高压涡轮气动优化与分析  

Aerodynamic optimization and analysis of a high pressure turbine

作　　者：杨伟平 房兴龙 欧阳玉清 李恩华 曾飞 YANG Wei-ping;FANG Xing-long;OUYANG Yu-qing;LI En-hua;ZENG Fei(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Hunan Key Laboratory of Turbomachinery on Medium and Small Aero-Engine,Zhuzhou 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002

出　　处：《燃气涡轮试验与研究》2022年第3期26-31,37,共7页Gas Turbine Experiment and Research

摘　　要：针对航空发动机高压涡轮气动性能提升需求,对其转静轴向间距和动叶进行了优化。首先,在不改变子午流道几何并考虑叶片冷却、结构强度设计的条件下,对高压涡轮进行级环境下的转静轴向间距气动优化。研究表明,存在一个最佳的转静轴向间距,使得涡轮扭矩功效率(以下简称效率)提高约0.20%。然后,基于iSIGHT,集成Numeca、CFX软件,开发了三维气动优化集成平台,实现了叶型参数化、网格划分、数值计算及三维计算结果的自动处理。采用该平台对动叶进行多目标优化,结果表明,在保持涡轮进口流函数和膨胀比基本不变的条件下,效率提高了0.799%,功率增加了0.785%,而级出口绝对气流角仅减小2.3°。In order to improve the aerodynamic performance of a high pressure turbine, aerodynamic optimization was carried out under stage environment without changing the meridional channel and considering the demand of cooling blade and structural strength design. Axial spacing between stator and rotor was optimized and the results show that there was an optimal axial spacing to increase the turbine efficiency by 0.20%. Furthermore, based on optimization platform iSIGHT FD, a 3D integrated aerodynamic optimization system was developed with Numeca and CFX to automatic process the blade parameterization, mesh generation, numerical calculation and 3D calculation result. The system has been applied to the 3D aerodynamic multi-objective optimization of the rotor blade. Results show that the turbine efficiency and power are increased by 0.799% and 0.785% respectively, while the stage outlet flow angle is only reduced by 2.3°.

关 键 词：航空发动机 高压涡轮 ISIGHT 轴向间距 多目标优化 性能需求 

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]