Abstract
AbstractProgressing advance concerning acquiring higher pressure ratio in an aeroengine compressor has been achieved, which attracts much attention in recent years. Distortion at the flow entrance creates deterioration in the performance of aerodynamics and thermodynamics in transonic compressors, which usually leads to unsteady flow phenomena such as surge and rotating stall. This paper focuses on the investigation of the non-uniform inlet flow field in the tip and hub region of a compressor rotor blade, and radial pressure distortion is paid main attention in this work. The results show that non-uniform flow entrance condition causes deteriorator impacts on the stability of the axial flow compressor. Furthermore, hub radial pressure distortion alleviates the occurrence of unsteady phenomena presented by smaller surge flow rate than clean flow entrance condition.KeywordsInlet distortionAeroengine compressorCompressor stability
Published Version
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