Design and validation of high-lift turbine nozzle guide vane profile

被引：0
|
作者：
Zhang S. [1 ]
Shi J. [1 ]
Li W. [1 ]
Chen J. [1 ]
Pan S. [1 ]
机构：
[1] Hunan Key Laboratoryof Turbomachinery on Medium and Small Aero-Engine Hunan Aviation Powerplant Research Institute, Aero Engine Corporation of China, Zhuzhou
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2021年 / 36卷 / 01期
关键词：
Aerodynamic loss; Gas generator turbine; High-lift profile; Nozzle guide vane(NGV); Profile design;
D O I：
10.13224/j.cnki.jasp.2021.01.021
中图分类号：
学科分类号：
摘要：
A method for high-lift turbine blade design based on Pritchard 11 parameters method was introduced for turbine nozzle guide vane working under low entrance Mach number and typically low lift at front part of the blade. A series of high lift nozzle guide vane profile were designed and investigated using numerical calculation, and validated by linear cascade test. Results showed that the blade loading of high-lift profile was more uniform due to increase of Mach number at front part of the suction side, and the throat suction moved forward. The Mach number characteristic and attack angle characteristic showed that the highly-loaded blades generated lower total pressure loss. The pressure loss coefficient of high-lift profile was 2.59% lower under design condition than that of the datum profile. © 2021, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：185 / 192
页数：7
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