利用分析函数表示叶型中弧线与厚度分布，结合准三维流动求解器以及序列二次规划算法对高负荷级的动叶和静叶进行了以减小落后角和气动损失为目标的气动优化。初始叶型为NACA 65叶型，中弧线采用广义抛物线表示，只用最大拱度和最大拱度位置控制；厚度分布采用一阶类/形函数表示，只用一个比例因子KR控制。叶型几何只用3个参数变量，实现对初始叶型的表达。优化后动叶和静叶设计点损失分别下降19%和7.4%，工作范围均有增加，静压比提高，优化叶型的气动分布符合可控扩散叶型的设计思想。

Both the camber line and the thickness distribution of compressor profiles are prescribed as analytical functions,which are combined with the quasithreedimensional flow solver and the sequential quadratic programming algorithm to reduce the deviation angle and aerodynamic losses in the rotor and stator blades of the high load stage.In this paper,optimization is started from a conventional NACA65 design，in which the camber line is prescribed by a generalized parabolic arc line and the thickness distribution is prescribed by the Class/Shape Function Transformation formulation.There were only three parameters to be used for representing the geometric model,and it had been verified that these three parameters can realize the expression of the initial profile approximately.After optimization,the losses of rotor and stator decreased by 19% and 7.4% at design points,respectively.The operation range and the static pressure ratio are increased clearly.The optimized profiles show close agreement with the design idea of controlled diffusion airfoils.

TK474.8

国家重点研发计划（2018YFB0604404）