摘要
根据台架试车试验的测量数据和部件的试验特性,分析了航空发动机压缩系统从全加力到小加力过渡态过程中压缩系统部件的工作点变化情况,给出了喘振裕度随时间的变化。结果表明:在该过渡态过程中,发动机参数有较大波动,风扇裕度不会减小,高压压气机的可调静子叶片角度偏开,导致裕度有所减小,涵道比有所增大。以上参数变化应该在压缩系统设计中给予考虑。
The operational behavior of compression system from full afterburning to half afterburning was analyzed with component experimental characteristics based on the test rigmeasurement data. The surge margin for time varying was given. The results show that the aereengine parameter is fluctuated largely, the fan surge margin is unchanged, the high pressure compressor surge margin is decreased with the variable stator opening and the bypass ratio is increased in the transition state. These parameters changes are considered in the compression system.
出处
《航空发动机》
2012年第3期38-41,共4页
Aeroengine
关键词
压缩系统
切断加力
过渡态
喘振裕度
航空发动机
compression system
cut off afterburning
transition state
surge margin
aeroengine
