N L E N nl R O R | RO R | n O R| n O NSTA _ a * b 3. _ J R4 O*O lea 0.0 0.0 OeO JR4 0*0 geO E I ?* L 4*7 8. 1 _ ' 2 | *J O*O O*g 1. 2 4*6 O*O O*G 1 4 6* L 2 *9 1 _ .0 4* 6 Te E O * O 0 * 0 406 T l_ 0 .0 O* O 9 A 4,0 4,J _ S,A t*4 a * E OoO g*O _ 04 4* B g* _ , d*g 1 0 8| *0 70 | | 2 06 6 ,9 G*i , G ,O O*O 6,9 0._ , 0.0 O*O (; 7 SEe4 6.9 2 1. ? i.9 So6 B e0 g*o |*Y b e 2 g*6 ODD -: 8 _ 00 E *| 22.9 2 *9 50 6 O*O 0.0 Ro B J *6 O*O O*O C 9 2*5 I J .,I E S* Z g*O 5*6 D,O 0* _ G *O E* G D*g O*O _* 1 _ _ ,S O*O 15 , 4 _ . 8 _ , 3 1.4 R o E g,g geg O*O ' g o d ( BARE EN GIN E NE |; H T • 1?60_ TOT A L EN G INE LE NGT H • ED*I A CC E SSO R Y HEIGH T • | 0* 5 qAxINUN RA O I US • 8,1 NEAT E X¢fl h EI G HT • G *O C ENTE R OF GRA V ITY • 00 1 EXHAUST SYST EN W T • 3*5 G E A R BOX HE I GH T • 214,9 PR_PF LLER HE I GH T • ISOeu TOTAL E N GI N E I E IG _ IT • 4B_ .4 _ ' Ig u r e 24 . WA T _ -S T ur b o pr o p Sa m ple C a se L ong ou tp u t, CASE I O E NT I F I CATIO N 4,B,1 TURBOPROP E N GINE S ANP LF C A SF NEIG *f T I NPUT BITA I N ENG I. UNI T S V E I G_T OU T PUT DATA IN E NGL UNITS B A R E ENGIN E N§ iG H T • 17 6 ,5 TOT A L E NGIN E L EN GT H • BB ,I AC CE SSO R Y UEIG NT • ._e•5 N AX I NUN RAO|US • (hit NEAT EX CH NE tG;tT • Dog CENTER OF G R A _ f ZTY " 001 EX HA US T STSTE N _ T _ 3, 5 G E A R BOX WEIGH T _ ' E_ Ao g PR,_P E LLBR H EIGH T • _S OtQ T O T A L ENGINE HEIGHT • 4S3,4 1; ' ig u ro 2 5 , W A T i_ -S T u rbo pro p S a mpl e C ase Sh or t Output.

4,3,2 Turbofan Engine Fi g u re 2 6 ill u s t rat es th e c o n fi g ura t i on o _ th e sample t u rb o - _ .- fa n t es t ease . T h e eng i n e ha s two spo o l s , Th e low - pr ess ur e sp ool ! oon sl s t s o f a tw o - s tage a x ial fa n , T-s ta_e , a n d tw o -sta ge axial i l o w- pr e s u r e tur b i ne. The h i gh- pr e ss u r e spo o l o on sist s o f a s i n g le -stag e c en tri_uga l c o mpres so r drive n by a si ngl e - s_a ge a x ia l h|_ h - p r e ssur e t u r b i ne. The eng i ne h as s r e ve r se-_ lo w _ u r n er a nd a ml xe r -oo mp o un d e xh au s t s y s t em.

F i gu re 27 i ll ustrat e s the i n put r e qui_e d t o e s timate th e weig h t o f t h i s e n g in e . T h e first tit l e card is f ollowe d b y t he c on fi gur at io n inpu t , n am el ist $C . T hi s e n g i n e c on fig u r ati on is nea r l y i d en t i ca l t o t he de fa ul t an d r e qui r e s f e w c h a n g e s. _ o m po- nen t 15 is a mix er i n stead of a n o z z l e , an d sh a ft 16 acnt ai n s _e fe n, T- sta g e, an d LP t urb i n e .

Follow i ng t he s e c on d tit le card , t he _ne r _ > _ y n a mic i n p u t ; s s pe ci f i e d i n the ST n am el ls t. The m as s f!a w ra te, tot al p r essure an d t emperature , an d fuel / a lr r atio ar e s pe ci fie d f o r eac h si s .

tl on . T h e thr u st a n d f u el flow a re e nte r e d i n t he "P E R P F" a rr a y, but t h e s e ar e : p t lonal input s an d a r e n o t r equi red for exe c u tlo n.

Ho w ev e r , t h e mi x ar flo w a r e as , D A T O UT(I, 1 5) an d D A T O UT(2 , 1 5) _re req uir e d and m us t be i npu t fo r t he m ixer w el gnt a n d dim e n si on c al- c u l at io n s .

The a e r o m e c h a n ic a l inpu t s are next, a n d are c ont ai ned i n t he SW na m el ist. D e f a u l t value s h a ve been u sed f o r m o st o f th e "X WMEC " a[ r a¥ s i nce t he sam pl e turbofan conf i gu r at io n i s so close t o t h e de f ault con figur a tio n . H oweve r , IWM E C(7,2) e nd IWM E C(7,5) a re se t e q ual to 2 f or t he t wo - st a ge fan, a n d IWM E C{7,7) is set e q u al t o 1 f o r th e s l n gl e- s t age t -stag e LP c o m pres s o r . & two- sta ge LP t u r b i n e i s in p ut , IW M EC(5 , 13) • 2 and c omponent 15 is spe ci f i e d as a f or c e d m i x er.

10 7 LOU OF P OORQU A L IT Y A,l|*2 TU RBOFAN E NGINE S AN PL| CASE B: 4T Y P| (ISI -8 , !

