Technical Paper ISSN 2383-4986 International Journal of Aerospace System Engineering EISSN 2508-7169 Vo l . 6, No.2, pp.11-16 (2019) http://dx.doi.org/10.20910/IJASE.2019.6.2.11 System Analysis of a Gas Generator Cycle Rocket Engine ٻ Won Kook Cho*ˋ and Chun IL Kim** *Rocket Engine Team, Korea Aerospace Research Institute 169-84, Gwahak-ro, Yuseong-Gu, Daejeon, 34133 KOREA †E-mail:[email protected] **Department of Mechanical Engineering, University of Alberta 9211 116 St. NW, Edmonton, AB, Canada, T6G 1H9 Abstract A system analysis program has been developed for a gas generator cycle liquid rocket engine of 30 ton class. Numerical models have been proposed for a combustor, a turbopump, a gas generator and pressure drop through a regenerative cooling system. Numerical algorithm has been validated by comparing with the published data of MC-1. The major source of error is not the numerical algorithm but the imperfect performance models of subsystems. So the precision of the program can be improved by revising the performance models using experimental data. The sea level specific impulse and vacuum specific impulse have been demonstrated for a 30 ton class gas generator engine. The optimal condition of combustor pressure and mixture ratio for specific impulse which is a typical characteristic of a gas generator cycle engine has been illustrated. Key Words : Liquid rocket engine, Gas generator cycle, System Analysis, Optimal Condition, Specific Impulse 1. Introduction UG {G G G G G G G G G G G hG G G G G G G G G G G G G G G G G G G G G GUG{G G GG UG {G G G G G G G G G G G G G G G G G G G G G UG {G G G G G G G UG {G G G SG G SG G G G GGGG GGGGG G SGGGUG{GGGG G G G G G G G G GGGGGG G G G G G G G G G G UG pG G G SG G G G GSGGGG¡GSG G G G G G G G G G G G G SG G G UG{GG G GGGG G G G UG ~G G G G G G G G SG G G G G G G G G G SG G G G G G G G G G G G G G G G G G G ¡G G OG G ZUXG G G PUG {G G G G UG pG G SG GGGGG GG GGG GGG G G G G G G G G G G G G G G G Received: Jun. 27, 2018 Revised: Oct. 11, 2019 GUG Accepted: Oct. 15, 2019 G † Corresponding Author Tel: +82-42-860-2937, E-mail: [email protected] ⡧ The Society for Aerospace System Engineering 12 Won Kook Cho · Chun IL Kim 2. Literature survey hG G G G G G G 3. Analysis Methods G G G G G v˅iG G lXUG { G G G G G 3.1. Specific Impulse G G G G G SG G {G G G G G G G G G G UG { G G G G UG {G G G G G G G G G G G G G GGGGGG G UG{ GGywTXGGjoZGG G G G G ¡¡G UG {G G G G ywTXSG soYG G sjo[G G UG {G G G G G G G G G G GGGGGG GGG G G UG {G G G G G G G G G G G G G G GGGGGGGGG SG G SG G G SG GGGGGUG mUGXGGG G SG G SG G GGGGG GGG SG SG pwzG OpTwG zPSG GGGSGGGSGGSG G G G G G G G UG mUG YG G G G G UG uhzkhG G G G G G GGGGUG slT\YUG {G G G G G G G G G G ZLG G G G G G G G G G XLUG toZG G G G G G G G SG G SG G G SG G G G G UG {G G G G G G G G G G G G G G G G UG {G G G G G G G G G G G GGSGGGGGGG G XWLG G YWLUG {G G G G G X[G G G G G ZWG UG {G G G G ot^iSG ysXWhTZTZhSG slT\SG zT[OthTZPSGsy`XSG\jSGoTXSGot]WSGqTYSGyzTY^SGslT [Schematic of a gas generator cycle engine[7ٻSG ys_^SG