Film cooling characteristics analysis of turbine blade tip in transonic flow

被引：0

作者：

Zhang B. ^{[1
]}

Xia J. ^{[1
]}

Hu Q. ^{[2
]}

Zhu H. ^{[3
]}

机构：

[1] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha

[2] College of Basic Education, National University of Defense Technology, Changsha

[3] School of Power and Energy, Northwestern Polytechnical University, Xi'an

来源：

Guofang Keji Daxue Xuebao/Journal of National University of Defense Technology | 2024年 / 46卷 / 02期

关键词：

blade tip; film cooling; mass flow ratio; tip clearance gap; transonic flow;

D O I：

10.11887/j.cn.202402016

中图分类号：

学科分类号：

摘要：

To grasp the film cooling characteristics of the turbine blade tip in transonic flow, the pressure sensitive paint technique was used to experimentally obtain the effects of the tip clearance gap and mass flow ratio on the film cooling performance of the blade tip. The results indicate that, under conditions of low mass flow ratio, increasing the tip clearance height effectively enhances the film coverage in the mid-chord region of the blade tip. However, when the mass flow ratio is high, changes in the tip clearance height have an insignificant effect on the distribution of film cooling efficiency in this region. Under conditions of small tip clearance heights, the cooling coverage in the mid-chord region deteriorates gradually as the mass flow ratio increases. In contrast, with larger tip clearance heights, an improvement in cooling coverage is only observed when the mass flow ratio increases from 0.1% +0.05% to 0.14% +0.07%. © 2024 National University of Defense Technology. All rights reserved.

引用

页码：153 / 161

页数：8

共 30 条

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