基于来流动量的叶根开槽对压气机叶栅角区分离的影响

To control the corner separation in subsonic compressor cascade， an incoming flow momentum-based slotted cascade was designed through parametric study and investigated for its flow control mechanism and adaptive capabilities under low cascade solidity. The results show that the slotted cascade can effectively inhibit the corner separation. Especially the control effect is 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 are also improved. However，the control mechanisms of the slotted cascade are different for different separation forms. For the weak corner separation form，the total pressure loss within 0%—25% blade span is reduced mainly by eliminating the concentrated shedding vortex， while for the corner stall form the total pressure loss within 0%—40% blade span is 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 is further enhanced. For a slotted cascade with the solidity of 1.33， its total pressure loss is reduced by an average of 29.53% and the static pressure rise coefficient is increased by an average of 26.06% in the range of full incidence angles. Therefore， the design solidity can be further reduced for an end-slotted cascade without reducing the cascade performance， which means that the end-slotted cascade has a significant potential to improve the thrust-to-weight ratio of aero-engines.