A method of examining inlet distortion for intensity of compressor blades was described.A CFD (computational fluid dynamics) modeling of entire compressor flowpath was conducted to analyze the pressure fluctuation on the rotor blades due to inlet total-pressure distortion.A finite element model of the blade was then used to analyze the modal frequencies and stress

providing information on the fatigue failure potential and sensitivity to the imposed distortion.Results show that circumferential total-pressure distortion not only causes the decrease of efficiency and stall margin of compressor

but also leads to nonuniformity of aerodynamic force of blades at different circumferential positions

producing an important influence on the blade intensity.