基于边界层分离控制的翼型优化设计方法

Numerical Optimization of Blade Profile Design

提出了不可压缩翼栅流动中最佳翼型的设计方法。将叶片间无黏流动和黏性流动的二维边界层设计统一到一般的最优化技术中 ,通过对翼型中线角度、厚度分布以及叶片安装角的控制来避免边界层的分离 ,而在大负荷时促进边界层分离点向翼型后缘推进。另外 ,在控制边界层分离点的同时 ,极小化边界层形式参数。以 NACA65 (0 8) 1 0和 NACA65 (1 2 ) 1 0翼型作为原始翼型对该方法进行了应用和讨论 。

A procedure for designing an optimal blade profile in incomp re ssible cascade flow is developed (compressors, turbine, and fans). It integrates the blade to blade inviscid flow and the two dimensional boundary layer viscous flow within a general optimization technique. The objective is, through the con trol of profile meanline angle and thickness distribution, as well as the blade stagger angle, to avoid the boundary layer separation, or precisely, to move the separation point obviously forward to the trailing edge in large load cases. Th e boundary layer incompressible form factor is minimized at the same time and se paration is controlled. Applications, by using NACA 65-(08)10 and NACA 65-(12) 10 profiles as starting configuration, are shown and discussed. The procedure is practical and the results are satisfactory.