高压涡轮导向器非轴对称端壁设计  

Design on non-axisymmetric endwall of high-pressure turbine nozzle

作　　者：唐洪飞 曾军 卫刚 马建 刘海祥 TANG Hong-fei;ZENG Jun;WEI Gang;MA Jian;LIU Hai-xiang(AECC Sichuan Gas Turbine Establishment, Chengdu 610500, China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2018年第2期8-15,共8页Gas Turbine Experiment and Research

摘　　要：为进一步降低高性能涡轮端壁二次损失,根据其内端壁二次流形成和发展机理,提出一种基于多段三角函数的非轴对称端壁正交造型方法。根据此造型方法,通过优化的方式对高压涡轮导向器进行了三维端壁设计,并对此具有工程约束的寻优设计结果进行了全三维N-S方程数值模拟,分析和讨论了采用的非轴对称端壁造型方法对二次流损失的影响。结果表明:采用多段三角函数的非轴对称端壁正交造型方法,能有效控制马蹄涡压力侧分支的流动和通道涡的形成,并能有效降低高压涡轮导向器的端壁二次流损失。To reduce the endwall secondary loss of high pressure turbine, a kind of non-axisymmetrie endwall modeling method based on multiple trigonometric function was put forward in according to the mechanism of secondary flow forming and development, and a high pressure turbine nozzle was redesigned by means of 3D endwall optimization design with this method. The optimal case was simulated by full 3D N-S equation, and the effect of the secondary flow loss on the non-axisymmetrie endwall modeling was analyzed. The results show that the horseshoe vortex pressure side branch flowing and the passage vortex development were effectively controlled, and the secondary flow loss of the high pressure turbine nozzle can be reduced effectively by using the non-axisymmetrie endwall design.

关 键 词：航空发动机 高压涡轮 导向器 二次流损失 非轴对称端壁 优化设计 高性能 

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]