高负荷动力涡轮叶型优化研究  

Optimization of blade profile of highly-loaded power turbine

作　　者：陈晨 李维 CHEN Chen;LI Wei

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：《现代机械》2022年第1期1-5,共5页Modern Machinery

摘　　要：对某型高负荷动力涡轮第一级导叶进行前加载、中间加载、后加载三种方案的叶型优化,用数值模拟的方法研究三种方案对流动损失的影响机理,将三种方案的气动性能参数与未优化的高负荷动力涡轮进行对比,分析了涡轮气动性能优化效果。结果表明:三种叶型优化方案均能控制叶片表面的流动分离,前加载叶片设计增加了端区的二次流损失,后加载叶片设计增加了二维叶型损失,中间加载优化方案具有更优的气动性能。In this study, three blade profile optimization schemes(front loading, middle loading, and rear loading) of the first-stage guide vane of a certain highly-loaded power turbine are carried out. By using numerical simulation method to study the influence mechanism of the three schemes on the flow loss, the aerodynamic performance parameters of the three schemes are compared with the unoptimized highly-loaded power turbine, and the optimization effect of the turbine aerodynamic performance is analyzed. The results show that the three blade profile optimization schemes can all eliminate the flow separation on the blade surface. The front-loading blade design increases the secondary flow loss in the end zone, the rear-loading blade design increases the two-dimensional blade profile loss, and the middle-loading optimization scheme has the best aerodynamic performance.

关 键 词：前加载 后加载 叶型损失 高负荷动力涡轮 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]