C77.-#"- t(,;t mU'_'Oi

(llA_ A-CR'-'161760) ADVitltCED It81-231_4

OXYGEH-_¥D_OCARBON ROCKET ENGINE _TUD¥Bimonthly PEogEe_ RepoRt, I Feb. - 31 MaR.

,, 1980 (AeEojet Li,_uid Rocket Co.} 53 p Unclas,{ _C A04/_F A01 C$CL 21t-1 G3/20 24073

Advanced Oxygen-HydrocarbonRocket Engine Study

Contract NAS 8-33452Bi-Monthly Progress Report 33452M-3April 1980

Prepared For:National Aeronautics And Space AdministrationGeorge C. Marshall Space Flight CenterMarshall Space Flight Center, Alabama 35812

By:C. J. O'Brien

!l

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1981014651

https://ntrs.nasa.gov/search.jsp?R=19810014651 2018-11-12T10:23:19+00:00Z

ADVANCEDOXYGEN- HYDROCARBONROCKEI

ENGINESTUDYi,

CONTRACTNAS 8-33452

r Bi-MonthlyTechnicalProgressNarrative33452 M3

lO April 1980

PreparedFor

NationalAeronauticsand SpaceAdministrationGeorgeC. MarshallSpace FlightCenter

MarshallSpace FlightCenter,Alabama35812

Preparedby: Approvedby:

en / J. IV.Salmo(k(kProjectEngineer ProgramMan_ge#ALRC Engineering ALRC Programs

AEROJETLIQUIDROCKETCOMPANYP.O. Box 13222

Sacramento,California 95813

,_._.,.................................................................-"'"_:_:':" ':-:-.....:::::::::::::::::::::........:_......::"=::'::.....:"'::-': ..................................i98i014651-TSA0:

FOREWORD

This is the third bi-monthlyprogressreportsubmittedfor the Advanced

Oxygen- HydrocarbonRocketEngineStudy per the requirementsof Contract

NAS 8-33452. The work is being performedby the AerojetLiquidRocketCom-

pany for the NASA-Marshal]Space FlightCenter. The contractwas issuedon

15 October1979. The programinclusivedates for periodof performanceare

15 October1979through15 February1981. This reportcoversthe periodfrom

l February1980to 31 March 1980.

The programconsistsof parametricanalysisand designto providea

consistentenginesystemdata base for definingadvantagesand disadvantages,

systemperformanceand operatinglimits,engineparametricdata, and tech-

nologyrequirementsfor candidatehigh pressureLO2/Hydrocarbonenginesystems.

The NA_A-MSFCProjectManageris Mr. R. J. Richmond. The ALRC Program

Manageris Mr. J. W. Salmonand the ProjectEngineeris Mr. C. J. O'Brien.

Contributorsto this bi-monthlyreportare:

R. L. Ewen - HeatTransferAnalysis

S. Kent - EngineWeightand EnvelopeAnalysis

G. M. Meagher- PerformanceAnalysis

."_ECEDING PAGE BL.ANKNOT F_,Lk_D

iii

1981014651-TSA04

L.NTS.

.!",".', I Introduc ti{ill ]

