基于二维优化方法的涡轮过渡流道设计  

Design of Intermediate Turbine flowpath Based on Two-dimensional Optimization Method

作　　者：杨金广[1] 吴虎[1] 杨鹏[1] 毛凯[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2013年第2期161-167,共7页Journal of Propulsion Technology

摘　　要：为优化涡轮过渡流道的气动性能,以期提高发动机的整体经济性能,采用二维通流法与单纯性优化算法相结合的方法,对某型发动机涡轮过渡流道进行了二维优化。优化后过渡流道出口的总压损失系数降低了8.4%,流道扩压能力增加了40.4%,同时过渡流道出口气流均匀性也得到很大幅度的改善。使用CFD技术对初始流道和优化后流道性能进行了三维数值模拟,并分析比较了过渡流道与整流支板的三维流场分布,从而验证了二维计算与优化算法的可行性。To optimize aerodynamic performance of intermediate turbine duct in order to gain improvement of better economic performance of the engine,a two-dimensional optimization method was adopted in designing of intermediate duct by combining two-dimensional through flow method and simplex method together.The optimization was conducted successfully in obtaining the total pressure loss coefficient of the duct outlet decreased by 8.4 percent and diffusion capability increased by 40.4 percent,meanwhile flow uniformity of that was improved substantially.Additionally,both initial duct and optimal duct,using three dimensional CFD method,were subsequently numerically simulated to compare the flow field of intermediate duct and struts,which shows the feasibility of this optimization method.

关 键 词：涡轮过渡流道 二维优化 数值模拟 总压损失系数 压力系数 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]