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[1]任加万,谭永华.燃烧室缝槽气膜冷却方案研究[J].火箭推进,2007,33(06):28-33.
　Ren Jiawan,Tan Yonghua.Investigation on the structure scheme of slot air film cooling combustion chamber[J].Journal of Rocket Propulsion,2007,33(06):28-33.
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燃烧室缝槽气膜冷却方案研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 33 期数: 2007年06期 页码: 28-33 栏目: 研究与设计 出版日期: 2007-12-28
Title:
Investigation on the structure scheme of slot air film cooling combustion chamber
作者:
任加万；谭永华；
西安航天动力研究所；航天推进技术研究院陕西西安710100；陕西西安710100；
Author(s):
Ren Jiawan1;  Tan Yonghua2
1 Xi’an Aerospace Propulsion Institute, Xi’an 710100, China;2 Academy of Aerospace Propulsion Technology, Xi’an 710100, China
关键词:
冲压发动机; 燃烧室; 气膜冷却; 壁温计算
分类号:
V434.14
文献标志码:
A
摘要:
针对超音速飞行器冲压发动机高马赫数、长航时的特点,结合工程计算方法和设计思想,建立了燃烧室缝槽气膜冷却过程一维计算模型,详细研究了各主要因素对气膜冷却效果的影响,并给出了某型冲压发动机高温燃烧室缝槽气膜冷却结构参考设计方案。结果表明,通过改善结构布局,合理分配缝隙冷气流量,可以有效地提高气膜冷却效果、降低壁温,适应高温燃气参数分布对隔热屏的热防护要求。

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更新日期/Last Update: 1900-01-01