| Citation: | MAO Xiaochen, WANG Yunyu, CHEN Xuan, et al. Effect of end-slot based on the incoming flow momentum on the corner separation of compressor cascade[J]. Journal of Aerospace Power, 2025, 40（8）：20230286 doi: 10.13224/j.cnki.jasp.20230286
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To control the corner separation in subsonic compressor cascade, an incoming flow momentum-based slotted cascade was designed through parametric study, and its flow control mechanism and adaptive capabilities under low cascade solidity were investigated. The results showed that the slotted cascade can effectively inhibit the corner separation. Especially the control effect was remarkable on the corner stall at the positive incidence angles. In addition to reducing the total pressure loss, the overall blade load and diffusion capacity were also improved. However, the control mechanisms of the slotted cascade varied for different separation forms. For the weak corner separation form, the total pressure loss within 0%—25% blade span was reduced mainly by eliminating the concentrated shedding vortex, while for the corner stall form the total pressure loss within 0%—40% blade span was greatly reduced due to the weakening of the separation vortex near the blade suction surface. Moreover, compared with the slotted cascade at the design solidity (1.82), the performance gain of the slotted cascade with a lower solidity was further enhanced. For a slotted cascade with the solidity of 1.33, its total pressure loss was reduced by an average of 29.53% and the static pressure rise coefficient was increased by an average of 26.06% within the range of full incidence angles. Therefore, the design solidity can be further reduced for an end-slotted cascade without reducing the cascade performance, indicating that the end-slotted cascade had a significant potential to improve the thrust-to-weight ratio of aero-engines.
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