全流量补燃循环发动机推力室再生冷却技术研究

汪小卫; 金平; 孙冰

全流量补燃循环发动机推力室再生冷却技术研究

北京航空航天大学宇航学院, 北京 100083

基金项目: 国家863基金(2005AA722040)

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出版历程
- 收稿日期: 2007-05-29
- 修回日期: 2007-10-01
- 刊出日期: 2008-05-28

Study on regeneratively-cooled technology of full-flow stage combustion thrust chamber

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 将层板式大高宽比、薄壁、弹性冷却内衬等新技术采用到全流量补燃循环发动机推力室再生冷却设计上,结合全流量发动机工作特点,建立了冷却通道准一维换热和二维数学模型,得到了推力室轴向热参数分布和危险截面冷却通道的温度场和应力场,得出了采用推力室再生冷却新技术相对于传统模式可以较大地降低推力室喉部内壁温、内衬最大等效应力和冷却压降,从而提高推力室寿命及发动机性能的结论,并初步设计出大推力全流量补燃循环发动机推力室再生冷却结构.
- 航空、航天推进系统 /
- 全流量补燃循环(FFSC)发动机 /
- 推力室寿命 /
- 再生冷却
Abstract: The full-flow stage combustion(FFSC) cycle engine may be applied in the next generation reusable launch vehicle.In order to meet the enhanced life of FFSCchamber,this paper employed some new technologies developed recently to the regeneratively-cooled thrust chamber for its design work.These technologies include formed platelet technology,high-aspect-ratio cooling passages and elastic cooling structure.While cooling models were established in consideration of the character of FFSCchamber,the modeling of applying these technologies to FFSCchamber was conducted.The results show that these methods can drastically reduce the temperature,the strain of hot-gas-side wall and the coolant pressure drop,and a regeneratively-cooled structure of the FFSCthrust chamber had been preliminarily designed.
- aerospace propulsion system /
- full flow stage combustion(FFSC) cycle engine /
- thrust chamber life /
- regeneratively-cooled

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参考文献(14)

[1]	Popp M,Schmidt G.Rocket engine combustion chamber design concepts for enhanced life[R].AIAA-96-3303,1996.
[2]	Giover R C,Kelley B A,Tischer A E.Studies and analyses of the space shuttle main engine[R].Marshall Space Flight Center,AL 35812.NASW-3737:SSME Failure Data Review Dianostic Survey and SSME Diagnostion Evaluation.SCD-SSME-TR-36-1.
[3]	Mathew J J,Nichols J T,Boyce W D,et al.Integrated powerhead demonstration:Full flow cycle development[R].Air Force Research Lab 4 Draco Edwards AFB,Aerojct PO Box 13222 Sacramento,William F.Sack,Boeing Defence & Space Group 6633 Canoga Ave Canoga Park,AFRL-PR-ED-TP-1998-003.
[4]	Davis J A,Campbell R L.Advantages of a full-flow staged combustion cycle engine system[R].Tokyo Japan:AIAA97-3318,July 6-9,1997.
[5]	Immich H,Kretschmer J,Preclik D.Thrust chamber technology developments for future launch vehicle liquid rocket engines[R].AIAA-2001-3544,2001.
[6]	Carlile J.An experimental investigation of high-aspect-Ratio cooling passages[R].AIAA-92-3154,1992.
[7]	Burkhardt W M,Hayes W A.Formed platelets for low cost regenreatively cooled rocket combuation chambers[R].AIAA-92-3526,1992.
[8]	Burkhardt W M,Tokin S W,Mueggenburg H H.Formed plateletliner concept for regeneratively cooled chambers[R].AIAA 90-2117.
[9]	Elam S K.Subscale hot-fire testing of a formed platelet liner[R].AIAA-93-1827,1993.
[10]	韩振兴,林文,张远君,等.液体火箭发动机铣槽推力室三维壁温分布计算[J].航空动力学报,1996,11(2):145-148.HAN Zhenxing,LIN Wen,ZHANG Yuaniun,et al.Calculation of the wall temperature for 3-D channels of a liquid rocket[J].Journal of Aerospace Power,1996,11(2):145-148.
[11]	Frohlich A,Popp M,Schmidt G,et al.Heat transfer characteristics of H2/O2-combustion chambers[R].AIAA-93-1826,1993.
[12]	刘国球.液体火箭发动机原理[M].北京:宇航出版社,1993:303-352.
[13]	华绍增,杨学宁.实用流体阻力手册[M].北京:国防工业出版社,1985.
[14]	Hua Shaozeng.Practical manual of the liquid on of high aspect ratio cooling channel designs for a rocket combustion chamber[R].AIAA-97-2913,1997.