Effects of endwall boundary layer suction position on the flow field and load in a high-turning compressor cascade

Experimental investigation was carried out to study the effects of the boundary layer suction implemented close to the suction surface on the endwall on improving the aerodynamic performance of a compressor cascade with a large camber angle. The flow fields of the cascade and the static pressure by tapping on the cascade surfaces were measured, and the ink-trace flow visualization was also conducted. Experimental results show that the applied manner of boundary layer suction mainly affects the suction and endwall corner region and the load of the blade root redistribution after suction. Suction before the separation in endwall corner region happening delays the flow separation, decreases cascade losses, and improves the flow condition of the endwall region effectively. But suction after the separation has occurred even worsens the flow field and enhances the blending of the low energy fluid, and increases losses.