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In this paper, the design for the mixed flow compressor is based on the results of a S2 through flow aerodynamic design program and a general arbitrary curved blade design method for axial, centrifugal/mixed compressors. Three different mixed flow compressors with different circulation distributions were studied. The results show that different circulation distributions should be utilized from blade hub to tip. For blade hub, more loading in posterior area should be chosen, while for blade tip more loading in frontal area of the blade is available. With this loading distribution, the separation flow in blade hub is controlled,along with the reduction of separation flow in blade tip. The performance of the mixed flow compressor can be boosted with a more homogeneous distribution of aerodynamic parameters from blade hub to tip, a more homogeneous flow field and a higher pressure recovery coefficient

The Aerodynamic Design and Investigation of Loading Distribution of a Mixed Flow Compressor