Experimental tests have been carried out to investigate the influence of inlet distortion on compressor stability margin in a low speed single stage research compressor.
在低速大尺寸单级压气机实验器上，实验研究了动态进气畸变对压气机稳定边界的影响。
2
A first order lagging equation is used to acount for dynamic effects. This model can simulate the compressor response to inlet temperature transients and find the critical stage.
该模型可以模拟进口温度（或压力）瞬变下压气机的逐级响应，寻找首先失速的关键级。
3
A stage - by - stage simulation method is introduced for analysis of inlet total pressure distortion effect on the multistage axial flow compressor characteristics.