三维涡轮叶片气动优化方法的研究  

STUDY FOR AERODYNAMIC OPTIMIZATION FOR TURBINE BLADE

作　　者：韩永志[1] 高行山[1] 尤莹[1] 李立州[1] 张娟[1] 

机构地区：[1]西北工业大学力学与土木建筑学院,西安710072

出　　处：《机械强度》2008年第1期63-67,共5页Journal of Mechanical Strength

基　　金：国家自然科学基金(50375124、10472094);航空科学基金(02C53011、03B53003);辽宁省智能信息处理重点实验室开放课题(2005-5)~~

摘　　要：提出一种进行三维涡轮叶片气动优化的多目标多约束方法。根据五次多项式方法进行三维涡轮叶片的参数化建模,采用N-S(Navier-Stokes)方程和湍流模型进行三维流场分析计算,K-S(Kreisselmeier-Steinhauser)函数法作为优化方法,利用近似技术加速循环优化速度,以气动效率和总压比为目标函数,对涡轮叶片进行多目标气动优化、形状优化。算例表明,使用该方法能使涡轮叶片的性能得到明显改善,证明提出的优化方法可行有效。Based on aerodynamic analysis, an optimization method is presented for the profiles of 3D turbine blade. The method is capable of addressing multiple objectives and constrains without relying on user input. A quintic polynomial is used to build the three- dimensional blade model and a three-dimensional Navier-Stokes solver and turbulent model are used to solve for the flow field around the turbine blade. The turbine aerodynamic efficiency and total pressure ratio are used as the objective functions. The optimization is com- pleted with the Kreisselmeier-Steinhauser function method and approximation technique to accelerate the iterative cycle. The result of optimizing on a true blade shows that the overall performance of the blade is improved remarkably, and proves that the proposed optimization procedure is feasible and effective.

关 键 词：涡轮叶片 多目标优化 气动 近似技术 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程] TB114.1[理学—运筹学与控制论]