JC O NF( ZT _I I-9*JC O NF (I E, 2 |eE,T* I I, J C O N F . (1 6, E i sI B _ O _ SE N D 4,S,: T URB OF A N E NG|N E S AN PL E CAS E f ' S T WY F e l?*l16elel? Bp|* B*ll lo |e9*OO? p l*g6g p *O |O_ l*g69 pl *? B B w * l_ O p le tE_m E e B eOlOJBOB o LBAJ i . TOPA ESe l %e 6 96 _l E,l _ Sj A Be E B?p 42 0178j L% eG96plOel A Bs | eABeS] l J Z e _ Oe t TOO t S E*193j E eBIOebQ%jEQB* 2 69JIOA*SEOJ I OE*IE B JAOvOETJAO*426JET*34?J TOTEN Pe J lO,T _ E62,B p ?BIoB, ZeTB6,6 _ SS Z o;S pE e? _ g,O wE eOE?,6 _| eI l B B o _pES ?Bo? p 2 077* . lJ E O?l o B*L69 %o A* 2 *168 ? *?s PARm l leo* : e*O192*eOlgE p oO l gZ _ oOZB lp *O l OO p *O _ OB w PERP P ( | )*691* 2_ B IB * 9 1 OkTIqPlS Jl ) l e6S P DiTOUT(X _ IBIeSI* ! OO _ IGoSB _ SE N O |_ N E C(t,?teb _ l _ AeO,l, I _ N E C(ZJ23|eBJS _ B _ lZ, _ JOJOJ Z _ R E C(I, IS | * _ S,6 e O, D E SVAL( I J _ Jee S b _ I* ?_ *4 _ leBe | * e I*B _ *4| I O* _ Oe e I*sO* e | * _ *96B _ O E SVAL( L JBJee% p |OeJOeJo _ * _ O E SVAL( I JBieoS6plo? _ o%JEeB* E eJL,Sjo4]*O*JOeeI*jOoJlef*96Bo O E SVAL¢I _ TIoeABJl o TJeO _ IeS p l o .S _ I, _ J o_ O _ Oo*O,, _ Ie _ OeJ _ , _ e B 61* B E SVAL(I*BIne4 _ %,jO, _ -L, _ OESVAL(I _ 9)ee42*AoI _ o59 p_ O op ZeO o * o ;9 _ ZeOo _ Io*Oo * * $ T _ *9? _ " OES _A L( _ ) _ O|ISSo _ oOO B IOJJe _e F OE SVAL(IpII|eo l bJle 24 pls6J _ e l o _ eBI p ZESOOOoJ E o _I * p O ES VAL(LJIEJo* _ *So*O, ) * I ** O | SV A Lf1 _ IBIe,ES*I o E _ I,6 _ l,S _ Z,O _ oBI*IESO00, _ I**I,* O E SVALII*I _ tu* _ *8, _ I _ *O** S EN O Figure 27. WAT E -S T ur b o fan Sample Case I n p u t. I 1 09 T he "D R SVAL" va l u e s f o llow th e "IWM R C" i n p u t s. In this caa e , _ mos t "DES V AL " valu es a r e s p e o lfled , t h e " DEFAUL " value s used for _ , _,; _ , _ . ,_ ( ,J om2 ,) n e nt 4) , in t er co mpre s s ors duc t (c ompo - n e nt 6 }, tu rbi n e exit duct ( Qom p one n t 14} , a nd sh aft s ( c o m p o -

nent s 16 an d 1 7). The fan, (c o mp o nents 2 a nd 5) h as an i n l et Math

number o f 0 . 56, i nlet hub / tip r a di u s rati o o f 0 . 4, an d e x it Ma t h number of 0°43. The t ip solldi ty is 1 .5 an d t he firs t a n d la s t stage a s pe c t r at ios a re 2 . 0 a n d 1.5 , r e sp ect i vely. The fan u til - I ze e a c o n s ta n t t i p ra dius d e s ign mod e, DESVAL(12,2) -3° ; and a 3.5 pe rc e n t s c ala r is a p p li e d to th e d e slg n- po_ n t pressur e-rat io c o r rec ted tip-speed c orr e l at lo n, D E SVAL( 1 3 , 2) = 0 .965. The inter- c o mpress o r d u c t, c o mp o nent 8, has an i nlet Mach number o f 0 .4 an d a l ength-t o -he lg ht r ati o o f 4. 0 . The in l et mean ra dius i s d e t e r - m in ed fr o m the u p str ea m c o m p o nent , LP c o mpre s s o r 7 . The b u rner th roug h-fl o w vel o city i s 5 5 . ft / Q an d a b u rn e r res id ency time o f 0 . 0 0 8 s ec on d s is specified. The inner di a m e t e r o f the burner i s spec i f i e d as the o u ter di a m eter of c om p on e n t 9, the HP t ur bin e (DESV A L(4,10) = -9 _ ) . T h is i s h o w revers e -fl o w b u r ne rs a r e h a nd le d wh e n t h e m e a n di a m e ter i s n o t kn o w n.

T h e HP t u r bi ne, c o mp o nent II, ha s an i nle t Ma oh number of 0 .16 , t ur b i ne m ean w or k c o eff ici ent o f 1.24, an d an ex i t Mach n u m- be r o f 0 .31. The t l p solidl ty is 1 .6 an d the aspect r at io is 1 .2.

A d isk re f e re n ce s t re s s o f 1 2 5 ,000 p si is s p e c ifi e d, DESV A L(7 , 11 ) = 125 ,000. T he for ce d m i x e r h a s a l en gt h to hy dr a uli c d ia me t er ratio of 0. 8 and has 8 lobes.

Fig ure 28 i l l ust r a te s th e c om ple t e de bu g out put for the t u r- bofan sa m ple c a s e. T h i s in cl ude s t h e c o n figur a t i on , the r mod y- n a mi c, ae rom e cha n i cal , an d p rin te r p l o t secti o n s .

ii0 $¢ O F ' P O_ l _ _ L; ,h . II Y dl_ Pk(15l- _; dC _ h l _ (IT _ l)' _p d _ £ h FCl _ ,2) u_J T w gI p JC _ NF(l _p_ t' 1 3 w O _ % 3.+ T U _MQ F A h EK G |KE $ A _ PL + CASE • ¢ _ hF |G Uk A TICh O _ T A 1 4 STAT _n NS 1? CGM P Gfl E h _$ C _ PU KEK I fl _| KC CLPFOhENT _ PSTR F A _ DG W N$1R L AM _ UFdE _ 1YP[ STAT _ flHS STAT I O N S 1 1 IhL E T 1 0 6 2 2 _ CO PPR E S R 2 0 3 0 2 OUCT B _ 0 _ 0 | 4 _ FCZZLE _ 0 S © _ C _ PRES E e 0 ?

