航天推进技术研究院主办
[1]唐亮,王凯,刘计武,等.液膜冷却对火箭发动机燃烧效率的影响[J].火箭推进,2023,49(03):69-75.
TANG Liang,WANG Kai,LIU Jiwu,et al.Influence of liquid film cooling on combustion efficiency of rocket engine[J].Journal of Rocket Propulsion,2023,49(03):69-75.
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TANG Liang,WANG Kai,LIU Jiwu,et al.Influence of liquid film cooling on combustion efficiency of rocket engine[J].Journal of Rocket Propulsion,2023,49(03):69-75.
液膜冷却对火箭发动机燃烧效率的影响
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
49
期数:
2023年03期
页码:
69-75
栏目:
目次
出版日期:
2023-06-25
- Title:
- Influence of liquid film cooling on combustion efficiency of rocket engine
- 文章编号:
- 1672-9374(2023)03-0069-07
- 分类号:
- V434+.3
- 文献标志码:
- A
- 摘要:
- 液膜冷却对发动机热防护和性能均有重要的影响,为了研究不同液膜注入条件对燃烧效率的影响,开展了燃烧室液膜冷却热试试验研究。试验中改变了射流流量、冷却孔的数量、射流倾角,并测量了两排分别位于正对冷却孔位置和两冷却孔之间位置的燃烧室壁温,计算了不同工况下的燃烧效率。结果表明:推力室点火后,液膜的注入会压低温度曲线上升的斜率; 在热试实验研究中,在相同的液膜流量下,不同的液膜注入方式并未对燃烧效率产生显著的规律性影响; 头部混合比在3.6附近时,液膜流量占燃烧室总流量的百分比每提高2.3%,则燃烧室的燃烧效率降低约1%。
- 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%.
参考文献/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.
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备注/Memo
收稿日期:2022-07-31; 修回日期:2022-08-31
基金项目:国家自然科学基金项目(11502186)
作者简介:唐亮(1991—),男,博士,研究领域为燃烧与传热。
更新日期/Last Update:
1900-01-01