Abstract:

The detailed experimental study on compressor cascade with three kinds of blade tip winglets has been carried out in low speed condition. The endwall flow fields are measured by static pressure taps. And the outlet flow fields of the cascade are obtained by five-hole aerodynamic probe. The effect of the blade tip winglet on the flow filed, total pressure loss and the flow capacity of the cascade are analyzed in detail. The results show that the blade tip geometry significantly affects the tip clearance flow field. Compared to the conventional cascade without blade tip winglet, the total loss can be reduced by the suction-side winglet, and the outflow blockage is reduced. The pressure-side winglet has little advantages over the baseline tip in reducing the overall losses and improving the flow capacity of the cascade. The combined winglet tip can positively affect the aerodynamic filed of the cascade by reducing the overall losses and improving the flow capacity. The flow physics are explored in detail to explain the results.

Key words: compressor cascade, experimental study, tip clearance flow, vortex structure, blade tip winglet