2 OUC1 B ? O ' _ 0 ? 4 CD P PNESR O O g IO 6 2 O_¢ T b 9 0 11 0 _ C _ RE$ _ 11 0 _ 2 13 1 _ 2 Ou C T S 12 0 1 _ 0 II _ TURDI _ L I_ 13 15 ¢ *l _ 2 _ L C T B I_ 0 16 @ 1_ 5 TLPBINE 1 _ tO IT 0 1 4 2 D LC1 S 11 0 1 0 G 1_ _ _ lXE k 15 _ lg 0 1? 11 S_ AFI 9 II 0 O ¢|hLT 2 ) ¢ _ NLT | ) T <DU C T 6 ) < D UCT _ ) 8 4 1 0 g cTu _ o 13 ) (OUCT O) _ CCMP g) ¢COMP g) 12 15 cO bO l lO ) <_ UR6 11 s 1.

CTURB 11 _ I D c D UCT 12) 1 6 <T _ ke 1 3 ) • uUCT 1. ) _ nlXR IS) SHAFt 1 15 1 IS CO K SLCItO TO C _ PI D ) . H _ COS +l 11 _ h O 1 _ R6 1 1 3 | A5 ¢ S _ AF1 |17) I S ¢O K EE _ TE _ TO CO _ P(g) _ q P TU E B l ll) AhO 11 1 OF pOORQUALI3 Y Ib li I ,I B_

" 8

4. 1 G, ,4,_ • , I 1 12 ORIGII' _A L I , . _ , : .. {'j OF. P OO l ] QUA L iT y la O JlOg O W_WW W _ _ i v M _i B i -_ j . JJ . j . j * j . j * JjJJ I liill i lll i llll l ll l _ I * U Il il l lll lll l l lllll _l l i *ll* ; m. m--m. * o * u * o. = _ = r ii ll llilii t l l iti lil i t lll lt lllilll l l l _ i_ 11 3 ORIGI _ , ! ALP P_ C _;;'_ t" " OF POOR QUALITV Sb ; kPEC(l s 2)-Z P I p Z w C _ S p C p 2 _ |b _E C(I _ 5) = 3 _ l , 2 , C _ 2 _ C _ 2 _ Z kP E ¢(l p ?|*6 _ I*4 _ C _ I _ ' | k r S¢( l ,13) = 9 _ 5 _5_ 12 _ 2 _ 0 _ 0 _ ]k M EC(l*l _ )-I S_ 6 1 ¢ p CESVAL(I _ 3J ' ,4 p 3¢e*O, * -Ie p ii ¢LSYAL(I _ 11)'o16 _ l.24 _ l* _ 2 _ l*2* o 31 p t2 _ CO0**2, _ l, _ ...........

IL _ D _ ' _ gure 28 . WA TE-S Tur bo fan Sa m ple Case Output ( C on td ).

CAS E ID EN TZF | C A T I CN 4, 3 , 2 T URBQ FAN f N G ZN F SA _ PLE CAS E _ llllilliiliU * * OF POOR QUALIT Y QIIo ee O *e om *2 OLCT P NO _E L T TO] P TOT P STAT At_A D AN * S 6O 621e 36 3 * IDLE* 222 2* * 3 79 Z*600 L lZFP A X S TR E SS D E K W GHT IA TR H I T [_DE * 2 _ ]T G_ o 0 2 _ 0 3 00 _ e b O e6 0 _ CC MP RLSSDR 3 NE CH A N|CAL D E S|G N LDADIN G N S TG D EA _ U TIP ¢ RPN C _e N N AX RP N 1.181 GaD 90C9 2 3 E 70 2 94042* _t_ 560 _ 4842, FF AN E kT • 2% $ 4 S TA G E 2 kO W B _S kh N¢ GL RHGG QH OD AR 1.0 X*b 2*6 C,O 2*6 3* 2 016 B 0168 2 * 00 SPR D E L H H A CH A R _A A HUB R T|e NS UTIe MAX STR ME X GHT 1I N T N AX STG I l ee* kAAN Z NG FCLL(wING STAGE DESIGN LZNZT _X C _ P E O *el*e $ 1 AOE WO _ s G UE F F ICI kNT 25 1.1e D E S L T_ TT tS ,q O * 4 S T AG E d G RK G CEFFZDZENT TO HSGH e ADO STAGES OR | NGRE ASE H I T |N PL T ** 1, _ 92 220 2 .5 _¢ * 3 7 5 1DEE 4*3S _2 23 0 2 01 3 S TeeD ToE | e l , $ 6 3 * 22* STAGE 2 kO M B N S kN N C ¢L R _ UB g _ O A R 3.1 .9 .9 * 9 2 * 2 2*? .160 g 160 1. S 0 $Pfl _E L H MA GH A R EA R H _ B _ TS P N _ UTZ Se AX STR N E EGH T T IN TM AX ST G Z 1*497 2212 1 49 S * 2 7 9 2 *80 4,5S 9 6 2 58 2 *1 2 5643* 7.9 654* 6S h 2 0 * h S T G _ E X GH T L E N GT H ¢E _G R A Z NE RT| A 2 2 D,k6 7. 3G 3.06 2 1. _ D_ ¢T P NO _ EL T TO T P TOT P S T A T A_A G A P * 430 564 1 T 46 . 6 2 69* 55 2_ * * 7 19 1 . 19 _ PR AD E F P L TO HP _ .3 G_ 08690 _2 e9. 746. 1117* HZ H G kl C_ Z 34. 4 7 I?Bo + G X ?* + O 1 3 000 e o eeee , _ * ee eeeo e o4 ee TGT A L CON P N E IGHT IS ! )O,S t * • DI _ CT 6 * I * ll *e** e_ ** _ * 2 / q A ] _ ¢C*hO | T | ONS *I'CCUI _ AT el ll * Q e _e l l o q , l ee eo 4e l ,e _ A LT ? _ PIC T D* .6- _ C 4eoeoeeeoe o , _ e _P C ? * eooooooooeeo2 P J X CGSD X T Z ONS OC C UR AT e o e6*ee o ee o ,eoe** o qe4 8 e,eeoeoeeeeeoeoooe A L T P N VALU _ PT O T ©* . 6 _ 0 43 e3 LD O SO r N TTCT O* *630 ?3%6 ©LG R Ck Z fl C* * 630 306 LO I _ C e _ ,ee*** _ eeeoe o * o_ e _ *eeo i * _ e _ eee* _ ****** 6LCT P NO VEL T TOT P TOT p STMT AqEA GaP • 43 0 962, 740, 6 260 , 552 3, , 110 1 , 39 _ eeeee RECALCULAT E UF S TflEAH OUCT C O HDITfQNSp 3P _ ¢IFZBD RPH CLCT P NO V § L T TOT P TOT P STAT A _ FA GAR ,435 5 660 T40, 62_ . 3508 * *110 1 *39 9 L TIP _ AX S TR E SS OEh W GHT I A TR H I T 12 3 504 120010 , 1 6 8 , 134 1*20 * 800 C C RPRESSO _ ? M ECHANICAL DES|Oh LCADZNG N STG C l AN U TIP C _D p C _mM RAX _ P M . 9C7 1*0 ?* 4 ? 9 5 0*7 348 _ 1, 2 917 3 * 3 4841* STJG£ 1 kO W O W S W N HC CL RHO6 PHO0" AP 104 *3 . 3 1.1 .O 1.2 016 0 0166 1* 3 0 5PR D_ L H _ A C H AREA R HU6 R TIP PA UTIP _ AX STR k EIGHT Tiff TPAX STG I e _ ee bAPN _ hG FQLLCk| N6 S TAGE D _SI G f LIP _ T f_ CE _| O eeoc, S TAGE bORK OCEFF|C| _ NT I $ *91 _ [$ L _ PT? TS *qC _ e S TA6 _ W OFK ¢O E FFLCIENT TO HZGH _ AOO SYiG E _ OR INCR E AS E H I T INPUTee 1 0 3 90 10 , 9 *4 3 5 , 1 1 0 Z* _ 9 9,7 3 ?0 t 1 3 _ 04 1 2 6 e6. 900 7*00 1 40 , 9* 3079 1027 1 , 1 7 Oe P " 5 STG _E_ G _ T L _ NGTH OE h G _ A _ NE R TIA OLCT P NO V _ L T TO 7 P TOT P $TAT A _ FI GA M 0400 DS O. e1 6 . 6 _ 64. 7 9|6. .0 _ 1 1 . 1 q i PR AD _ F PC 70 HP 1 , 3 5 0 *bSq Z @46 4 , 616. _ 410 HI HO _I O W l 1 77, _ ¢ 1q 6 * 1 0 _ *C1 3. 63 teeeeeeeeee.eee,eeo TOTAl. COI_ P hEIGHT t$ _. 9 _igu c e 28, W&T_ / -S _u c bo [ a n Sa m ple C a_ e O u tput ( Con t d) .

