涡轮平面叶栅非轴对称端壁优化设计  

Optimal design of profiled endwall for turbine cascade

作　　者：唐慧敏[1] 刘帅强[1] 罗华玲[1] 

机构地区：[1]中国航空工业集团公司商用航空发动机有限责任公司研发中心,上海200241

出　　处：《航空动力学报》2015年第3期707-713,共7页Journal of Aerospace Power

基　　金：上海市科学技术委员会科研计划(13521101100)

摘　　要：开发了一套造型灵活直观、网格生成速度快的涡轮平面叶栅非轴对称端壁优化设计工具,该工具的核心技术是非均匀有理B样条(NURBS)曲面造型和网格变形.在此基础上以商业软件Isight为优化驱动器,以CFX为求解器,搭建了非轴对称端壁优化设计流程.以Pack B涡轮平面叶栅为例,对其进行了非轴对称端壁优化设计.优化后涡轮平面叶栅总压损失系数减小了12.96%.结果表明:涡轮平面叶栅端部的静压分布改变削弱了涡轮平面叶栅通道中马蹄涡、通道涡的强度,提高了涡轮平面叶栅的气动性能.A method based on non-uniform rational B-spline （NURBS） surface technique coupled with mesh deforming technique was developed to design the profiled endwall for tur- bines cascade. This method has the advantages of flexible geometry representation and auto- matic rapid remeshing. An optimal design procedure of profiled endwall has been developed by integrating the commercial CFX solver and the optimization driver Isight. This procedure was applied to optimal design the profiled endwalls of Pack B turbine cascade. The total pressure loss coefficient of turbine cascade was reduced by 12.96% after optimization. The results show that the static pressure field on the endwall of turbine cascade is changed, so the horseshoe vortex and the passage vortex in turbine cascade passage are weakened. There- fore, the aerodynamic performance of the turbine cascade is improved.

关 键 词：涡轮平面叶栅 非轴对称端壁 优化设计 非均匀有理B样条曲面 网格变形 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程] TK263[动力工程及工程热物理—动力机械及工程]