Optimization design and test of the non⁃axisymmetric endwall of the compressor stator

被引：0
|
作者：
Wang J. [1 ]
Hu J. [2 ]
Jiang C. [2 ]
机构：
[1] Shenyang Engine Research Institute, Aero Engine Corporation of China, Shenyang
[2] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2021年 / 36卷 / 10期
关键词：
Compressor test; Embedded stator; Local blade height; Multistage compressor; Non⁃axisymmetric endwall; Optimization design;
D O I：
10.13224/j.cnki.jasp.20200389
中图分类号：
学科分类号：
摘要：
In order to explore the optimization design method of non⁃axisymmetric endwall in multistage compressor environment, the non⁃axisymmetric endwall profiling of the casing endwall and the hub endwall of an embedded stator was studied by numerical simulation optimization and experimental test.The local total pressure loss coefficient of local blade height near the endwall was selected as the objective function.The result proved that compared with the traditional total pressure loss of whole blade height as the objective function, the total pressure loss coefficient of stator can be reduced more in less optimization steps (400 steps), showing that this method can effectively reduce the optimization time and lay a foundation for the engineering application of non⁃axisymmetric endwall optimization design in multistage compressors. © 2021, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：2157 / 2172
页数：15
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