Effects of End-Wall Taking Hole-Suction on Aerodynamic Performance of a Compressor Cascade

In order to uncover the effects of hole-suction on the aerodynamic performance of a compressor cascade,detail experimental research was carried out.The effects of taking hole-suction at different location in the endwall on the flow pattern,outlet loss contour and distribution of secondary flow vectors of the large turning cascade were obtained.As a result,flow filed of original cascade is changed while applying boundary layer suction.Suction before corner separation delays passage vortex happening and reduces the loss of original cascade.Suction after corner separation which is fully developed is not advised.As the total suction massflow is given,taking hole-suction may pronounce a better aerodynamic performance than taking slot-suction.