Abstract: In order to analyze the influence of inflow distortion on flutter characteristics of gas turbine compressors, an inlet total pressure model with radial distortion was established. Based on the influence coefficient method, the effects of radial inflow total pressure distortion with different phases and distortion intensities on the flow field characteristics and aeroelastic stability of compressors were studied. Results show that the radial inflow total pressure distortion with phase angles of 90° and 180° will increase the minimum value of aerodynamic damping under dangerous conditions, and the aeroelastic stability is improved. The radial inflow total pressure distortion with phase angle of 180° can improve the aeroelastic stability of the compressor at all inter blade phase angles. However, the radial inflow total pressure distortion with phase angles of 0° and 270° will increase the risk of compressor flutter, which should be avoided.