Numerical simulation for applying boundary layer suction on end-wall to improve the aerodynamic performance of cascade

By using of numerical simulation, the effect of applying boundary layer suction on end-wall to the aerodynamic performance for a van with a high-turning angle and meridional divergence was discussed. The result showed that for the cascade with larger separation, perfect effects can be obtained by applying boundary layer suction on the end-wall near suction surface. The separation configuration of the flow field will be changed by end-wall suction. The flow separation at the corner will be restrained and also the separation on the suction surface will be delayed or depressed. Therefore the blade loading along the blade height will be enlarged. Furthermore the flow loss will be decreased and the flow field will be distributed uniformly along radial.