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. * *., o *,*,, O f p O 0'_ QUA LI' IY O m O • ** o * ooom e* o * E _J_ CCh_ T |_ N S O¢CU_ A T i _ i OQ lti O il OOOO iillii Q i ALT _N P l O T 0 , ,b_O TTCT C* , G_ ¢ n _o S uE* R To E , BO £ E NGe Z **q AE EA* ,091 E) l_ * ,16 E C A S _T X _ ¢kT WT OT o4 b e4O ,B E Qq l J ieeeeeeeeDe e * O O I :E C 9 * Q * oooO * o * olo_ * 2 RA ) _ criI*,O I T I ONS OCCUR A T e I G OI i m G B ,G$4* t 4G e l e o $** Ooo_o000Q G$ O GG OQ ALT R h VALUE PTOT 0* * G S C g e* E LB I _ Q | N 11OT 0, ,bEE O].T* b O E G g CkZH O* ,6S 0 E *8 L| I S E ¢ 411iili_ iiililill ii $411 _ ililiiliillIilii P NO V E L T TOT P TOT P ST A T AR E A SAN • AE O .*TT o BIG* 8380* ? 4E 8, • °O E e 1, $ 91 S TA G E I BLADE ST RES S E XO E E OS A LLO WA E L E* STR E SS * 9tO _ g* ALLO _A OLE ° 4614 E * STAGE , 1 EEZSK _ E L O kSHR9 _ OZFR Ct _ HO 502 ' O Ib i_ S oO _ i _G o_ 6 SPP RRI_ R T ZP NO U TIPC O _ TR O S Tfl k E S G HT STAGE I 5,3. _ 61iGgO* EeST _ 0 IE45*6 4a )6OEe _)].Ogg° . a Go G 14,4 E ET G dE _G HT L E NG T E ¢ k :NG RA ZHE R TT _ P NO ¥ EL T TOT P TOT P sTAT A RE A GAM CI " CT 1 q, t 6 Be E4 E * _ I4 14°4 1 • 190 341, 13Q6 _ 4 4 740* 4366 | * ,O A_ _o 3 _ 6 FR A n E F PG TO HI; • .*33% , t _2 01 44 T 40° l _ lgb ° 1 6 4 q* H| HE _ Z C _ ][ iq E ,I C $ 41,T0 ee _ ; T ,?.,6 4 iliiiil*i**i*iitlli Tr, TAL C C ,I _ P kE | GflT ZS 9,6 • HPT 11 * F igure 28. WATE-S Tucbo f a n Sampl e Case Output (Contd).

11 8 RJ_ ¢ c_o lf x_ s Q ¢¢ UR Ar OF POO H Q tIAI.,II7 OQI * O_II * eOB i e * OIQOI * moeOe_OoOmI * I ** OQO_ AL Y nN ¥AL U !

P10l b* .610 lil*l LI I I R |N • 1 ? 1 Of O* . 65 0 IS ?t *? O E G P CbCU ? G* ' , _D O a i d L _ l Sg¢ AIO I II U tO U _I I I U _ l l S Q t lOII IB I I*III _O II OI © LCT t P NO V _ L 1 TG T P TUT P ST A T A R |A GA m I *]60 38| , _b_ * 4 2_1 * _Z 2 4 4. s O ? 8 |*2 99 : L TI P PA X |T R IES 06 N WS_ T I A ? R , _ 1 ?

