级环境下叶轮前缘倾角对离心压气机性能的影响

Impact of Leading Edge Angle of Impeller on Centrifugal Compressor Performance in Multistage Environment

对某船用离心压气机进行了级环境下的气动性能仿真分析,结果表明,原方案中叶轮进口处能量损失过大,致使叶轮内效率下降过快,不满足要求.为此,针对性提出叶片前缘倾的两种优化方案.研究表明,叶轮前缘倾角对离心压气机级的气动性能影响较大,每一个结构确定的叶轮都有一个最优的前缘倾角,该倾角可以有效改善气流在流道内的流动情况,明显减小进口处的能量损失,从而使压气机的整级性能得到提高.

Numerical analysis of a marine centrifugal compressor in multistage environment was carried out. The results show that the energy loss at the impeller inlet of prototype model is rather big, resulting in a fast drop of the impeller efficiency. In the present thesis, two optimization schemes of leading edge angle of the impellers were proposed,and the numerical results show that the angle has a greater influence on the aerodynamic per- formance of the centrifugal compressor. It also indicates that there is an optimal leading edge angle for every impeller, which can improve effectively internal flow field of the compressor and reduce significantly energy loss at the impeller inlet and improve compressor performance in multistage improved.