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为了分析附面层抽吸流动控制对低雷诺数下压气机特性的影响,本文采用数值方法模拟了低雷诺数下附面层组合抽吸方案对NASA Rotor 37跨音速压气机性能和稳定性的影响特点及作用机理。通过在该压气机转子叶片吸力面和机匣上分别设计附面层抽吸槽,探讨了组合抽吸方案对低雷诺数下(H=20km)压气机性能和稳定性的影响。结果表明:采用组合抽吸方案后,压气机峰值效率提高约1.3%;压气机最大增压比提高约2.5%;压气机转子的近失速点流量减小约14.6%。进一步分析作用机理发现,组合抽吸槽有效抑制了附面层径向涡向叶顶的运动和聚集,使叶顶附面层分离区减少约70%从而有效改善了压气机的流场特性。
In order to analyze the influence of surface suction flow control on the characteristics of the compressor at low Reynolds number, a numerical simulation of the performance and stability of the NASA Rotor 37 transonic compressor at low Reynolds number Impact characteristics and mechanism of action. The effect of the combined suction scheme on the performance and the stability of the compressor at low Reynolds number (H = 20km) was discussed by designing the suction layer on the suction side and the casing of the compressor rotor blade respectively. The results show that the peak efficiency of the compressor is increased by about 1.3%, the maximum turbocharger ratio of the compressor is increased by about 2.5%, and the flow near the stall point of the compressor rotor is reduced by about 14.6%. The mechanism of action is further analyzed. It is found that the combination of suction slots effectively restrains the movement and accumulation of the radial vortices on the top of the stratum, and reduces the separation area of the stratosphere by about 70%, which effectively improves the flow field characteristics of the compressor.