航天推进技术研究院主办
[1]张 锋,仲伟聪,张魏静.壁厚对空间小推力发动机喉部壁温的影响[J].火箭推进,2011,37(06):34-37.
ZHANG Feng,ZHONG Wei-cong,ZHANG Wei-jing.Effect of wall thickness on throat wall temperature of space small thrust engines[J].Journal of Rocket Propulsion,2011,37(06):34-37.
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ZHANG Feng,ZHONG Wei-cong,ZHANG Wei-jing.Effect of wall thickness on throat wall temperature of space small thrust engines[J].Journal of Rocket Propulsion,2011,37(06):34-37.
壁厚对空间小推力发动机喉部壁温的影响
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
37
期数:
2011年06期
页码:
34-37
栏目:
研究与设计
出版日期:
2011-12-15
- Title:
- Effect of wall thickness on throat wall temperature of space small thrust engines
- 文章编号:
- 1672-9374(2011)06-0034-04
- Keywords:
- wall thickness; small thrust engine; throat wall temperature
- 分类号:
- V430-34
- 文献标志码:
- A
- 摘要:
- 介绍了空间小推力发动机通常采用的冷却方式及降低推力室喉部壁温的常用方法，分析了通过增加壁厚降低喉部壁温的可能性。通过简化模型，对不同壁厚下的喉部壁温进行了计算，计算结果表明，适当增加壁厚可以起到降低喉部壁温的作用。
- Abstract:
- The frequently-used cooling modes for spaceborne small thrust engines and ways usually-used to reduce the throat wall temperature of the thrust chamber are introduced. The possibility of reducing the throat wall temperature by increasing the wall thickness is discussed. The throat wall temperature under the condition of different wall thickness is calculated by simplifying the model. The results show that the throat wall temperature could be reduced by increasing the wall thickness properly.
参考文献/References:
[1]STECHMAN R C. Film cooling design criteria for small rocket engines, AIAA 68-617 [R]. USA: AIAA, 1968.
[2]GRISSON W M. Liquid film cooling in rocket engines, AD-A234 288 [R]. USA: AD, 1991.
[3]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.
[4]刘国球. 液体火箭发动机原理[M]. 北京: 中国宇航出版社. 1993.
[5]杨世铭, 陶文铨. 传热学[M]. 北京: 高等教育出版社. 1998.
备注/Memo
收稿日期：2011-05-07；修回日期：2011-07-17
基金项目：总装备部预研项目（2009AA7020510）
作者简介：张锋（1981—），男，工程师，研究领域为液体火箭发动机传热技术
更新日期/Last Update:
1900-01-01