_,:,,;.*I A. Ta';k| L l,(}illP(:ycI{_C{111fi¢IIlriitJOIl[}eflnltlon 2

;L_I';;'_", [_. T,14k I] -' i Jib,lille P_r_lillo.tri¢ All_l],ysis _'_

C. '[,_skIll .-IJIuine/VehicleTrajectoryPo.rfoMilallCe 2Assessment(En{.!ine Screenitlg)

I). Task IV - LIaselineEngineSystemsbefinition 2

IL. Task V - Reporting 2

II. TechnicalProgress5u,l,ary 2

A. Task I - LngineCycle ConfigurationDefinition 4

B. Task II - EngineParametricAnalysis 12

C. Task Ill - Engine/VehicleTrajectoryPerformance 32AssesSlllellt

D. Task IV - BaselilleEngine SysLeIi!Definition 32

E. Task V - Reporting 32

III. CurrentProblei1_s 46

IV. Work Planned 46

A. Task I 46

B. Task II 46

C. Task Ill 46

D. Task IV 46

E. TaskV 47

iv

- * 1981014651-TSA05

TABLE LIST

':'!i No. P.a,j.o:.:'_ I Purlfled RP-'ICooling Sunlnary 5

i...i_ !I Methane Coolin.qSummary 6;ii'!:"_. III Oxygen Coolin,qSmmlary 7

IV Hydrogen Cooling Smmtary (LOX/RP-I Enqine) 8

V Hydrogen Cooling Summary (LOX/CH4 Engine) 9 ,i

Vl Nozzle Cooling Sunmary lO I

Vll LOX/IIDFBaseline Engine Weight Breakdown 43 1

VIII LOX/RP-I En_lineEnvelope 44 i

IX LOX/CH4 Engine Envelope 45

FIGURE LIST

.F.i_]ure No. p_a_ge

1 Major Milestone Schedule 3

2 Delivered LOXIRP-I Engine Performance Versus Chamber Pressure 13

3 Delivered LOX/RP-I Engine Performance Versus Mixture Ratio 14

4 Delivered LOX/RP-I En.qinePerformance Versus Thrust 15

5 Delivered LOX/RP-I Engine Performance Versus Area Ratio 16

6 Delivered LOX/CH4 Engine Perfmlllance Versus Chamber Pressure 17

7 Delivered LOX/CH4 Engine Performance Versus Mixture Ratio 18

B Delivered LOX/CH4 Engine Performance Versus Thrust 19

9 Delivered LOX/CH4 Engine Performance Versus Area Ratio 20

I0 Typical AOIICWTWeight and Envelope Computer Program Printout 21

II LOX/RP-I End.lineWeight Versus Chamber Pressure (, _ 20) 22

1'2 L.IIX/RP-IEngine Weight Versus Chamber Pressure (, = 50) 23

13 LOX/RP-I Engine Weight Versus Chamber Pressure (, = 80) Z4

14 LOXIRP-I En_lim, Weight Versus Chamber Pressure (, : lOO) 25

15 LOX/RP-I Fn!lineWeight.Versus Area Ratio (Pc _ 5000) 26

16 LOX/RP-I En!lineWeight Versus Area Ratio (Pc = 4000) 27

1981014651-TSA06

FI_G!I LJs.X. t..,.)

F.i_._Lre_No. .Pa_!_;

17 LOX/RP-I Engine Weiqht Vor_a_ Area Ratio (Pc _.3000) 2B

I_ LOX/RP-I Engine Weiqht Versus Area Ratio (Pc _ 2000) 29 :

19 t.OX/RP-I[ngine Wei_lhtVersus Area Ratio (Pc :"I000) 30 I

20 LOX/RP-I En_.lineEnvelope Parameter_ Versus Chamber Pressure 31

21 LOX/CH4 Engine Weight Versus Chan_er Pressure (, = 20) 33

22 LOX/CH4 Engine Weight Versus Chambe.rPressure (, = 50) 34

23 LOX/CH4 Engine Weight Versus Chamber Pressure (, : 80) 35

24 LOX/CH4 En_jineWeight Versus Chamber Pressure (, = I00) 36 i

25 LOX/CH4 Engine Weight Versus Area Ratio (Pc = 5000) 37

26 LOX/CH4 Engine Weight Versus Area Ratio (Pc : 4000) 38

27 LOX/CH4 Engine Weight Versus Area Ratio (Pc --3000) 39

28 LOX/CH4 Engine Weight Versus Area Ratio (Pc = 2000) 40

29 LOX/CH4 Engine Weight Versus Area Ratio (Pc : I000) 41

30 LOXICH4 Engine Envelope Parameters Versus Chamber Pressure 42 "

_" vi

1981014651-TSA07

I. INTRODUCTION

In the dr_cadeof tho lBBO'sand beyor1(I,tho nation'.sexpanding,space

operationsmay r_.quir__n improwd ,;urfacf,-to_orbittran._partationsystem

using advanc_.dboostervehicleswhich havo in_.roa_edp_rformanc_and capa-

bllitycompared'tothe currentspaceshuttloc(}ncept.The mlxc,d-modepro-.

pulsionprincipleclearlyindicatesthe potentialporformanc_advantagesof

usinghighdensity-impulserocketpropellantsin such large^V applications.

For thisreason,hydrocarbonfuelsexhibitingincreasedden.sityrelative

to liquidhydrogen(L.H2),at the penaltyof lower specificimpulse,are beingconsideredfor the boosterpropulsionsystemof space shuttleimprovement_

and derivativesas well as for single-stage-to-orbitand two-stage-to-orbit

heavy-payloadvehicles..I

Preliminaryidentificationand evaluationof promisingliquidoxygen/ 'i

hydrocarbon(LO2/HC)rocketenqinecyclesis desirableto producea consistent .'and reliabledata base for vehicleoptimizationand designstudies,to demon- _

stratethe significanceof propulsionsystemimprovements,and to selectthe

criticaltechnologyareasnecessaryto realizesuch advances.

