燃气轮机跨声速高压涡轮导叶叶型优化及验证  

Optimization and Validation of Gas Turbine Transonic High Pressure Turbine Guide Vane Profile

作　　者：柴家兴 李昂 陈云 黄鹏 Jia-xing Chai;Ang Li;Yun Chen;Peng Huang(AECC Shenyang Engine Research Institute)

机构地区：[1]中国航发沈阳发动机研究所

出　　处：《风机技术》2025年第2期13-18,共6页Chinese Journal of Turbomachinery

基　　金：国防基础性军工科研院所稳定支持二期项目。

摘　　要：为探究跨声速高压涡轮叶型优化方向及设计方法,基于某型导叶提出融合小安装角、前缘增载及喉部后平直型线的复合优化策略。采用数值模拟与平面叶栅试验开展了研究分析。研究结果表明:通过减小安装角并采用叶背平直段优化叶型,使气流膨胀峰值马赫数位置前移15%,同时前缘曲率强化促使叶型载荷分布更均匀,峰值马赫数降低8%;通过调节尾缘激波强度分布,有效抑制激波与附面层干涉效应,尾迹区域宽度显著降低;最终实现设计工况下总压损失系数降低0.8%。To explore the optimization direction and design method of transonic high-pressure turbine guide vane profile,a composite optimization strategy is proposed based on a certain type of guide vane,which integrates small installation angle,leading edge loading,and straight throat profile.Research and analysis were conducted based on numerical simulation and plane cascade experiments.The results show that the optimized guide vane profile can move the peak Mach number position of airflow expansion forward by 15%by reducing the installation angle and using the straight section of the blade back.At the same time,the strengthening of the leading edge curvature promotes a more uniform distribution of blade load,resulting in an 8%reduction in peak Mach number;By adjusting the intensity distribution of the trailing edge shock wave,the interference effect between the shock wave and the boundary layer is effectively suppressed,and the width of the wake region is significantly reduced;Ultimately achieving 0.8%reduction in total pressure loss coefficient under design condition.

关 键 词：跨声速 高压涡轮 导叶 优化 平面叶栅 

分 类 号：TK14[动力工程及工程热物理—热能工程]