高压自燃双组元液体火箭发动机燃烧模型

A COMBUSTION MODEL FOR THE HIGH-PRESSURE LIQUID HYPERGOLIC BIPROPELLANT ROCKET ENGINE

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

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

摘要:

本文提出了一个高压自燃双组元液体火箭发动机稳态燃烧计算模型.文中报告了特种发动机燃烧室压力、混合比、推进剂喷注温度和喷注器结构对燃烧过程影响的计算及分析结果.各种参数影响规律与实际发动机试验结果符合很好.

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.