Abstract: Effects of rotating inlet distortion on the aerodynamic stability of compressor were carried out in a 2-stage low speed compressor.The results show that the rotating screen in the upstream has great impact on the aerodynamic stability and total static pressure rise ratio of the compressor.When the rotating screen rotates at a different direction with the compressor,the pressure rise ratio and flow coefficient of stable boundary point vary little.If both have the same rotation direction,the speed of the rotating screen has big effect on both of the stability and the pressure rise ratio,especially between 40～60 percent of rotor speed.Through analysis of the variation of amplitude of characteristic frequency,it's concluded that the rotating stall induced by the low-total-pressure area produced by rotating screen will appear in the compressor.If the mass flow continues to decrease,the compressor will enter into natural rotating stall state.The experimental results of stall inception process reveal that the rotating inlet distortion can't affect the stall inception of the compressor.