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离心压缩机元件的气动设计通常是根据一个给定工况点设计其几何形状。如此设计的元件在该设计工况点一般能保持较好的气动性态，但当实际运行工况改变时，性能往往会恶化。本文将机翼的多点设计思想引入离心压缩机叶栅的优化设计，并应用遗传算法对这类多目标优化问题进行求解，希望由此获得在运行工况间能较好折中的叶栅型线设计。以离心压缩机扩压器叶栅为例，在两个给定设计工况下采用所提出的方法求解其最佳叶片型线。数值结果显示，方法是有效和可行的。
The aerodynamic design of centrifugal compressor components is usually based on a given operating point design geometry. Components designed in this way generally maintain a good aerodynamic behavior at this design point, but performance tends to deteriorate when the actual operating conditions change. In this paper, the multi-point design idea of the wing is introduced into the optimization design of centrifugal compressor cascades, and the genetic algorithm is used to solve this multi-objective optimization problem. It is hoped that the cascade with better compromise between operating conditions can be obtained. Line design. Taking centrifugal compressor diffuser cascade as an example, the proposed method is used to solve the optimal blade profile under two given design conditions. Numerical results show that the method is effective and feasible.