|Table of Contents|

Influence of liquid film cooling on combustion efficiency of rocket engine (PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2023年03期
Page:
69-75
Research Field:
目次
Publishing date:

Info

Title:
Influence of liquid film cooling on combustion efficiency of rocket engine
Author(s):
TANG Liang;  WANG Kai;  LIU Jiwu;  ZHANG Botao;  LIU Yazhou
(Science and Technology on Liquid Rocket Engine Laboratory,Xi'an Aerospace Propulsion Institute, Xi'an 710100, China)
Keywords:
liquid film cooling;  combustion efficiency;  liquid rocket engine;  combustion chamber
PACS:
V434+.3
DOI:
-
Abstract:
Liquid film cooling has important influence on the thermal protection and the engine performance. In order to study the effect of different liquid film injection conditions on the combustion efficiency, a thermal test study of liquid film cooling in the combustion chamber was carried out. In the test, the jet flow rate, the number of cooling holes, and the jet inclination angle were changed, the wall temperature of the combustion chamber at the position facing the cooling holes and between the two cooling holes was measured, and the combustion efficiency under different working conditions was calculated. It was found that after the ignition of the thrust chamber, the injection of the liquid film will reduce the slope of the temperature curve. In the experimental study, under the same liquid film flow rate, different liquid film injection methods did not have significant regular effects on the combustion efficiency. When the oxygen-fuel ratio of the head is around 3.6, for every 2.3% increase in the percentage of liquid film flow in the total flow of the combustion chamber, the combustion efficiency of the combustion chamber reduces byabout 1%.

References:

[1] 唐亮,李平,周立新.液体火箭发动机液膜冷却研究综述[J].火箭推进,2020,46(1):1-12.
TANG L,LI P,ZHOU L X.Review on liquid film cooling of liquid rocket engine[J].Journal of Rocket Propulsion,2020,46(1):1-12.
[2] 张锋,仲伟聪.膜冷却推力室传热计算研究[J].火箭推进,2009,35(4):34-37.
ZHANG F,ZHONG W C.Computational investigation of heat transfer for film cooling thrust chamber[J].Journal of Rocket Propulsion,2009,35(4):34-37.
[3] 蔡国飙,李家文,田爱梅,等.液体火箭发动机设计[M].北京:北京航空航天大学出版社,2011.
[4] 杨成虎,林庆国,刘昌国.高性能液体远地点发动机技术发展[J].火箭推进,2013,39(4):1-7.
YANG C H,LIN Q G,LIU C G.Technology development of high-performance liquid apogee engine[J].Journal of Rocket Propulsion,2013,39(4):1-7.
[5] BODEN R H.Heat transfer in rocket motors and the application of film and sweat cooling[J].Journal of Fluids Engineering,1951,73(4):385-390.
[6] MORRELL G.Investigation of internal film cooling of 1000-pound-thrust liquid-ammonia-liquid-oxygen rocket-engine combustion chamber[R].NACA RME51E04.
[7] KNUTH E L.The mechanism of film cooling[D].Pasadena:California Institute of Technology,1954.
[8] TOTTEN J K.Ramjet structural elements and non-regeneratively cooled combustion chambers and nozzles[Z].Marquardt Corporation,1964.
[9] VOLKMANN J,TUEGEL L,MCLEOD J.Gas side heat flux and film coolant investigation for advanced LOx/hydrocarbon thrust chambers[C]//26th Joint Propulsion Conference.Reston,Virigina:AIAA,1990.
[10] KIRCHBERGER C,SCHLIEBEN G,HUPFER A,et al.Investigation on film cooling in a kerosene/GOx combustion chamber[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virigina:AIAA,2009.
[11] COOK R,QUENTMEYER R.Advanced cooling techniques for high-pressure,hydrocarbon-fueled rocket engines[C]//16th Joint Propulsion Conference.Reston,Virigina:AIAA,1980.
[12] ABRAMSON A E.Investigation of internal film cooling of exhaust nozzle of a 1000-pound thrust liquid ammonia-liquid oxygen rocket[R].NACA RME52C26.
[13] KINNEY G R,ABRAMSON A,SLOOP J L.Internal film cooling experiments with air-stream temperature to 2000 in 2- and 4-inch diameter horizontal tubes[R].NASA 1087.
[14] SHINE S R,KUMAR S S,SURESH B N.Influence of coolant injector configuration on film cooling effectiveness for gaseous and liquid film coolants[J].Heat and Mass Transfer,2012,48(5):849-861.
[15] 加洪.液体火箭发动机结构设计[M].任汉芬,颜子初,译.北京:宇航出版社,1992.
[16] YU Y,SCHUFF R,ANDERSON W.Liquid film cooling using swirl in rocket combustors[EB/OL].https://www.semanticscholar.org/paper/Liquid-Film-Cooling-Using-Swirl-in-Rocket-Yu-Schuff/865ff58c75f7823b430febafc37dfc001b
360b8c,2004.
[17] WARNER C F,GUINN G R.An experiment study of liquid film cooling accomplished by dual slot injection[J].Journal of Spacecraft and Rockets,1966,3(10):1547-1549.
[18] VOLKMANN J,MCLEOD J,CLAFLIN S.Investigation of throat film coolant for advanced LOX/RP-1 thrust chambers[C]//27th Joint Propulsion Conference.Reston,Virigina:AIAA,1991.
[19] 林庆国.空间轨控发动机高效燃烧室仿真与试验研究[D].长沙:国防科学技术大学,2015.
[20] KNAB O,PRECLIK D,ESTUBLIER D.Flow field prediction within liquid film cooled combustion chambers of storable bi-propellant rocket engines[C]//34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virigina:AIAA,1998.
[21] GORDON S,MCBRIDE B.Computer program for calculation of complex chemical equilibrium compositions[R].NASA 1311.

Memo

Memo:
-
Last Update: 1900-01-01