Abstract
A method of using the blade end slot for passive control of the corner separation in a transonic compressor cascade was proposed. Because of the pressure difference between the pressure and suction sides, the blade end slot enables one to induce jet flow into the corner region, thereby restraining the corner separation in transonic cascade. The effect and mechanism of the blade end slot on the performance of the compressor cascade at different incidence angles were investigated numerically. The results demonstrate that, at smaller incidence angle, high-speed jet flow through the blade end slot can destroy the ring vortex in corner region, thereby reducing the corner separation, improving the performance of the cascade; at larger incidence angle, the jet flow can no longer destroy the ring vortex, but still re-energized the low-momentum fluid in the corner region, suppressed the corner separation, and the operation range was extended. The blade end slot reduced the total pressure loss coefficient by 11.6% at 0° incidence angle, and the operation range were increased from 2° to 3°.
Translated title of the contribution | Control of blade end slot on shock wave/boundary layer interaction of transonic cascade corner |
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Original language | Chinese (Traditional) |
Pages (from-to) | 1377-1387 |
Number of pages | 11 |
Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
Volume | 36 |
Issue number | 7 |
DOIs | |
Publication status | Published - Jul 2021 |