The paper reports on numerical investigations into the effects of inlet boundary layer skew on the aerodynamic performance of a low aspect ratio, high turning compressor cascade. The cascade geometry corresponds to the hub section geometry of a low aspect ratio stator of a highly loaded single-stage axial-flow low-speed compressor (fan). The skewed cascade flow simulates the reenergized stator hub flow and brings about a much better performance with inlet skew than without. However, the performance improvements caused by a skewed inlet boundary layer decrease with increasing inlet angle.

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