弯掠前缘叶型对小型跨音速离心压气机性能的影响

Effect of Blade Leading Edge Sweep on the Performance of a Micro Transonic Centrifugal Compressor

为了探索提高跨音速离心压气机喘振裕度的方法,根据国外某型微型涡喷发动机压气机参数,设计了直纹面叶轮和弯掠前缘叶轮。利用Fine/Turbo分别对这两个叶轮进行CFD计算,对比叶轮内部流场及性能曲线,分析两种叶型对离心压气机喘振裕度的影响。结果表明,弯掠前缘叶型能有效的提高压气机喘振裕度并且改善叶轮出口流场。

To improve the surge margin of a transonic centrifugal compressor, a ruled surface impeller and a swept leading edge impeller are designed, based on the parameters of a foreign micro turbojet engine compressor. The two impellers are modeled by Fine/Turbo and the flow field and performance curves of the impellers are compared.Additionally, the effect of the two blade profiles on the surge margin of the centrifugal compressor is analyzed. The results show that a swept leading edge blade effectively improves the compressor surge margin and flow field in the outlet.