[ 1 _R B I h i _1 R_ C _A fl | C A L 8 E S X G H H I T _ S TG _ _ R _ ¢ A FEA *O3S _ lO _ * _4 0 *076 • t? R TI P _ HUO OEL H h_ N A X R FP TO R G SI A G£ C X S K _ LAO E VA _ E HHD ¢A S 6 6 R _ *O . 4 . 6 1.0 *? X * 2 0 SP R DEL H HA¢ _ AREA R H UE R ? |P _ UTt m_A X S T R NE X G H T L E flGT H S TG | eete k _ Xfl6 FG LL C_X EG ST A_ § O E S X Gfl LX HIT EX CE _ O E O _ ot* **STRE S S X S TGG HI G H _E SUC E SHAFT SPEEO O R ZNC R E A_ | [X X T _A C H Nb R I§ROe |,_ 0¢ 247 , 4 ,26C ,0?6 _, o _ 3 , 30 73 208 _, 6 _ 7268 , ?,sT 2, _ © || , S TG LkHGT H _ k X GH l ¢ E HGR A |flER TI A 1, _ 0 ?*6? 1.2 2_ * _C CT P N O VEL Y TGT P TO T P ST A T A RE A GA R FR TR _ O EF P8 T O T O , I 2. _ 3 L.242 . 89 _ _ 0 _ 2.3 20?7ol _ 0??, _ P l fl H OUT A_ Z FLO _ H P ¢*o**e _ ee _m ee * e _ e* e T _ TAL ?UR8 b E |GHT TS ? i T 4 _ oeeeoet _ ee _ e • OUC T 12 • iltto ' eleetet 2 _X CC _ D X TIDN $ _ ¢CU _ AT IIm lIIIIIIIOIIIUI II Ul I O A LT R N PTO T O * , _ 5Q 1I CY ¢* .65¢ R_m 2 * 7 6 ATe ]040 LE NG m E t a 2 CAS kT | _ ¢ VT _ TOT * _ *70 1 .7 3 _i_ ur e 28. W AT _ -S Tucbofan Sa m p l e Case O utput (Contd), 1 1 9

[

ih : OH IGIH _L i' _&6__ OF pOORQUA L ITY e $ e _T IS e

' •

11111t 00 $$1 0 I _A N CG h G | TZONS OCC U R AT _ * $1 1 ii O_ UO mo *Ol O OOleOJlOO$$$ I i $ ii SB iOO S f $ A LT _ N V AL U !

PT C T O * .6 _ 0 10 2 . 1 L| O SO | N T ICT © * _ 6D C a O?l* S O iG R Ck C U T O* , B S C Q *C LB I SfC e e *$$* $ $ee$$e$$$e $ e, $ e,0ee$e m $$$$$e$$$ei C LCT P NO Vt L T TOT P TOT P S TAT A RE A QA N • E|O 4 9S, 2 0T E e 147@ 6 o 1 4 2 C60 e140 lest| _ TlP _ k X STRESS D iN N GHT I A T R N I T 119 6. 4 S |?S ? , . 2B6 .2 6E 1 .00 * ?_ 4 I _ RB I hi 13 N [ C hAN ZC A L O| S ZG N H I T N STG P A RK C Ak _ A • T 6 4 2 .0 Z* ECC . 140 UT R T Z P RH b E OEL _ QP N H AMRR _ T ORG 1196 . 4 3. 9 3 3 001 1 0 6 . 0 3 4041e 3 6_ 41 , 2 46 2 0 ST A G E 1 £|SK BL AG_ ¥ & h E H N O CASE A R | , 6 2 . 2 1.4 1 .| 1.1 1 ._ 0 S P R DBL M N AC _ A RE A R HUB R TzP NS UTt _N AX STR NE |G H T LENGTH ST G Z 1 ,$ 49 S | , 4 *ES C .14G 3001 3 , 9S 6 _ 11 9 6** S ITSt* e, 9 0 _ . 6 0 2 e, S I A BE E Cl SK EL A D E VANE HW D CASE A R E *O l*T 1. _ 1. 2 1 , 1 2,00 S P R OEL H H k Ch A R kA R HbB R TIP N_ U T Z _N RX S T R NE S G HT LENGTH ST G S Ie BE E $ 3,4 ,ETC *l Te 2 * T C 2*9 _ 66 1196.4 403 S2. O* S O 1 . 59 2 6 .

F PA NE N T • I E . 5 0 h STG L EN GT H k E tG H T C E NG RA |N E RTI[A E 3 o_ e 30*2 9 S * O 52* CL CT P KO ¥ EL T TOT P I'OT P S T A T AO E A G i N , |l O B 0 4, 16 9 40 S BB I * S_E O, 0P44 1, _ .1 2 7 F R TR A O E F PO TO Y_* t 2 . 501 1.* _ .Z S .9 143 .*)6 6 0*5 1 _ 94** 1694 * 4 h ZN H OUT ahO , t FLG N H P S S B *E9 429, D 3 *_ ;42 9.01 1 S BL * ee , e e_m ee $ oe e ' e e Se e $ 4 $ T O TAL TUNS liEZGH T Yq ; _ 0*$ $*$eeee eq ,$ ee$ $ $ e OUCT L_ $ $ e $$$$$$$$ 0 55 *E PA_ CthUlTlO _ S _ JCCUR A T $$ 0 55 $$mp_m o _ * $_ e $$$ q $ e*0 5 l ,' igut'e 2 8 . WAT E-S T u r bo f a n Sa m pl e C a se Ou tp u t (C ontd ) .

1 2 0 J_ L A * *11_ PMO * *1_6 ¢A $ _ T Ih ¢ _ T WTO T 4* _ 90_ e _ 098 ORIGINA L PAQ_ 11 9 oo q eee*e** _ * _ OF POORQUALriY e NOZ 4 t Q qO*4q _ *** _ * 2 HA_ C _h 01T|ONS DCCU _ A 1 ALT _ N P T OT O o .6 5 C 1 1 C T 00 0 65 ¢ OQ O**4 _Q *OO** O@ * _q iO* SQ kEIG H T= 9.1 6 LEhGTH a 90 _ 0 TR W T= 0.00 O @ S_ F 16 * e , OO O _ * O **** _ * 2 MJ_ TORQUE CD H DITOO h I CRQU E _ 05,2 SHAFT 16 DO DZ L ENG ON _ T • 95 *76 1 2 006 *84 ,8?

1 CTAL IN _ K II A _F 1H| S S POOL I S _ o eeee,e_ e***** e SHA F 17 * e * p _ t TCRGUE C U hOITIO _ OoOeteoo*uoeee _ e*eo _ s * * 1 C R O NE _ ***e,e,e _ ,eqoooe*ete o SFA FT 1?

DO £I L Eh G O h kT 1. 9 1 1.2 5 9 02e _ *21 *10 1CTAL INERII A OF TH I S S P O OL IS _ 1.

T _E Oh VALUb OF Z 011 F ILLION IS HIGH Figu_ u 28. WA T E- S Tur bo fan S am p l e C a se O utput (C o n t d).

