Influence of trailing edge designs of squealer tips on aerodynamic performance of high-pressure turbine

被引：0
|
作者：
Jiang H. [1 ]
Zhang Z. [1 ]
Lu S. [2 ]
机构：
[1] University of Michigan, Shanghai Jiao Tong University Joint Institute, Shanghai Jiao Tong University, Shanghai
[2] School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 06期
关键词：
aerodynamics performance; high pressure turbine; over-tip-leakage flow; squealer tip; trailing edge cutback;
D O I：
10.13224/j.cnki.jasp.20230512
中图分类号：
学科分类号：
摘要：
In this article，full cavity squealer tip and several pressure side and suction side cutback blade tips were designed，their detailed flow field and aerodynamic performance were compared with full cavity squealer tip numerically，including vortices inside cavity and flows around blade tip trailing edge，differences in tip leakage flow rate，downstream total pressure loss and entropy rise. The result indicated that pressure side cutback designs caused the cavity vortex leak earlier compared with full cavity tip，a small vortex formed at cut region leading to increase in total pressure loss of 7.1% at most; flow inside cavity left at cut region for suction side cutback designs instead of crossing over cavity wall，downstream total pressure loss was relatively smaller，with the reduction of 4.6% at most. Compared with full cavity and pressure side cutback squealer tip，suction side cutback designs have better aerodynamic performance. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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