It is the purposeof this study to generatea consistentenginesystem

data base for definingadvantagesand disadvantages,systemperformanceand

operatingli-'_ts,engineparametricdata, and technologyrequirementsfor

candidatehigh pressureLO2/HCenginesystems. The studywill alsosynthesize

optimumLO2/HCenginepower cyclesand generaterepresentativeconceptual'enginedesignsfor a specifiedadvancedsurface-to-orbittransportationsystem.

To accomplishthe programobjectives,the study is composedof four

major technicaltasksand a reportingtask. These tasksand summarizedob-

jectivesare:

A. TASK I ENGINECYCLE CONFIGURATIONDEFINITION

Formulateand assessfamiliesof high chamberpressureL02/IICenginecycles.

l j.!

1981014651-TSA08

1_. TASK II ENGINE PARAMETRICANALYSIS

it Gl,ll_w,| t¢_ pot FOl'lll_llc(_., wt_'l¢,]ht,, _lnd _nv(_,lope ptit'dlllO,t.ri_: data forvlabl(, cmlCel)t,,; l_a_,d upml historical data and c(mCel)t, ual (_valuat'ions.

t C. TASK III INGINII/Vi]IICL_ TRAJICTORYP[RFORMANCI"ASSESSMENT(IiNGINF _CRL[:NING)

Li a preliminary comparison engine cycles utilizing

Conduct of selected

a simplified vehicle trajectory performance model.

ii.D. TASK IV - BASELINE ENGINE SYSTEMS DEFINITION

Prepare preliminary designs of two baseline engine configurations.

Conduct heat transfer, turbomachinery, combustion stability, structural, and

controls analysis of the baseline engines and components. Conduct a parametric

sensitivity analysis including the effects of turbine temperature and number

of usable life cycles. Provide the appropriate data in a format suitable for

use in vehicle application analyses.

E. TASK V - REPORTING

Provide infomnal bi-monthly technical and fiscal progress reports,

f hold program reviews at NASA/MSFCand prepare a final report./II. TECHNICAL PROGRESS SUMMARY

., - ......................................

The overall progress on the program is indicated in Figure I.

......................"- # '_......"...........:'._" '_;.':C_L"'L:"_"_."'0:'• '....' "''_"':"_ ....."'-''"'"''._.'_""_''!,'_

1981014651-TSA09

3

• ++'+. "'+ + "" + + + .. +, ' , .+. + + + " ++t:_. _} _. ' • '+'+ + /"_+ " +'+ ..'+..+++++,, . + +'" "+ .+ , " + • . . . _ •. ' _ .. " _ + : ....... + C " . " • + +. ....... _ _ -+ + .............. _ .......... ++.-_-'.-- ....,.++.._m_'._+._ +............ ._.._++.,+-:-:-:.... ,::+-._.,._--_++--_,, 0., +........ F,++-,+....... _ ....... +_.+ .:'+ + . ++,++. • , ++_, ._.... ., + . <s,...+. ,..... , .+,+'+.,,_ ,,, , .* +'y++ ,, , " + ++ _ , +..... :.s, . ..... - .. ,+ ;'_,+" .... +,,+ '

....'-_:_",.+.'+:,..+ '- , +, +,+ '.+++''P,,+_. + + ''>.'+ ;+_,,+ ,"._o ' • . _+" + _, '+.+ _ ', "_'+' +,+.'-., +,_V,-+<'....,, ,_+,,'_" .++ . +'_,:+ ,+' .._;'+_, ,+',_+. >-';_, " ,%+,,. +' ,+._-, ,.', ,+ '..,..+ ,,._'+ + " ,',...+

]98]01465]-TSA]0

A. TASKI - ENGINECYCLECONFIGURATIONDEFINITION

1, T_h.ru._.tC.hamh_r._!'ImLt.T_rjTnsf'Or

The paraB_trlcchamberand nozzle,(, _ H to 40) cooling

analy._isis completefor the fourpotentialcoolants' RP-I, LCH4, LO2 and

LII2. Docune.ntationof the resultsis underway. A summaryof the coolingcapabilityof each propellantis (.livenin Tables I throughVI.

