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[1]吴东波,李家文,常克宇.GH2/GO2涡流冷却推力室设计与数值计算[J].火箭推进,2010,36(05):17-22.
　WU Dong-bo,LI Jia-wen,CHANG Ke-yu.Design and numerical calculation of GH2/GO2 vortex-cooled combustion chamber[J].Journal of Rocket Propulsion,2010,36(05):17-22.
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GH2/GO2涡流冷却推力室设计与数值计算

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 36 期数: 2010年05期 页码: 17-22 栏目: 研究与设计 出版日期: 2010-10-15
Title:
Design and numerical calculation of GH2/GO2 vortex-cooled combustion chamber
文章编号:
(2010)05-0017-06
作者:
吴东波1; 李家文1; 常克宇2
1 北京航空航天大学 宇航学院，北京 100191；2 西安航天动力研究所，陕西 西安 710100
Author(s):
WU Dong-bo1;  LI Jia-wen1;  CHANG Ke-yu2
1 School of Astronautics，Beijing Univ. of Aeronautics and Astronautics，Beijing 100191，China
关键词:
涡流冷却; 数值仿真; 双向涡流; 壁面温度; 燃烧效率
分类号:
V434
文献标志码:
A
摘要:
涡流冷却是一种新型液体火箭发动机推力室冷却技术。采用该技术可以简化推力室结构、降低成本，并可提高系统可靠性。对涡流冷却推力室进行了初步设计，并采用PDF非预混燃烧模型和DO辐射模型对所设计的推力室进行了数值仿真。根据计算结果：推力室内部形成了双向涡流；推力室圆筒段壁面温度低于760 K；在考虑辐射条件下，推力室圆筒段壁面温度平均升高约140 K，最高温度低于900 K；涡流冷却技术是可行的，但目前存在燃烧效率相对较低的问题。
Abstract:
Vortex cooling is a new type of thrust chamber cooling technology for the liquid rocket engine. This technology can simplify the thrust chamber structure, reduce cost and increase system reliability. In this paper, preliminary design of a vortex cooling based thrust chamber is performed. The numerical simulation of the designed thrust chamber is made by adopting PDF non-premixed combustion model and DO radiation model. The result shows that a bidirectional vortex is formed in the internal of thrust chamber and the wall temperature in the cylinder section of the thrust chamber is lower than 760 K. The average temperature of the cylinder wall is increased about 140 K but the maximum temperature is lower than 900 K while considering the radiation effect. Therefore, the technology of vortex cooling is feasible, but at the present the combustion efficiency is relatively low.

参考文献/References:

[1]CHIAVERINI M J, MALECKI M J. Vortex combustion chamber development for future liquid rocket engine applications, AIAA 2002-4149[R]. USA: AIAA,2002. [2]FANG Dianqi, MAJDLANI Joseph. Hot flow model of the vortex-cooled wall liquid rocket, AIAA 2003-5055[R]. USA: AIAA, 2003. [3]MAJDLANI Joseph, FANG Dianqi. On the bidirectional vortex and other similarity solutions in spherical geometry,AIAA 2004-3675[R]. USA: AIAA, 2004. [4]唐飞, 李家文, 常克宇. 涡流冷却推力室中涡流结构的分析与优化[J]. 推进技术, 2010, 31(2): 165-169. [5]KARGAR Mahdi Msc, SAIDI Mohammad Hassan. Exper-imental investigation of heat transfer modes in vortex combustion engines, AIAA 2007-5586[R]. USA: AIAA, 2004. [6]MARTIN J. CHIAVERINIi, J. ARTHUR Sauer, et al. La-boratory characterization of vortex-cooled thrust chamber for methane/O2 and H2/O2, AIAA 2005-4131[R]. USA: AIAA, 2005. [7]周庭宇, 鲁雪生. 液氧过冷用热交换器的热力设计[J]. 低温工程, 2007 (3): 35-39. [8]栾叶君, 孙纪国, 田昌义, 等. 氢氧推力室再生冷却内壁故障分析[J]. 火箭推进, 2006, 32(5): 21-25. [9]滑利辉, 田维平, 甘晓松, 等. 喉栓式推力可调发动机喷管流场数值模拟[J]. 固体火箭技术, 2008, 31(4): 344-349. [10]陈建华, 杨宝庆, 周立新, 等. 人为粗糙度强化换热机理分析及效果评估[J]. 火箭推进, 2004, 30(4): 4-8.

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备注/Memo

收稿日期：2010-０9-08；修回日期：2010-09-1７
基金项目： 国家863资助项目（2009AA7020515）
作者简介： 吴东波（1985—），男，硕士研究生，研究领域为液体火箭发动机设计及数值仿

更新日期/Last Update: 1900-01-01