航天推进技术研究院主办
[1]宣智超,刘中祥,齐 戎.膨胀循环发动机推力室传热优化[J].火箭推进,2012,38(06):8-15.
XUAN Zhi-chao,LIU Zhong-xiang,QI Rong.Heat transfer optimization of thrust chamber in expansion cycle engine[J].Journal of Rocket Propulsion,2012,38(06):8-15.
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XUAN Zhi-chao,LIU Zhong-xiang,QI Rong.Heat transfer optimization of thrust chamber in expansion cycle engine[J].Journal of Rocket Propulsion,2012,38(06):8-15.
膨胀循环发动机推力室传热优化
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
38
期数:
2012年06期
页码:
8-15
栏目:
研究与设计
出版日期:
2012-12-15
- Title:
- Heat transfer optimization of thrust chamber in expansion cycle engine
- 文章编号:
- 1672-9374(2012)06-0008-08
- Keywords:
- expansion cycle engine; thrust chamber; enhancement structure of heat transfer; heat transfer optimization
- 分类号:
- V434+.34
- 文献标志码:
- A
- 摘要:
- 针对膨胀循环发动机推力室身部燃气侧的内壁增强换热结构和冷却剂侧的冷却通道结构这两个影响推力室身部换热最关键的结构分别进行多种结构下的数值模拟对比。通过分析各结构的模拟结果，得到了能够合理提高推力室身部换热能力的内壁加肋结构和圆柱段冷却通道深宽比的结构特征。
- Abstract:
- To further enhance the heat transfer capacity while maintaining the pressure drop of the cooling channels and gas wall temperature in control is one of the key technologies in the design of advanced expander cycle engine. Numerical simulation of inner wall heat transfer enhancement structure at the hot-gas side of thrust chamber and the cooling channel structure at the coolant side was made in this paper. The two structures are the most important ones which affect on the thrust chamber heat transfer. By analyzing the numerical simulation results of each structure, the inner structure with ribs which can enhance the heat transfer capacity of the thrust chamber reasonably and the structure characteristics which can improve depth-to-width ratio of cooling channel at the cylindrical section were obtained.
参考文献/References:
[1]朱森元. 氢氧火箭发动机及其低温技术[M]. 北京: 国防工业出版社, 1995.
[2]孙纪国. 膨胀循环发动机技术现状及其进展[J]. 导弹与航天运载技术, 2001 (2): 51-57.
[3]TOMSIK T, VERES J P. RL10A-3-3A rocket engine model-
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备注/Memo
收稿日期：2012-06-11；修回日期：2012-08-14
基金项目：国家863项目（2009AA7020512）
作者简介：宣智超（1986—），男，硕士，研究领域为液体火箭发动机推力室设计
更新日期/Last Update:
1900-01-01