A method for monitoring of stage-pressurization characteristics of multistage axial flow compressors was developed to locate the specific compressor stages

where flow field was poorly matched at a given operating condition.The newly developed method was used to analyze rig-test data of a turbojet engine.The results show that

ill-matched compressor stages during engine speed transient could be located accurately.Then the method was successfully used to control on-off switching of the bleed valve of the test engine.It demonstrates that the method is promising in surge boundary detection

engine transient process control

and stage-level compressor flow control.