In order to study the effect of the trailing edge sweep angle of the centrifugal impeller on the aerodynamic performance of the centrifugal compressor, 6 groups of centrifugal impellers with different bending angles and 5 groups of different inclination angles were designed to achieve different impeller blade trailing edge angle. The computational fluid dynamics (CFD) method was used to simulate and analyze the flow field of centrifugal compressors with different blade shapes under design conditions. The research results show that for transonic micro centrifugal compressors, changing the blade trailing edge sweep angle can improve the compressor’s isentropic efficiency and pressure ratio. The pressure ratio of the compressor shows a trend of increasing first and then decreasing with the increase of the blade bending angle. When the blade bending angle is 45°, the pressure ratio of the centrifugal compressor reaches a maximum of 1.69, and the isentropic efficiency is 67.3%. But changing the inclination angle of the blade trailing edge has little effect on the isentropic efficiency and pressure ratio. The sweep angle of blade trailing edge is an effective method to improve its isentropic efficiency and pressure ratio. This analysis method provides a reference for the rational selection of the blade trailing edge angle, and provides a reference for the design of micro centrifugal compressors under high Reynolds numbers.

中文翻译：

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微型离心叶轮的后缘角对离心压缩机性能的影响

为了研究离心叶轮后缘扫掠角对离心压缩机空气动力性能的影响，设计了6组不同弯曲角度的离心叶轮和5组不同倾角的离心叶轮，以实现不同的叶轮叶片后缘角度。在设计条件下，采用计算流体动力学（CFD）方法对不同叶片形状的离心式压缩机的流场进行了仿真和分析。研究结果表明，对于跨音速微型离心压缩机，改变叶片后缘后掠角可以提高压缩机的等熵效率和压力比。压缩机的压力比呈现出随叶片弯曲角的增加先增大后减小的趋势。当叶片弯曲角为45°时，离心压缩机的压力比最大达到1.69，等熵效率为67.3％。但是，改变叶片后缘的倾斜角度对等熵效率和压力比几乎没有影响。叶片后缘的后掠角是提高其等熵效率和压力比的有效方法。该分析方法为合理选择叶片后缘角提供了参考，并为高雷诺数下的微型离心压缩机的设计提供了参考。但是，改变叶片后缘的倾斜角度对等熵效率和压力比几乎没有影响。叶片后缘的后掠角是提高其等熵效率和压力比的有效方法。该分析方法为合理选择叶片后缘角提供了参考，并为高雷诺数下的微型离心压缩机的设计提供了参考。但是，改变叶片后缘的倾斜角度对等熵效率和压力比几乎没有影响。叶片后缘的后掠角是提高其等熵效率和压力比的有效方法。该分析方法为合理选择叶片后缘角提供了参考，并为高雷诺数下的微型离心压缩机的设计提供了参考。