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基于计算流体动力学和数值优化算法,研究了一种压气机叶型优化设计方法.以入口马赫数为0.7的高亚声速轴流压气机叶型为研究对象,采用拉丁超立方实验法选取优化变量并构建了考虑攻角特性的目标函数,通过引入Gamma-Theta转捩模型,考虑了附面层转捩的影响,最终获得了可以有效改善攻角特性和降低总压损失的高亚声速轴流压气机优化叶型.计算结果表明:优化叶型可以显著降低入口马赫数为0.2~0.8时+4°和-4°攻角的总压损失,使设计工况(入口马赫数为0.7)下的低损失攻角增加4°以上,优化叶型最佳稠度降低20%并改善低雷诺数时叶栅的流动特性.
Based on computational fluid dynamics (CFD) and numerical optimization algorithms, a method for optimal design of compressor blades is studied. Taking the high subsonic compressor with an inlet Mach number of 0.7 as the research object, the Latin hypercube experiment method is adopted to select and optimize The objective function considering the characteristics of angle of attack is constructed. By introducing the Gamma-Theta transition model, the influence of the transition of the surface layer is considered. Finally, the high subsonic speed axis which can effectively improve the angle of attack characteristics and reduce the total pressure loss The results show that the optimized blade can significantly reduce the total pressure loss at the entrance Mach number of 0.2 ~ 0.8 and at the attack angle of -4 ° and the attack angle of -4 ° so that the design conditions (entrance Mach number is 0.7) Under the low loss angle of attack increased more than 4 °, optimization of leaf shape the best consistency to reduce 20% and improve the low Reynolds number cascade flow characteristics.