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为研究周向进口总压畸变对跨声速压气机气动稳定性影响的物理机制,采用整环三维定常数值计算方法对进口总压畸变条件下的NASA 37号转子进行求解。计算结果表明:周向进口总压畸变导致压气机稳定裕度大幅降低,设计转速时稳定裕度仅为均匀进气时的59%;畸变区与转子旋转速度相同时,位于畸变区的转子叶片进气速度、压力较小,当压气机工作点接近稳定边界时,该区域的叶片会出现叶尖泄漏流前缘溢流和尾缘倒流的现象,同时叶尖区域出现严重的吸力面附面层分离,叶尖泄漏流和吸力面附面层分离共同导致压气机失稳;周向进口总压畸变不会改变失稳的始发位置,但会影响失稳的原因。
In order to study the physical mechanism of the total pressure distortions on the aerodynamic stability of transonic compressor, a three-dimensional finite element method was used to solve the NASA rotor 37 with total pressure distortion. The calculation results show that the total pressure distortion in the circumferential inlet leads to a substantial decrease in the compressor’s stability margin, and the design margin is only 59% of that in the uniform intake. When the distortion zone and the rotor rotate at the same speed, When the operating point of the compressor is close to the stable boundary, the leading edge leakage flow and the tailing backflow of the tip leakage flow will appear in the blades of the area, and the serious suction surface attachment appears in the tip area The layer separation, the tip leakage flow and the suction surface separation layer together lead to the instability of the compressor. The total pressure distortion in the circumferential inlet will not change the origin of instability, but it will affect the cause of instability.