关键词: 多元燃料发动机;火箭发动机燃烧室;传热;计算

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.

Key words: Multifuel engine;Rocket combustion chamber;Heat transfer;Computation