氢氧烃三组元发动机燃烧室传热、流阻初步分析

THE PRIMARY ANALYSIS ON HEAT TRANSFER AND PRESSURE DROP OF THE THRUST CHAMBER IN HYDROGEN-OXYGEN-HYDROCARBON TRIPROPELLANT ROCKET ENGINE

关键词:  多元燃料发动机  火箭发动机燃烧室  传热  计算

Key words:  Multifuel engine  Rocket combustion chamber  Heat transfer  Computation

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.

Abstract:

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.