Effect of inlet guide vanes on response of an axial flow compressor to steady circumferential pressure distortions

An efficient calculation procedure was established which allows the rapid computation of the total pressure distortion development through any combination of rotors,stators and clearances.The predictions of response of an axial flow compressor rotor,stator and axial clearance to steady circumferential pressure distortion were presented with and without inlet guide vanes.The effects of inlet guide vanes on response of an axial flow compressor to steady circumferential pressure distortion were found.By using inlet guide vanes,great attenuation of total pressure distortion and static pressure distortion,weak incidence angle changes and low total temperature distortion production through the rotor were obtained.It is apparent that the effective improvement in stall margin can be achieved with inlet guide vanes under conditions of inlet circumferential pressure distortions.Appropriate design of inlet guide vanes for multistage axial flow compressors should ensure that the axial compressors have high tolerant to inlet pressure distortions.