1 22 r _ * ** , , ,* ** ,,,,* * ,,, OF PUO I_ Q U A I .I ( Y ACeS W T e O u Q le* q * IIgO l* J CC$ WT* 3 1 .61 C _S E I OENT | F L C A T|CN 4 ,3,Z'TUR6OF A N C N GI N _ SA F P L| C A S E k _IG_ T I hPUT [A T _ |N [bGL UN Z T$ k[IGHT GUl P UT DAT A IN ENGL _ NIT$ C L PP kT ¢¢ M P ACCU UP S TR |AP O AO Z U $ DGMHSTR|A _ RAO | U$ h © _ $ T Ll _ LEh R| RC P Z _ 0 _ Z R G RZ _ 0 NSTAG E 2 _ 5.1 ?.4 T *4 3*5 4 . 5 OeO 0.0 4.0 4 *5 GoO GeO C 3 _ 0 4 2 6 *7 2 6el 3 lq 4*5 OeO 0 * 0 _* g _ e _ C*O (*C C 4 3*2 ge l 3 5* 2 OeO 4* _ OeO 0.0 O*O 4* 1 0*0 OeC ¢ 2 5 .3 7. _ 7. _ Z* 8 30 _ 0 * 0 0.0 3*2 4*G ¢*0 CoC 2 6 *3 0 8 8.1 3 . 2 4.0 0.0 0.0 _ * 2 40© 0.0 @ *C ¢ ? 3, 8 1. 2 9.3 _ *© 3.? O*O 0.0 9*0 3.? ¢*0 ¢*¢ ) e *9 2 . _ 1 1 .8 3*0 3.7 O*O 0.0 |00 3*T ¢*0 C*C 0 q g*b _ .3 15.1 1 .5 _ * _ OeO 0*0 1*5 4*G _ ,0 C0¢ 1 1 _ 3507 _ 03 _ 0,4 _ *0 _ 03 000 0,0 4,O 5*3 C*0 ¢00 C 11 7.7 102 16,3 _ 08 3*4 C*O O*O _ *T 3*5 CoO CoC • 1 12 1.? 3.1 1 _ ,4 2 .8 3*4 0.0 0.0 2 .8 3*4 C* O ©*© © 13 30*3 4*0 2304 _ 00 309 0. _ 000 2,1 3 0g C*O C,6 2 14 *a le _ 25.C 201 3,T 0.0 0.0 _ .1 3*T OeO @*© O lff 2. _ 4, _ _ 9, _ _ *0 3*8 _ .0 4. _ _ *0 4. _ C*O _ *C ¢ 16 *g 0.0 1 _ e1 300 4*4 _ * _ 4*0 O*O 0.0 O*O Co0 C 17 .2 C . O 0.¢ 3,C 3,7 1. _ 2*5 ©*0 _ * C _ *0 _ *C C BAPE ENG]N _ N _ GH _ • _ 30*6 TOTJ _ _ N _ ZHF L _ NGTH * 29,4 _ CCESS O_ Y _ |IGHT • _ ?.6 qAX _ MUM _ A0 _ U$ • _ * _ H _ AT _ XCH be|GHT • 000 C_ NT _ O _ GRAV | TY • 25*0 E X HA U ST SYbTE _ _ T • 5,7 1CTAL _N G: _ e #_ |G _ T • 173,9 FL _ ur e 28. WATE-S Turb o f a n Sam p l e Case Output (Con t d).

1 23 r 4.4 Program D i a _ n os tios The WA TE -B pr o gr a m o o n talns s e v e ra l er r o r chec k s to aid t h e u s e r in obt a i n i n g an a c c ep ta b l e engine design. A lis ti n g o f the s e • err ors , an d t he s u b r ou t ines th e : occ u r in, a r e included i n Table X I V. N one of t he s e e rr o rs w il l cause t he exe c u ti on o f WATE-S t o stop. T h e subroutine t h e er r o r occurred i n m a y be te r - f m ino r e d an d s ub s e q uen t component calc ul a ti on s can be i n e rr o r .

_ 4 . 5 Program Structure The WAT E -S c o de is wr i tten i n FORTRAN I V an d ha s bee n c hec k e d o u t o n t h e IB M 370 c o mputer. H o wev er , th e c od e wa s d evelope d a t ! Garrett on a CDC 170 mac h ine in an overlay s t r u c t ur e. The c o d e is i wr i tten i n single precisi o n an d requires no s ubr o utine s bey o nd th o se in t h e IBM FORT RA N IV manual. There is n o chara c t er m an l p u - l at lo n and o nly f u l l w o rd test s a r e us e d when t e st i n g BCD input.

The main pr og ra m i s calle d WAT E S and i n t u rn calls INPUT an d WTEST a s sh o wn i n Figure 29. S u bro u t i n e INPUT reads the c o nflgur- ati o n ($C) and the rmo dyna m i c (ST) d ata. Su b r ou t i n e WT E ST reads t h e aer om ec h en lc a l ($W) data and ca lls the c o mp o nent r o utines.

These com p o nent r o ut i nes are ind e pendent o f each o the r , and s o m e u se t he same l o wer level r ou t l ne8 a s o thers. A ft er all weights and dimensi o ns have been e s ti m at e d, E NGPLT is c a lled t o m ake t h e printer p lot .

T h e f o ll o w i n g variables in the c o mm on bl o cks m ay be refer- enced by a c o mp o nent wei g ht esti m at ing r o utine depending on the c o m p o nent t ype: DATOUT, WTF , TOPR E S, TOTEMP , FAR, C O R F LO, JCONF, JTYP E , NCOMP, NOSTAT. In n o case i s an y value changed b y t h e we ig ht e s t im at io n c o de.

1 25 ORIGINAL P A G E I; _ OF P OOR QUALI ' IY 'PAB LI _ X] ' V . WA TI " - - S E I _OR M_ . SSA G E8 g Uq R QUT T N E F IG *J RE - _L O WR ATH , _ 1*t O _D N T E_ O , CH E ¢ _ L O J_ C SU_R, UT I_ F .I S _ - ......

tar t *AV ERA GE O I SK S T R E SS GR EA TE R THA N ALLOW A BL e S T R ES S ee Rt* X X KX X XX.

SU qRO U T I N E OUC h - SUBRO UT I N E CE NC n N- S T AGE ! [ 1 DT SX S T RE SS E XC E EDS A LL n dA g LE. STR E SS - XX XXXX X . AL L D_AR LE • X XRX X X X .

