Numerical simulation on flow field of axial compressor after bleeding

被引：0
|
作者：
Liang D. [1 ]
Gong Z.-Q. [1 ]
Chen C.-P. [1 ]
Gao S. [2 ]
机构：
[1] Aero Engine Academy of China, Aero Engine (Group) Corporation of China, Beijing
[2] Shenyang Engine Research Institute, Aero Engine (Group) Corporation of China, Shenyang
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2017年 / 32卷 / 02期
关键词：
Axial compressor; Bleeding; Grid independent; Stall margin; Total pressure loss;
D O I：
10.13224/j.cnki.jasp.2017.02.024
中图分类号：
学科分类号：
摘要：
By analyzing the transonic single-stage compressors NASA Stage 35, the results of numerical simulation and the experimental results were combined, proving the veracity of numerical simulation. The hole and slot bleeding were calculated by two ways, and the same results were got. At last, the results of hole bleeding and the slot were compared. Result showed that, the slot bleeding was better. The bleeding/cooling block of NUMECA software was easy to realize the bleeding, another way increased the difficulty and complexity of numerical simulation, but it agreed with the fact of bleeding on compressor. Before the bleeding, the efficiency improved, and the total pressure ratio declined little. At same time, stall margin was enhanced. © 2017, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：446 / 454
页数：8
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