Investigation of improving the aerodynamic performance in highly-loaded compressor cascade by boundary layer suction holes

The detailed experiment and numerical simulation were carried out to analyze the effects of boundary layer suction hole on loss control of highly-loaded large bending angle compressor cascade suction surface. In experiment, the exit aerodynamic parameters were measured by five-hole aerodynamic probe. Experimental and numerical results come to similar conclusions. The results show that boundary layer suction can effectively improve aerodynamic performance of compressor cascade, reduce the loss of flow. High-loss area at the exit section diminishes and get close down to the end-wall. The loss decreases obviously in the region of middle blade, but not in the end-wall region. When using big-hole suction, suction volume increases at the same time may result in loss increase in the region nearly 20% blade-high from the end walls.