RP-Iwas found to be an unsatisfactorycoolantwhen a

coolant-sldewall temperatureof 550°F {theacceptedcokingtemperature

for this fuel)is imposed. If a purifiedversionof RP-I (e.g.,JP-7) with i

a coolant-sidewall temperaturecokinglimitof 800_F is used, the purified _

fuel is seen in Table I to be capableof coolingenginesoperatingat cham-

ber pressuresup to 2500 psia.L

All of the heat transferanalysesare based upon a clean

zirconium-copperhot gas-sidewall. Early LO2/RP-Iengines,such as theTitan I, the H-I and the F-l enginesbenefitedfroma carbonlayerbuildup

on the thrustchamberhot gas-sidewall. These enginesoperatedat chamber

pressuresfrom600 to I000 psia and at fuel-richmixtureratiosfrom 2.23to

2.27 (equivalenceratiosfrom 1.53to 1.51),and were RP-I cooledto area

ratiosfrom 8:1 to lO:l. Since the carbonlayerbuildupon such engineshas

been knownto flakeoff, advancedengineparametricstudies(suchas on

ContractNAS 3-19727)were directedby NASA/LeRCto be based on uncoatedwalls.

This assumptionis seen to ruleout conventionalRP-I as a coolantat chamber

pressuresof lO00psia or greater.

An investigationof the sensitivityof a carboncoatingis

beingconductedon anotherproqram (NAS9-15958). The data and approachfor

thateffortwill be reviewedon thisprogram,and the coatingsensitivity

_ .. ..

1981014651-TSA11

, ')'

. .].

i TA_BJ:.F-_!_._, PURIFIED RP-1 COOLINGSIIMMARY

COKINB WALL TI:MPERATI.IRI;LIMII _._HOO'_F

-i'Thrust I) AIb

Jlm

' ¢ Coolant AP L'

) ).p6].bf, P.s_!_ Fr_a._.tlon p,_1 "_,l

:] 0.2 I000 0.9 192 191 14.14;l) 1500 641 203 12,.88 i

2000 1.0 1210 195 12.05

2500 2322 200 1I. 45 1

0.6 I000 O.9 237 165 22.38 ]

1500 614 165 18.27 i

1" _ 2000 1210 168 15.83-_FJ

i! 2500 2063 169 14.74 i2.0 lO00 332 147 40.86

1500 794 148 33.36

2000 1466 150 28.89

2500 1.0 2517 135 25.84

5

....;...................._,.................;.-....",...-.':-..........._:;_..-:,'-,i_:_......:"'"''""_............_"...................

i98iOi465i-TSAi2

1Off]bf pst a p'_1 "F

/it0,2 I000 45 147

2000 258 '176

3000 840 193

4000 219_ 197

O,6 ]000 6}2 IP.9

2000 295 138

3000 833 147

4000 2088 ] 53

5000 4885 156

2,0 1000 84 117

2000 388 123

3000 1220 124

4000 2818 124

,_.1'::', ..-.- , . '_" • ,%,, , .:_: _' ....-,. " t . ,

1981014651-TSAq3

....

T!_!_U:_._UI

OXY(41_NC(.I(.II.INGLIIIMMARY

l'hru,;t Pc Co_'lant Ap ATb I,'1061hf pc,i,_ Fraction fmi "F Ill,

O,2 1UO0 I,0 78 82. 14,14

2000 376 % 1_,05

3000 1122 103 10.98

400U 2889 107 1U,28

0.6 1000 108 72 22,3b

2000 450 73 _[ :

3000 11?_" ,:. 14.14i

4000 28,. 79 13.23 1

2.0 1000 0.87 125 73 40.86

2000 553 74 28.89

3000 1672 73 23.59

4000 4424 73 20.43

1981014651-TSA14

TABLE IV _.i

HYDROGENCOOLINGSUMMARY

LOX/RP-IENGINE

Thrust Pc Coolant ap ATb1061bf psia Flow,Ib/sec psi _F

0.2 lO00 7.5 53 655

4000 15 440 445

5000 20 799 355

0.6 lO00 15 137 787

4000 25 405 491 I'

5000 30 680 429

l.O lO00 20 256 946

4000 30 429 559

5000 35 770 498

2,0 lO00 40 607 879

4000 50 715 594

5000 60 850 478

8

1981014651-TSB01

!_'I-'.F_

.,,_i TABLEYHYDROGEN COOLING SUMMARY

LOX/Ctt4 ENGINE

Thrust Pc Coolar AP ATb

!.06!bf psia F_l_gw_,_.J__Z_e__P_.i. ._.._

0.2 I000 7.5 72 740

4000 14.6 611 495

5000 19.4 II05 395

0.6 lOOO 15.0 199 900

4000 24.7 563 558 _!

