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Responses of an axial compressor isolated rotor\udblade row to various inlet distortions have been investigated utilizing\udcomputational fluid dynamic technique. Distortions have been imposed by five\udscreens of different geometries, but with the same blockage ratio. These\udscreens were embedded upstream of the rotor blade row. Flow fields are\udsimulated in detail for compressor design point and near stall conditions.\udPerformance curves for distorted cases are extracted and compared to the\udundisturbed case. Flow simulations and consequent performance characteristics\udshow that the worst cases belong to non-symmetric blockages, i.e., those of\udpartial circumferential configurations. These cases produce the largest wakes\udwhich can disturb the flow, considerably. Superior performances correspond to\udthe inner and outer continuous circumferential distortion screens. Since,\udthey produce no significant disturbances to the main flow in comparison to\udthe non-symmetric screens

Performance of a Low Speed Axial Compressor Rotor Blade Row under Different Inlet Distortions