ST& _E TT BL A D E I_ TR E SS EX C EE D S A LLG WA GLE. S T RESS • XXXXX X X. A LLO WAB L E - XXW X YX V , _ s T A _E II 9LkO E f : R E GU E NCY L ESS T HA N _ I R E V SUqR n UT I N _ C M EC Hm t*et WAR N I NG ¢OLLO WIN G S T AG E D ES I G N LZ NIT EKC E FO E D tilt* 8 LA,E PO n T S T R ESS I _ xxxx x xx. DE S LE MI T ZS XXXXX X X.

t* S T RE_S I S 1'00 NIGH R E DU CE SHAF T SPEED OR E N C P EASE E XIT _ i CH NU M_E Rtt tttt NA _ NIH6 FnLLO WIN G STAGE D E S IG N L|PTT EX C EE D ED crete ST AGE H U R TS _ RATIO E S X. XX DES LE N ST IS X. XR eR H UR TEe R A TED I S TOO H I G H R E DUC E H U _ T ER R AT I O S NFU T ee • met _ A R NE N G FOLL _ VIN _ STAG E D E SI G N L I_ IT E XCEEDED erie* _ TAGF H U _T Z _ RA TIO ES X.XX DES L | N I T IS X.XX te H U D TIP RATIO I S TO0 LO W I NCR E ASE H Uff T I P RA T | Q I N PUT _ e tet t W A _ N | NG FOLLO WI NG STAGE D E S| ON L | MI T EXCE E D E D ott _ e l I T S T A G F R _ ATZ C t $ _ X . XX q E _ L I_I T I S X X .X X ttST _E A LL O d A_ L E P RE SSU RE R ATlfl I S TOg H IGH R E DU C E |N PUTe* • tet _ fA R H| N G FOLLOH I NG STAGE D ES IGN L E N I T EXCEED ED teat* LAST STAGE N ACH NO S S X.XX D ES LIMIT IS X . X X t OL A_ T S TA G E HACH NO |S TOO HI G H R E DUC E ST A GE EXI T N A CH N ? I HPU T t _ • toe _ A R NI N G FOLLOW ING STA_E D E SIG N LIfl l T EXCEE D E D tete_ qTAG E _L A D Y HEI gh T I S X X.X X DE S L E NI T IS XX t X X • * ST A GE B LAD E WE I G H T IS TOO SMA LL CHANG E D ES OP R DR REDUCE H I T | N_ UTet tree WA RN I NG F GLL _N I Nfi S TA GE fl _ SS G N L SN S T FXC EEDE D tea t * _ ti _E W_ eK C _ER F I CIFNT IS X X oX X D E S LI_ IT I S X X , NX • * _ Tl _ r W_R K C_E FFICI EN T TO H IG H , A DD ST A GE S O R INCR E ASE H I T IHPUTee C _ PR E SS _ R tl tPE SSUR E _AT ID |S TOD HIGH CO M P RE SS , R 1 | STAG E AMD EL R OE P AR AmE TE r S. qE A H I NGL E S S 1 2S ORIGINAL | _, , : , , , OF PO OR Q U ALI _ Y ORIGINAL P /_ , GEi _ OF POOR QIIALI 1 Y WATE il

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R ADT U R i _ F RAME m C WT DWT IMPDEK _ O I SK TURW T I _ OL DWT SI Z E DIEK STREE TVOL TABX 8T R E8 TVOI .

DU CT CEN C OM Figure 2 9 . Diagram o £ S ubrou ti n e Co nn e c t i vity .

12 8 B as ed on th e informatio n i n N C O MP an d the JT Y P _ a r ra y , th e pr o pe r co m pone n t routine is c a l le d with t h e component n u mber (_ ) t a s an argume n t . E ac h o omp o nen t i s expec t ed to fill WAT E ( X ) , ALE N G(I), TLE N G( 1 ), R O( 1 ,Z) , RO( 2 ,Z) , RI(I I I), R Z( 2 , Z). RO tati ng compo n e n ts al so fill R PMT( 1 ) . Th e s h aft c o mpon e nt fi ll s DSHAFT(N) where N l u th e s h a ft co u n t fr o m t h e i ns i d e ou t.

The a rr ay "C O NV E R " i n common CON VER are conversion fa c t o rs t o co nve rt En g lish t o SI u nit e for o utput, o r Sl to En g l ie h u nit e f or input. H o weve r , a ll interna l c alcu l at lo n e i n WAT E -S _ re p erfo r m ed in English u nits.

UNITS UN I TS LOCATIO N VALU E E NGLISH t o S I 1 2.540 0 i nch cm 2 0 .3048 0 feet meter 3 0. 45359 ibm K g 4 0 . 0 929 0 3 ft 2 m ete r 2 5 0 . 0 27680 ib m / i n 3 K g / cm 3 i I 6 0 .68948 ib f / in 2 Newt o n / c m 2 7 4.8824 I bm / f, 2 Kg / m 2 1 8 0.55556 oR O K !

9 2326.0 B t u/ ib m J o ule / K g i 0 0. 0 7457 0 hp KWat t ii 47.880 i b f / f t 2 New to n / m 2 1 29 5.0 CONCLU BI ONS A ND R E COM ME ND A TION S T h e WAT E -S pr o gr a m ca n pr ov id e t h e le vel of ac c ura cy in pre- dl o tlng we i g ht end dim en sio n s of b o t h sme ll e nd int e rm e dia te p r o- - p u lsi on gas tur b i n e e ngi nes th a t I s r e qui r e d f or p r e limi na ry en gin e cyc l e selection s t u di es. On an absolute bas i s , t he ca l cu- la t ed w eig h t s and dimensions ha ve been d e m on str a ted t o be w it h i n ± 10 perce n t for s i x refe r enc e engines. On a r ela ti ve b a s is , between engines of t he sam e ge n eri c fami ly and c on f i g u r a ti on , the ac c u r ac y i s much be tt e r , estimated a t less than ± 2 percent.

T h e f lex i bi li t y of m odel ing th e e n g ine allows v i rtua l ly a n y c onv e nt i onal o r no nc onve n t i onal ga s t ur b ine e n g ine to b e a n alyzed given t he t her m o d y na m i c performance of the eng i ne co mponen ts .

WAT E -S is viewed a s an exte nsio n of the B o eing WAT E -2 c o de, that is , the s t ru ct ur e o f t he basic p r og r a m wa s n ot alte r ed. H o pe- f u l l y , t hi s s hou l d allo w u s ers o f t h e WAT E -2 cod e t o e as il y a dap t WATE-S t o their de sig n s y st e m , i f d e sir e d .

T h e f o l l o wl n g i m proveme n ts t o th e progr a m are re co m m en d e d : (a) E xit Math n um be r should be used to size t he b l ades fo r axial t u rbi nes inste ad o f inlet M a t h n u mber a s i s c u rre n tl y i n u se.

Exi t Math n um be r is a m o re fund am ental para m eter in t u rbine design an d the c o de sho u ld reflect this.

