摘要
本文对几种发动机的冷却作了分析比较,指出使用铜锆合金是高压大热流发动机的必然要求.对大推力氢氧烃三组元试验发动机燃烧室的传热分析表明:热流仅相当于相同推力氢氧双组元发动机的1/3～1/2,热壁温低于800K,完全满足设计要求,但流阻较大,对氢泵不利.
The heat transfer analysis on several rocket engines has completed in this paper.It is inevitable for copper-zirconium alloy to be used in hight pre- ssure great heat flux rocket engines. After analyzing the hydrogen-oxygen-hydrocarbon tripropellant rocket engine, we recognized that the heat flux is 1/3 to 1/2 that of hydrogen-oxygen propellant rocket engine with the same thrust.The gas-side wall temperatures satisfy completely the design request which are lower than 800K.But the pressure drop is so large as unfavourable to the hydrogen pump.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1990年第5期30-34,共5页
Journal of Propulsion Technology
关键词
多元燃料
火箭发动机
燃烧室
传热
Multifuel engine, Rocket combustion chamber, Heat transfer, Computation