5000 29.5 1041 484

l.o 1000 25.0 334 852 I;

4000 29.7 767 642 iJ]5000 34.6 1369 568

2.0 1000 40.0 893 1004 :!I

4000 49.6 983 684 ;:

5000 59.4 l]22 551

ii

:!

"198"10"14651-TSB02

TAB!-EVI

NOZZLECOOLINGSUMMARY(t__ B to 40)

I. BaselinoD(_siqns(LOX/RP-I)

F _ 600,000Ib Pc _ 4000psia ]

Coolant ^P ^Tb

psi °F

_"_ Purlfied RP-1 440 106O_ 77 56C

2. Scaling

^p pc3"5 F0.25

ATb -.PcO.O5/FO.075

?

4'

lO

1981014651-TSB03

II,TechnicalProgre._sSummary(cont.)

determinedfor selectcasesat a thrustl(_velof 6(10KIbf. Caremust be

taken,however,in applyingdata from lowerpressure(Pc _,1000psia)

chambers. The higherpressuresof this programrequirea mixttlreshift

towardstoichiometric(e.g.,Pc _ 4000 psia,MR _,2.9, ER _ l.IB),and the

lessfuel-richenvironmentmay not resultin as greata carbondeposit.

Methaneis capableof coolingan LO2/LCH4 thrustchamber

to chamberpressuresof 4000 psia. Above thispressurelevelthe coolant

channelpressuredrop becomesexcessiveas shown in Table II for the 600K

Ibf engineat a chamberpressureof 5000 psia (^P = 4885 psia).

Table Ill showsthat liquidoxygencan coolan LO2/RP-Ior

LCH4 engineto chamberpressuresof 4000psia. The high pressuredrop shown d

for the largethrust(2M Ibf)enginecan probablybe reducedthroughchamber

geometryoptimization.Scalingo_ the baseline600Kengineresultsin a !relativelylongchamberat the high thrustlevel,which resultsin a high I

coolantchannel^P. .i

Liquidhydrogencoolingsunmlariesare given in Tables IV

and V, for LO2/RP-Iand LO2/LCH4 engines,respectively.It is seen thatsmallamountsof hydrogenare required,theseamountsbeing co_nensurate

with the powerbalancerequirementsfor theseengines.q

The nozzlecoolingsunmlaryis given in Table VI for bothi

purifiedRP-I and LO2 coolants. The pressuredrop and bulk temperaturerisein both casesappearto be satisfactoryfor the baselinecase given in the

table. Scalingequationsfor differentchamberpressuresand thrustlevels

are also given in the table.

II

] 98] O]465]-TSB04

II, A, task I - En_In_)Cycle Conflquration Definition (cont.)

No additional work was cond,cted on this subtask pending

completion of the heat transfer effort.

B. TASK II - ENGINE PARAMETRIC ANALYSIS

I. .EnginePerfomnance

Parametric engine performance data are summarized in Figures

2 through 9 for the LO2/RP-I and LO2/LCH4 engines. The simplified JANNAFmethodology was used to derive the delivered performance for each point design

engine. A more detailed description of the n_thodology and results will be

given when this effort is con@leted.

2. En._ne Wei_lhtand Envelope

These subtasks have been completed. An existing ALRC

parametric weight/envelope computer program was modified to provide the

weight and envelope data for the advanced oxygen-hyarocarbonengine cycles

considered in this _tudy. A sample output for the baseline case (LO2/RP-I,fuel-rich gas generator, RP-I cooled) is illustrated in Figure lO. Parametric

engine weight and envelope data are presented for LO2/RP-I engines in Figures

II through 20. Table VII gives the baseline weic_ts used throughout the

analysis. (This table is an updated version of Table V of Bimonthly Progress

Report 33452 M-2, February 1980.)

Because most of the cycles studied are very similar, parametric

information is presented only for a typical baseline cycle. Differences in

these cycles leading to weight differences will be reported separately when a

con@arisen is nBde between the cycles.

12

h ar_

13

1981014651-TSB06

il 14

"Z.

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1981014651-TSB07

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1981014651-TSBO8

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Ig81014651-TSBII

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L l o o

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1981014651-TSC04

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1981014651-TSC06

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1981014651-T8009

If, B, Ta._k II - Enflln_ ParametricAnal.w;is (c_mt.)

Bas_l'InP m,_lino,w_i!.lht and onvel_pe data i'nr th_ I-,O?/LCH4

_,la.,;flenorator, fu_q-r'ich ,qas !_,,,oratm', LCH4 cooled cycle ar(_ pr_smlted in' Fiqures 21 throuqh 31_.

