Effect of Total Pressure Distortion on Aerodynamic Stability of Compressor

An experimental investigation was performed to study the effect of tip and hub total pressure distortion on aerodynamic stability of axial compressor.The results show that stall cell appears at tip region first with uniform inlet flow.Compressor will stall earlier with tip total pressure distortion as a result of increasing the attack angle at tip region.On the other hand,hub total pressure distortion will reduce the attack angle at tip region,so will enhance the stability.Meanwhile,the three-dimensional diffusion characteristic of modal wave and stall cell will also be affected by the change of radial flow variables distribution.