A new model is presented for calculating the end-wallboundarylayer and its blade force defect inside the axial compressor cascade, based on theoretical analysis.
By using of numerical simulation, the effect of applying boundarylayer suction on end-wall to the aerodynamic performance for a van with a high-turning Angle and meridional divergence was discussed.
针对某大折转角子午扩张型导叶,通过数值模拟,讨论了端壁附面层抽吸对叶栅性能的影响。
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The result showed that for the cascade with larger separation, perfect effects can be obtained by applying boundarylayer suction on the end-wall near suction surface.