基于全局气动优化方法的跨声速叶栅气动优化  

Aerodynamic optimization of transonic cascade using global aerodynamic optimization method

作　　者：宋立明[1] 罗常[1] 李军[1] 丰镇平[1] 

机构地区：[1]西安交通大学叶轮机械研究所,西安710049

出　　处：《航空动力学报》2008年第6期1019-1023,共5页Journal of Aerospace Power

摘　　要：提出了适用于叶栅三维气动设计优化的全局自动气动优化方法.对NASA Rotor 37转子叶栅进行了气动优化设计.利用该叶栅的试验数据校核了计算流体(CFD)程序的可靠性.以等熵效率最高为目标函数,在满足流量约束和总压比约束的条件下,完成了跨声速叶栅的气动优化设计.优化叶栅的等熵效率提高了1.66%,具有优秀的气动性能和变工况性能.优化结果表明,通过优化三维跨声速叶栅的型线和径向基迭方式,可以有效的减小跨声速叶栅的激波损失.A global aerodynamic optimization method was proposed for three-dimensional cascade design. The method was applied to the NASA Rotor 37, which was a test transonic compressor cascade representing complex three-dimensional viscous flow structures. The capability of the computational fluid dynamics（CFD） code was validated by comparing the computed results with experimental data available in the open literature. The transonic cas-cade was optimized for the maximization of the isentropic efficiency under given flow conditions, using constraints on the mass flow rate and the total pressure ratio. The isentropic efficiency of the optimized design was 1.66% higher than that of the reference design, showing a better aerodynamic performance and better off-design performance. It shows that the shock losses of the transonic cascade could be reduced by optimizing the profiles of the transonic cascade and its radial stacking mode.

关 键 词：航空 航天推进系统 气动优化 跨声速 三维叶栅 自适应差分进化算法 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程] O354[理学—流体力学]