高压涡轮变叶顶蜂窝角度二次流动特性研究  

Secondary Flow Characteristics of High-Pressure TurbineVariable Angle Honeycomb Tip

作　　者：孙爽[1] 宁嘉昕 孙小鹏 薛成 司海旭 卢乐晗 孔庆国[3] SUN Shuang;NING Jia-xin;SUN Xiao-peng;XUE Cheng;SI Hai-xu;LU Le-han;KONG Qing-guo(College of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China;MTU Maintenance Zhuhai Co.,Ltd.,Zhuhai 519030,China;Sino-European Institute of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300 [2]珠海保税区摩天宇航空发动机维修有限公司,广东珠海519030 [3]中国民航大学中欧航空工程师学院,天津300300

出　　处：《推进技术》2023年第11期111-119,共9页Journal of Propulsion Technology

基　　金：航空发动机及燃气轮机基础科学中心项目(P2022-B-Ⅱ-008-001)。

摘　　要：为减少叶顶泄漏流带来的气动损失,本文对高压涡轮叶顶复合蜂窝的排布角度进行寻优,并分析其气动性能。研究过程保持叶顶蜂窝几何形状不变,改变复合蜂窝在叶顶的排布角度,降低叶顶二次流的总压损失系数和叶顶相对泄漏比。以叶栅出口下游30%轴向弦长位置的面平均总压损失系数为目标参数,利用Isight软件嵌套图形-网格自动生成流程,对0~57°旋转角度内的蜂窝排布方式进行遍历寻优,得到低总压损失的蜂窝排布方式。研究表明,最优排布结果与平叶顶相比,叶栅总压损失降低5.21%,与基准角度蜂窝相比降低1.34%。最优排布方案对叶顶泄漏流的阻碍效果更明显,增大了蜂窝对气流的耗散能力,降低了跨叶顶的横向驱动力,减少了泄漏涡的损失。In order to reduce the aerodynamic loss caused by tip leakage flow,the arrangement angle of a composite honeycomb at the top of high pressure turbine blade was optimized and the aerodynamic performance at the tip region was analyzed.In the present research,the geometry of the honeycomb at the blade tip was kept un-changed,and the arrangement angle of the composite honeycomb at the blade tip was changed to reduce the total pressure loss coefficient and the relative leakage ratio of the secondary flow at the blade tip.With the plane aver-age total pressure loss coefficient at 30%axial chord length downstream of the cascade outlet as the target parame-ter,the honeycomb layout mode within the range of 0~57°rotation angle was optimized by using the Isight soft-ware nesting graph grid automatic generation process,and the honeycomb layout mode with low total pressure loss was obtained.The results suggested that the optimization honey tip reduced the total pressure loss of the cas-cade by 5.21%compared with the flat tip and 1.34%compared with the basic honey tip.The optimal arrangement scheme had a more obvious effect on preventing the tip leakage flow,increasing the honeycomb’s ability to dissi-pate the flow,reducing the transverse driving force across the tip,and reducing the loss of the leakage vortex.

关 键 词：高压涡轮 复合蜂窝 流动控制 气动损失 叶顶泄漏流 

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]