Numerical investigation on flow field characteristics of a transonic compressor rotor

被引：0
作者：
Zhong, Jing-Jun [1 ]
Gao, Yu [1 ]
Li, Xiao-Dong [1 ]
Jiang, Xue-Hong [2 ]
机构：
[1] Marine Engineering College, Dalian Maritime University, Dalian
[2] School of Foreign Languages, Dalian Jiaotong University, Dalian
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2015年 / 36卷 / 12期
关键词：
Flow field characteristic; Numerical simulation; Shock wave; Tip clearance; Transonic compressor;
D O I：
10.13675/j.cnki.tjjs.2015.12.006
中图分类号：
学科分类号：
摘要：
In order to investigate the inner flow field characteristics of a transonic compressor rotor at the design speed and explore the flow mechanism, shock wave location and development under the transonic flow condition, the three dimensional numerical analysis are used. The result shows that the transonic compressor rotor has a wide operating ranges, the stall margin is 27.15%. Near choking condition, a bow shock wave occurs on the leading edge of the rotor blade, and a normal shock wave occurs in the flow passage. With the back pressure increasing, the location of shock wave moves forward to the leading edge. The relative Mach number reached by 1.5 at the tip blade on the leading edge in peak efficiency condition. Near stall condition, the normal shock wave disappears. There exists intense interaction between the shock wave-boundary layers and shock wave-tip leakage on the tip of the rotor blade. The entropy increases at that position with the increase of the back pressure. With the shock wave moving forward, the region with high entropy moves towards the leading edge of the blade. © 2015, Journal of Propulsion Technology. All right reserved.
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页码：1795 / 1801
页数：6
相关论文
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