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.
Effects of a Skewed Inlet Boundary Layer on the Aerodynamic Performance of a Stator-Hub Equivalent High-Turning Compressor Cascade
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Bode, C, Hoffmann, J, & Stark, U. "Effects of a Skewed Inlet Boundary Layer on the Aerodynamic Performance of a Stator-Hub Equivalent High-Turning Compressor Cascade." Proceedings of the ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. Volume 2A: Turbomachinery. Seoul, South Korea. June 13–17, 2016. V02AT37A006. ASME. https://doi.org/10.1115/GT2016-56087
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