关键词: 液体推进剂火箭发动机;燃烧效率;燃烧室;喷射;温度分布

Abstract: A steady-state combustion computer model for the high-pressure liquid hyper-golic bipropellant rocket engine is presented in this paper.The results of the calculation and the analysis of effects of combustion chamber pressure,mixture ratio,propellant injection temperature and injector type on the combustion processes are reported.The computational results are in good agreement with the experiment.

Key words: Liquid propellant rocket engine;Combustion efficiency;Combustion chamber;Injection;Temperature distribution