叶片表面粗糙度分布形式对压气机性能的影响

Comparison of Compressor Aerodynamic Performance in Different Blade Surface Roughness Distribution Forms

基于CFX商用软件,以NASA Stage35压气机叶型为研究对象,采用非均匀分布和等效均匀分布2种处理方法,对不同转速条件下压气机气动性能及内部流场进行了研究。研究结果表明:叶片表面粗糙度增加会引起压气机气动性能衰退,在100%设计工况中度腐蚀条件下,粗糙度增加使压气机峰值效率减小2.45%,压比减小0.56%,流量减小1.15%,温比升高0.24%;采用不同分布方式的粗糙表面计算得到的压气机内部流场差别较大,但总体性能差别较小,在仅需压气机整体参数时可以使用等效粗糙度来加快计算速度。

In order to grasp the influence of the surface roughness of the compressor blade on its aerodynamic performance,the CFX commercial software was used to study NASA Stage35 compressor.The non-uniform and equivalent uniform distribution were used to study the internal flow and performance.The results show that the increase of roughness will cause the aerodynamic performance of the compressor to decline.Under the condition of 100%design condition,the increase of roughness will reduce the peak efficiency of the compressor by 2.45%,the pressure ratio by 0.56%,the flow rate by 1.15%,and the temperature ratio increased by 0.24%.The internal flow field of the compressor obtained by the rough surface calculated by different distribution methods is quite different but the overall performance is similar.The equivalent roughness can be used to speed up the calculation,only the overall parameters of the compressor are needed.