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Certificating characteristics of stall and surge is an important work for engine airworthiness. Requirements and instructions of these characteristics are issued under CCAR 33.65. For stator cascade, the flow structure of corner separation region is complex. The separation can lead to highly loss in compressors and even cause corner stall and deterioration on cascade performance. This paper studied boundary layer suction on the suction surface and end wall to control the corner separation and eliminate corner stall to enhance the stability of the compressor. A total of six slot arrangements were investigated by CFD method. The results showed that using boundary layer suction can reduce passage total pressure loss and extend available attack angle of the cascade. Furthermore, through the analysis of the control effects, two groups of combination suctions are proposed to get better control effects

Control of Corner Separation to Enhance Stability in a Linear Compressor Cascade by Boundary Layer Suction