具有良好灵活性的高精度叶型参数化建模方法对于压气机叶型设计和优化具有重要影响。本文研究了一种基于非有理B样条曲线理论(NURBS)曲线组和遗传算法的轴流压气机叶片参数化建模方法。该方法基于中弧线厚度叠加法，采用两条三次七点NURBS曲线分别构造中弧线形状和厚度分布，前尾缘采用双二次NURBS曲线，通过多段曲线光滑拼接实现叶片造型。以压气机型线方差值最小作为目标函数，利用遗传算法实现了叶型的参数化建模。通过数值模拟实验证明，本文提出的参数化造型方法适用于高亚音速压气机叶型的参数化建模。

The highprecision,flexible parametric modeling method for blade profile has an important impact on compressor blade design and optimization.In this paper,a parametric modeling method of axial compressor blade based on nonuniform rational Bspline (NURBS) curve group and genetic algorithm is studied.This method adopts the traditional mean camber thickness superposition method,using two threetime sevenpoint NURBS curves to construct the mean camber shape and thickness distribution respectively,and the anterior tailing edge adopts a double quadratic NURBS curve,and the blade shape is achieved through smooth splicing of multisegment curves.Taking the minimum variance of the compressor spline as the objective function,the parametric modeling of the blade profile is realized by using genetic algorithms.Numerical simulation experiments show that the parametric modeling method proposed in this paper is applicable to the parametric modeling process of the blade profile of high subsonic compressor.

V231.1

国家科技重大专项（2017-II-0006-0019）