Film Cooling Characteristic on Trailing Edge Cutback of Gas Turbine Airfoils with Dimple/Protrusion Structure

被引：0

作者：

Zhang, Ling ^{[1
]}

Shi, Meng-Ying ^{[1
]}

Yuan, Zheng ^{[1
]}

Hong, Wen-Peng ^{[1
]}

机构：

[1] College of Energy Resource and Mechanical Engineering, Northeast Electric Power University, Jilin,132012, China

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2020年 / 41卷 / 02期

关键词：

D O I：

10.13675/j.cnki.tjjs.190233

中图分类号：

学科分类号：

摘要：

In order to investigate the effects of the dimple and protrusion structures of suction surface on film cooling characteristics of turbine blade trailing edge, the cooling performance and flow mechanism of turbine blade trailing edge were analyzed in detail by numerical simulation method when the blowing ratio M=1.1 (Re=2.5×105). The results show that, compared with the original one, the dimple and protrusion structure on trailing edge can improve the film cooling efficiency in the region of X/H > 6 (the split width of H is 4.8mm) downstream of the split outlet, while have little effect on the film cooling efficiency in the region of X/H © 2020, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：372 / 381

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