Numerical simulation on stall margin improvement of transonic compressor by a trapped vortex casing treatment

被引：0
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作者：
机构：
[1] Research Institute of Unmanned Aerial Vehicle, Beijing University of Aeronautics and Astronautics, Beijing
[2] National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing
来源：
Yuan, Wei | 1600年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 29期
关键词：
Casing treatment; Compressor; Rotating stall; Stall margin improvement; Tip leakage flow; Transonic;
D O I：
10.13224/j.cnki.jasp.2014.12.023
中图分类号：
学科分类号：
摘要：
A type of trapped vortex casing treatment (CT) was designed, using pressure difference between suction side at front and pressure side at rear of passage to drive fluid flowing back. Boundary flow was sucked into slot at rear of passage, then injected into main flow at front of passage. During this process, momentum of the fluid in the leakage was increased, and then the stall margin of the blade was enhanced. The loss of mixing is decreased by adjusting the direction of suction and injection to the direction of main flow. Also the size of CT in axial direction is inside the blade dimention, which means this CT could be used in each stage of multistage compressors, without overlapping with stators. Numerical simulation was used to evaluate the effectiveness of this CT. Result shows that this CT could increase the stall margin 17. 39% of a transonic compressor rotor without compromise on efficiency. ©, 2014, BUAA Press. All right reserved.
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页码：2948 / 2956
页数：8
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