摘要
概要介绍了某型航空发动机燃烧室出口温度的2种计算方法,结合发动机试车数据对采用2种计算方法得到的结果进行了对比分析。结果表明:采用涡轮流量法计算某型发动机燃烧室温度的结果比采用压气机特性法得到的计算结果更接近实际结果。
Two calculation methods for combustor outlet temperature of an aeroengine were described. The calculation results were analyzed comparatively combining the test data, The results show that the combustor temperature calculated by the turbine flow method is more practical than results calculated by the compressor characteristics method.
出处
《航空发动机》
2009年第5期1-3,共3页
Aeroengine
关键词
燃烧室
出口温度
压气机特性法
涡轮流量法
喉道面积
combustor
outlet temperature
compressor characteristics method
turbine flow method
throat area