!! ParamL,tri(:envelope'Infnrmal,i{_n,as gt,neratt)dby the AOHCWT

coml_ut:eri_rL_gram,is (t_:l_en(h,ni_ only on thrust, area ratio,and propellant

" combination.Thesedata are presentedgraphicallyin Flqures20 and 30 for

-!_ U_ebaselinearea ratioof 50:I,but otherarea ratioenvelopedata are in-_'_i cludedin TablesVIII and IX.

C, TASK Ill - ENGINE/VEIIICLETRAJECTORYPERFORMANCEASSESSMENT

I. MissionCharacteristics

The characteristicsdata presentedin BimonthlyProgress

Report33452M-2were approvedby the NASA ProjectManager.

Z. Traje_cto_orgy_PerformanceModels

This taskwas delayeduntildefinitiveenginedatawere

generatedin Task I.

D. TASK IV - BASELINEENGINESYSTEMDEFINITION

No scheduledactivity.

E. TASK V - RFPORTING

An inform,i!prm}ramreviewwas held 7 March wlth the NASA Project

Mana_ler.It was concludedfrom the discussionthat ._uchitemsas turbine

32

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"198"10"1485"I-TSC'I3

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1981014651-TGC14

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1981014651-TSD02

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1981014651-TSD03

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1981014651-TSD05

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1981014651-TSD06

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TABLEVl!

LOXIHDFBASELINEENGINEWEIGHTBREAKDOWN

_ LOX/RP.'I L0._X/_C,_H4"

I STAGED GAS STAGEDGAS. CO_MB_USTIONGENERATO_R.C.__!BLI_§T_IONGEN_ERAT_OR

FB (Thrust,Ib) 600,000 600,000 600,000 600,000

PCB (ChamberPressure,psia) 4000 4000 4000 4000

'B (AreaRatio) 50:1 50:1 50:I 50:I

'ATTB (AttachedArea Ratio) 8:1 8:I 8:1 8:1

ATB (ThroatArea, in.2) 85.66 85.66 86.14 86.14(AllWeightsin Ibs)

WGB (Gimbal 207 207 207 207

WMISCB (Miscellaneous) 296 296 296 296

WINJB (Injector) 656 656 656 656

WTCNB (Nozzle) 420 420 422 422

WCCB (ThrustChamber) 226 226 22.7 227

WPBOB (Ox RichPreburner) 224 - 224 -

WPBFB (FuelRich Preburner) 181 50 181 51

WVOB (OxidizerValves& Actuators) 325 325 331 331

WVFB (FuelValves& Actuators) 82 82 131 131

WBPOB (OxidizerBoost Pump) 307 307 313 313

WBPFB (FuelBoost Pump) 52 52 83 83

WMPOB (MainOxidizerPump) 862 623 878 638

WMPFB (MainFuel Pump) 327 366 521 567

WLPLB (LowPressureLines) 201 201 243 243

WHPLB (HighPressureLines) 268 268 324 324

WPSSB (PressurizationSystem) 133 133 133 133

WHGMB (HotGas Manifold) 207 207 207 207

i!I WIGNB (Igniters) 60 60 60 60WCNTRB (Contro11er) ]30 !3_0 ]_30 130

/ii TOTAL 5164 4609 5567 5019

1981014651-TSD08

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.+,-,,.,+,̂ _, ; _ ± .:_'....... +.....

iIii! inl(,tt,_mlmraturefro'nxidizer rich turbin,,Gbt_ro-t_xamin,_din an effort

I in e_;tabli_htim tochntllo_lyrequlr_ment,s t_)make some of the marginal cycle_.;.- cm)ipetitive.

i:!i Completion of the heat transfer effnrt six weeks behind schedule is-f

not anticipated to cause a slip in the overall schedule for completion of

Task I and the interim program review scheduled for mid-June.V. !'mH..KPfANN[?

A. TASK I

Complete the engine cycle power balance, define the component

design requirements, establish optimum engine operating conditions, and

establish an engine cycle rating system. Document the heat transfer results.

B. TASK II

Complete documentation of the work accomplished in this task.

C. TASK Ill

Set up trajectory perfon_lance models for the most promising

engine cycle_, determine vehicle performance for tilevarious engine cycles,

and establish an engine cycle ranking based upon the mission payload results.

D. TASK IV

No scheduled activity.

1981014651-TSD11

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47

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1981014651-TSD12