In this paper, a time marching method is proposed to predict the propagation of steady inlet circumferential distortion through an axial flow compressor rotor (or stator). This method also adopt the “Semi-actuator disk” concept to replace the rotor. It is assumed that the flow fields outside of the disk are described by a set of ideal, compressible and unsteady quasi-linear partial differential flow equations. Furthermore, the unsteady response of rotor is also taken into account. This method can be easily developed to a stage or extended to investigate the effect of transient disturbance on the stability of a compressor. Through numerical experiments, it has been found that distortion amplitude, rotation of the rotor, the chord length and especially the characteristic curves of the blade row have crucial effect on the attenuation behavior of the rotor.

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