摘要
根据层板单元的热分析结果和层板发汗冷却推力室固有的结构特点,提出这种先进发动机冷却方案的设计原理和结构参数的计算公式,结合一台50kN发动机推力室喉部改再生冷却为发汗冷却的改形设计,分析其层板发汗冷却段喉部的设计方法和主要结构尺寸的计算结果。还比较了全再生冷却和发汗冷却两种冷却方式下发动机推力室的温度、热流密度和重量。对先进层板发汗冷却推力室的结构设计提供了参考。
According to the thermal analysis results of the platelet cell and the inherent characteristics of platelet transpiration cooling thrust chamber, the design principle and computational method of the advanced cooling project of rocket engine were brought forward. By the design to change the regeneration cooling into the transpiration cooling at the throat section of a 50 kN liquid rocket engine thrust chamber, the design method of the platelet transpiration cooling section and the calculation results of main geometrical dimension were all analyzed. The temperature, thermal flux and weight between the complete regeneration cooling thrust chamber and transpiration cooling thrust chamber were all compared. The content can be helpful for the design of the advanced platelet transpiration cooling thrust chamber.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2004年第4期316-319,共4页
Journal of Propulsion Technology
