微型离心叶轮叶片进口角度对压气机性能影响

Effect of Inlet Angle of Minicentrifugal Impeller Blade on Performance of Centrifugal Compressor

为了研究离心叶轮叶片进口角度对离心压气机气动性能的影响,在叶片进口处设计5组不同叶顶弯曲角度和3组不同叶根倾斜角度的离心叶轮,实现了不同的叶轮叶片进口角度,采用计算流体力学(CFD)方法对不同叶型的离心压气机在设计工况下的流场进行了仿真分析。研究结果表明:对于跨声速微型离心式压气机,增大进口叶片叶顶弯曲角度可提高压气机的等熵效率和压比。当叶顶弯曲角度从50°增大到70°时,离心压气机的压比增大17%,等熵效率增大22%,进口气流角减小而出口气流角增大。增大叶根倾斜角度压气机出口压力比降低2.4%,等熵效率降低3.9%。叶片进口弯曲角度是提高其等熵效率、压比的一种有效方法,该分析方法为合理选择叶片前缘角度提供了参考,为跨音速微型离心压气机的设计提供了借鉴。

In this study,the effect of the inlet angle of a centrifugal impeller blade on the aerodynamic performance of a centrifugal compressor was investigated.Five groups of impeller bending angles and three groups of blade root inclination angles at the blade inlet of the centrifugal impeller were designed to obtain different blade inlet angles of the impeller.The computational fluid dynamics method was used to simulate and analyze the flow fields of centrifugal compressors with different blade shapes under design conditions.The results showed that for transonic microcentrifugal compressors,an increase in the inlet blade tip bending angle increases the isentropic efficiency and pressure ratio of the compressor.When the blade tip bending angle increases from 50°to 70°,the pressure ratio of the centrifugal compressor increases by 17%,the isentropic efficiency increases by_(2)2%,the inlet airflow angle decreases,and the outlet airflow angle increases.Increasing the blade root inclination angle decreases the compressor outlet pressure ratio by_(2).4%and the isentropic efficiency by_(3).9%.The blade inlet bending angle is a critical parameter for increasing the isentropic efficiency and pressure ratio.This proposed analysis method provides a reference for rationally selecting the blade leading edge angle and designing transonic microcentrifugal compressors.