涡轮导叶非轴对称端壁技术研究  

Investigation of the Profiled Endwall for a High Pressure Turbine Vane

作　　者：胡书珍 吕剑波 罗华玲 HU Shuzhen;LÜ Jianbo;LUO Hualing(AVIC Commercial Aircraft Engine Co.,LTD.R&D Center Dept.,Shanghai 200241,China)

机构地区：[1]中国航发商用航空发动机有限责任公司研发中心,上海200241

出　　处：《工程热物理学报》2022年第5期1233-1239,共7页Journal of Engineering Thermophysics

基　　金：民用飞机专项科研项目(No.MJZ-2014-D21)。

摘　　要：本文基于非均匀有理B样条曲面造型和网格变形技术开发了涡轮导叶非轴对称端壁造型工具,并以商业软件Isight为优化驱动器,同时借助CFX为求解器,搭建了非轴对称端壁自动优化设计系统。应用该系统对某高压涡轮导叶进行非轴对称端壁优化设计,优化非轴对称端壁使得导叶总压损失系数减小了3.44%,非轴对称端壁试验验证总压损失系数减小了5.67%;通过流场细节分析表明,非轴对称端壁设计通过改变下端区轮毂处压力分布,减小了横向压力梯度,削弱了端壁区域流向涡的强度,从而减小了二次流损失,改善了涡轮导叶的气动性能。A method based on non-uniform rational B-spline surface(NURBS) technique coupled with mesh deforming technique was developed to design the profiled endwall of turbines. An optimization procedure has been developed by integrating the in-house geometry manipulator, a commercial three-dimensional CFD flow solver and the optimization driver, Isight^(TM). This procedure was applied to design the profiled endwalls of a turbine vane. The total pressure loss was reduced to 3.44% by numerical evaluation. The experiment data validated the total pressure loss was reduced to 5.67%. Results showed that the static pressure field on the hub endwall was changed, and the streamwise vortices were weakened near the hub region. Thereby, the aerodynamic performance of the turbine vane was improved.

关 键 词：高压涡轮导叶 非轴对称端壁 优化设计系统 实验验证 流向涡 

分 类 号：TK123[动力工程及工程热物理—工程热物理]