Experimental Study on Film Cooling Effectiveness of the Turbine Blade with Compound-Angled Fan-Shaped Holes under Wake Influence

被引：1
|
作者：
Li J. [1 ]
Zhu H. [1 ]
Chen D. [1 ]
Chen G. [2 ]
Zhou D. [1 ]
机构：
[1] School of Power and Energy, Northwestern Polytechnical University, Xi'an
[2] AECC Shenyang Engine Institute, Shenyang
来源：
Hsi-An Chiao Tung Ta Hsueh/Journal of Xi'an Jiaotong University | 2019年 / 53卷 / 09期
关键词：
Compound-angled fan-shaped hole; Film cooling effectiveness; Pressure sensitive paint; Turbine blade; Wake;
D O I：
10.7652/xjtuxb201909022
中图分类号：
学科分类号：
摘要：
The film cooling effectiveness of the turbine blade with compound-angled fan-shaped holes was measured by the pressure sensitive paint technique. The wake's Strouhal number was varied from 0 to 0.36 and three mass flux ratios were determined. Results show that the compound-angled holes can enhance the lateral spreading of coolant, and the injection has a wider coverage area without wakes. The increase of the mass flux ratio causes an increase in the film cooling effectiveness over the leading edge and most area of the pressure surface with compound-angled holes, but a decrease on the suction surface. The increase of mass flux ratio also reduces the area near the tip on the suction side, where the film coverage is insufficient under wake influence, and causes an increase in the film cooling effectiveness over the leading edge, the pressure surface and the suction surface near the trailing edge, but decreases this effectiveness on the mid-chord region of the suction surface. The wake causes a remarkable decrease in the film cooling effectiveness over the blade surface. In the case that wake's Strouhal number is 0.36, the average film cooling effectiveness over the blade is decreased by 35% under the condition of low mass flux ratio, and decreased by 26% under the condition of high mass flux ratio. © 2019, Editorial Office of Journal of Xi'an Jiaotong University. All right reserved.
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页码：167 / 175
页数：8
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