zztlG G mTXUG {G G G G Fig. 1^ G SG G SG G SG G SGGSGGSGGSG G SGGOVPSGsQSGGSGG G SG G G SG G G SG GGGSGG SG GG G SG G SG G SG G G G G G G G VG VG VG UG zjvylzG OzjG vTG yG lG zP[GGG GGGGGG G UG rG G U\G G G G G G G G G sVG UG{GGGG GG tjTXG GG GG UGhGGGG G G G G G ]UG {G G G G \¥]G G G G G Algorithm for converged mass flow rate[7,8]GٻGGG[GGGGG Fig. 2 UGG G System Analysis of a Gas Generator Cycle Rocket Engine 13 G UG mG G G G G G G {GGGGGGGGG Ɂ UGuGGGGGG ஼೑ G G G G rzs}Tpp^T`G G G GG G G G G G G כ GɁ G GGGGGtjTXXWUG ௖ jmkG G G G G G G G {G GGGGGGGG G UG pG G G G G GGGGGGG G G G G G XXSXYUG ^S_UGG mUGZGGGG GUG{G G G GGGGGGUG 3.2. Performance Model for Combustion Chamber G {G G G G G G 3.3. Performance Model for Turbopumps G G G ¡G G UG wG {G G G G G G G G G G G G G G G G G G GXZGG GlUO\PUG GGGGGUGm SG G GG G G G TG G ஐொబǤఱ G G TG ¡¡UG {G ȳ௦ ൌ బǤళఱGG G O\PG ൫௚ൈο௛Ȁேೞ೟ೌ೒೐൯ G G G G G G G G G G G {G G G G G G G G G G ¡¡G UG pG G G SG ¡¡G UG {G ¡G G G G G G G G G G G G G G G G G G G G G G G G GGGG G G UG G G G G UG iG G G G {G G G G G G G UG oG G TG G G lUOXP¥lUO[PUG GGGGGGUG G {G G G G G G G ஼כ௖ ܫ ൌ ೑GG G G OXPG G UG {G G G G G ௌ௉ ௚ ሺ௣ ሻ ஺௚ GGGGGGGGGG ൌ ೎ ೙ೞ GG G G OYPG כܿ ௠ሶ ೟೎ GGGG UGlUO]PGGlUO^PG GG G G OZPG כܿ ൌ Ɂ כܿ ௧௛ GGGUG כ௖ ௧௛ ܥ௙ ൌ Ɂ ܥ௙ GG G G O[PG G ஼೑ ଴ሻGG G G O]PGܥG Ʉ்஻ ൌ݂ሺݑȀ ംషభ ఊ ଵ ം ܥ଴ ൌ ඨʹ ܴܶ௜ ቈͳ െ ቀ ቁ ቉GG G O^PG 300 ఊିଵ గ CEA G 290 x cf G CFD 3.4. Performance Model for Gas Generator x c* {GGGG GGGG (s) SL 280 G UG {G G G G G G Isp exp x c* G G G G G G UG 270 iGGGGGGGGG G G UG {G G G GGGGGG GGG 260 2 2.2 2.4 2.6 2.8 3 G G G G UG {G O/F)CC G G GGGG G Correction concept of combustor efficiencyGٻFig. 3 G G UG zG G G G G G G G G UG {G G SG G G G G G G G G {GGGG GGjlhG G G G G G G G G GGGZGGGGUG{G G UG lO_P¥lUOXWPG G G G GGGGGGGGG GGGGUG GGGGGGGGG G UG{GGGGG GG 14 Won Kook Cho · Chun IL Kim ை ൌቀ ǡ݌ ቁGG G G O_PG ி ீீ ை mG\GGGGGGUG{G ܶீீ ൌቀ ǡ݌ீீቁGG G G O`PG ி G G G G G G XG UG zG G ை ߛ ൌቀ ǡ݌ ቁG G G G OXWPG ீீ ி ீீ G G G G G G G UG {G G G G G G G G G ZWG G UG 3.5. Required Pump Head Model {G GG G G G G GGG {GGGGGGGGGG G G G G G G G G G G¡GGUGpGGGGG GWUW]GtwUGhG GGGGG G G G G G G G G G G G WUW[G twG G WUXG twUG G G G G G G {G G G G G G SG GGGUG{GGG G G G G G G GGGGGGGGG UG oG G G G G G G UG zG G G G GGGGUGzGGG G G G G G G G G G G G G G G G G G G UG {G G G G G G G G G G G G G G G G G UG {G G G G G XSG XXUG {G G G G G G G G G G G G G G G G G G G G G G G G G G G G G G G G G G G G UG {G G G G G G G G G G G G UG SG G G G G G G ~GGGGGGGG G G G G G G G G G G G G G G UG mUG [G G GG G G G GG UG hG G G G G UG {G G G G G G G G G G G G G G G G G G G UG {G G G G G GGGGGGG G G G G G G G G G G G XSG XXUG {G G G UG oSG G G G G G G G G G G G G G G G G G G G G G G UG zG G G G G G G G G G G G GGGGGGGGG GGXGUGG GUGG G G 12 2.8 O/F)CC=2.2 O/F)CC=2.3 10 O/F)CC=2.4 2.7 O/F)CC=2.5 O/F)CC=2.6 O/F) =2.7 8 CC 2.6 O/F)CC=2.8 CC (Mpa) 6 2.5 O/F) regen p 4 2.4 2 65 2 2 6 2 6 4 2.3 3 0 2.2 4 6 8 10 12 4 6 8 10 12 p (Mpa) p (Mpa) CC CC G Sea level specific impulse (unit: s)GٻPressure drop of regenerative coolingG Fig.