| Citation: | XU Wenfeng, ZOU Shilong, SUN Dan, et al. Effect of suction leading edge vortex generator on characteristics of compressor cascade[J]. Journal of Aerospace Power, 2025, 40（5）：20230485 doi: 10.13224/j.cnki.jasp.20230485
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A compressor linear cascade was studied, and vortex generators were arranged near the suction leading edge of the end wall to improve the stator aerodynamic characteristic and control the corner separation. The effects of the vortex generators with different heights, lengths, and pitch positions on the corner separation flow and aerodynamic characteristics were studied by numerical simulation. The results showed that the suction leading edge vortex generator can generate the induced vortex near the end wall of the passage inlet, which inhibited the accumulation of low-energy fluids in the corner region, shifted the separation starting point backward, and narrowed the corner region along the pitch direction, thereby reducing the flow loss. The vortex generator should be arranged at the starting position of the corner separation. The control effect of the corner separation first increased and then decreased with the increase of the height of the vortex generator. With the increase of the chord of the vortex generator, it gradually decreased. As the arrangement position was far away from the suction, it first increased and then decreased. When the vortex generator was arranged at the boundary between the end wall recirculation region and the mainstream region, the chord was equal to 25% of the blade chord, and the height was equal to 2% of the blade height, the flow loss can be reduced by 10.3%.
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