关键词: 角区分离, 篦齿封严, 级间泄漏, 涡系结构, 引气射流结构

Abstract: In this study, the influence of the interstage sealing air-entraining jet structure at different positions and geometric structures on the aerodynamic performance of the compressor cascade is deeply explored. The effect and mechanism of the interstage sealing air-entraining jet on the vortex structure in the corner region of the compressor cascade under the conditions of variable incidence angle are analyzed. It is found that with the movement of the jet port to the trailing edge and the increase of the width and height of the jet port, the suppression effect of the air-entraining jet on the total pressure loss of the cascade increases first and then decreases. When the jet port is located at the starting of corner separation, the height is 20 % blade height and the width is 8 % chord length, the improvement effect is the best, and the total pressure loss can be reduced by 8.5 % compared with the prototype(ORI). In addition, the arrangement of the air-entraining jet structure under different incidence angle conditions reduces the influence range of the passage vortex pitchwise direction, but leads to the increase of the separation vortex height in different degrees. With the increase of the incidence angle, the suppression of the separation vortex in the pitchwise direction by the air-entraining jet structure increases first and then decreases, and the increase effect of the flow loss near the mid-span gradually weakens. For this reason, the improvement effect of the air-entrining jet structure on the cascade performance is first enhanced and then weakened. The best improvement effect is shown at 0 °, and significantly improve the aerodynamic performance of its high-load compressor cascade.

Key words: corner separation,, labyrinth seal,, interstage leakage,, vortex structure,, air-entraining jet structure