关键词: 风扇;压气机;基元叶栅法+;双激波模型+;边界;雷诺数

Abstract: A method to calculate the multistage axial fan/compressor off-design performance was established.It can catch the nature of shock system,and has better accuracy of predicting the loss,owing to a dual-shock loss model suitable for high-speed flow.It is also able to estimate the effects of Reynolds number on the performance of fan/compressor,and the boundary stability of multistage fan/compressor in an extensive range of Reynolds number by means of maximum pressure rise potential.The method is flexible and reliable,validated by test results of three different compressors,such as high-pressure compressor,transonic fan and high bypass ratio fan/booster.Besides predicting the performance of a fan/compressor,it may as a tool of design and researching a fan/compressor in the case of lower Reynolds number.Thus it has an abroad engineering applications foreground.

Key words: Fan;Compressor;Element cascade method+;Dual-shock model+;Boundary;Reynolds number