Inlet Flow Distortion in Turbomachinery

Abstract

A single stage axial compressor with distorted inflow is studied. The inflow distortion occurs far upstream and may be a distortion in stagnation temperature, stagnation pressure or both. The blade rows are modelled as semi-actuator disks. Losses, quasi-steady deviation angles, and reference incidence correlations are included in the analysis. Both subsonic and transonic relative Mach Numbers are considered. A parameter study is made to determine the influence of such variables as Mach Number and swirl angle on the attenuation of the distortion.