(b) T he heat e xc han g e r calc u lation sh o u l d be m ade t o " clos e the l oo p" o n fix e d tube n um be r . Cu rr e nt ly , WAT E -S esti m ates the pr e ss u r e drops thro u gh the he a t exchanger for the i n p ut num- ber of t u b e s . Thi s c o uld b e com pa r e d a g ain st the ther mod y- n ami c data, and the n um ber va rie d until the re s u l t s a gr ee.

F or no np rop u lsi on e ngi ne s , e. g . a ux !l l a ry p o wer uni ts , stati o nary p o wer units , an d vehicu l a r engines, the heat ex c hange r c a n be the la r g est an d heav i est c o m po ne n t in the engine , and hence, s h o u ld b e m o de l e d a s a c c ur a t ely as p o s- s ibl e .

1 3 0 E ( c ) For d uct s, bu r n ers , a nd du ct bu r ne r s w h ere t h e Z D wa ll ie s u bject e d t o c ol lap s i ng pressure rat h er t h a n i n ter n al b urst - ing pre ss ur e , t he calculati on s ou tli n e d i n S e cti on 3 .1. 6 sh o ul d b e incl ud e d. Du ct w eig h t s are typicall y a small £ z ac- ti on o £ t o tal e ng i n e weight b u t a d efi n ite c o mp on e n t acc u racy impr o vement c o ul d be o btai n e d . I n a dd iti o n , the du ct m od el c ou l d be impr o v ed t o ra d ially match bo th the u pstream a nd down stream c ompon e n t s.

(d) Bl ade me a n s o li d it y sh o ul d b e use d t o de t erm ine t h e b l ad e count for ax i a l c ompo n e nt s i ns te ad of the blade ti p s ol i d ity .

Blade m ea n solidity g en er all y has m o re s i g n i f ica n c e a nd c on- s i ste nc y th an doe s blad e t i p sol i d i ty .

1 3 1 A PP EN D I X A LIST OF SYMBOLS A area ( cm 2) O w h e e l s peed ( m / s ) AF activi t y f acto r V v o lume ( om 3) AR a sp e c t rati o W w eight (k g ) C bla d e chord ( c m) _ s h ea r st re s s ( N / cm 2) C-D c on ve rg e n t -d l v er g e n t _ turb i n e wo rk nozzl e c o e f f i c i e n t C / S s o lidit y , b lade c ho rd t o P de ns it y (kg / em 3) spaci ng ra ti o D dia me te r ( cm ) _ r o tati onal v e lo c i t y (cad / s) F f o rc e (New t on ) o nor m al s t res s ( N / c _ 2) g g rav it a tiona l cons t an t e h ea t ex ch anger K S _ - _ e f fec ti veness N-S2 O r ati o o f local t otal te m pera tu re t o GR g e a r ra tio s t an d a rd te mpera tu re h he i ght (c m ) 6 r atio of loc al t o t al h / t hub / ti p rad iu s r a ti o pr e s s u re to st an d a rd H t o ta l en tha lp y (J o ule / kg ) p r e ss ure co mpressor w or k HP h ig h -p r e s su re s p ool c oe f f ic ient I r o ta tio n a l in e rt i a ( cm 2 -kg ) J 77 8 . 16 f t- l b f / B tu Subsc ri p ts: K f act or for blade v o l u m e h h u b L l eng th (c m ) t ti p LP lo w-pre s sure s poo l B bl ade M n M ac h nu m b er c case o r cor rec t e d N number of elements c o nditi o ns P p r ess u re (N / om 2) S st ato r PTO po w e r ta k e of f hw h ardware PW p o w er ( KWa tt ) St g s t a ge R ra d iu s ( c m ) D di sk RPM r e v ol u t io ns per mi n ut e SPL s plitter S b lade spac i ng (c m ) 2 e n g i ne in l e t st a tion T t e mper a tu re (°K ) o r m me an to rq u e ( c m - N ) i l inn er t thi ckness (c m ) i o o uter TR b la de t a p e r r at io 1 32 A PPEN D I X B REFERE N CE, 1 . On at , E ., a nd G . W. K les e , "A M et hod to Estimat e W ei gh t a nd Dim en sio ns o£ L a rge a nd S m a ll Ga s T ur b i n e E ng i n es - Fi n al R epo rt", NAS A CR - 159481, Januar y 1979 .

2 . Es hb a ck, O . W., e d . , Ha ndb o ok o£ E ng i nee ri n g F u nd am en ta ls.

3. S c hmid t , A. H ., " A M e t hod fo r Estimati n g t h e Weight o£ Air- cr a ft T r an smissions" , S AW E Pa p e r No . 112 0 , Ma y 1 9 76.

4. " Ce ramic R o tary H e at E x ch an g er Co r e s", C or ning Gla ss W o rks, 1 974.

5, K e lt h, F . , Principle s o f Heat Tran s fer, I nt e rnati o na l Text- b oo k C o ., 1 967 , p p . 483-5 0 8.

6. " Pa r a me t ri c Pr op elle r Data Pa c kage f or Advanced Te c hn o l o gy C o mm u ter Aircraft Pr o pel l ers, Small Tran s p o rt Air c raft Te c h- n ology Propelle r St u dy ", Ha mi lt on S t a n da r d .

7. F i shbao h , L. H. a n d M . J. Caddy, "NNEP - The Navy-NASA E ngi n e Pr og ra m", NASA T M X- 7 1857 , De c e m be r 1975.

8. Gerend, R . P., and J . P. R ou ndhi l l, " C o r r elat io n of G a s Tur- bine En gi ne Weig h ts a nd D i me n si on s " , AIAA Pa p er 70-6 6 9, June 1 970.

9 . Klee s, G . W. , and L . H. Fi s h b a c h, " Airc r a f t E n g ine Weight E s t i m at io n M et ho d " , SAW E Paper No . 1248 , M ay 1978.

1 0. GASP Gene r a l Av i ati o n Synthesis Pr o gra m . Aer o ph y s l cs Resea r ch C or p o rat io n , N ASA CR1523 0 3.

ii. Baers t , C. F., and D. G. F u r st, " General Aviati o n T u rbin e E n gi n e (GATE) Study " , AiRe s ea r oh Ma n u fact u ri n g Company of Ariz o na, NASA C R -159482, 1 979.

12. Mech t ly, E. A . , " T h e Interna tio n al Syst em o f Un it s " , N A SA SP-7 01 2, 1 973.

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