Impacts of non⁃axisymmetric stagger angle on performance of compressor rotor blade

被引：0
作者：
Zhuang H. [1 ]
Teng J. [1 ]
Ma Y. [1 ]
Zhu M. [1 ]
Qiang X. [1 ]
机构：
[1] School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2021年 / 36卷 / 09期
关键词：
Aerodynamic performance; Axial compressor; Non⁃axisymmetric; Rotor blade; Stagger angle;
D O I：
10.13224/j.cnki.jasp.20200489
中图分类号：
学科分类号：
摘要：
In order to provide a reference for engineering design and manufacture of high pressure compressor blades at all operating conditions, steady and unsteady numerical simulations on multiple single⁃passage and eight⁃passage cases were conducted, and the impacts of non⁃axisymmetric stagger angle distribution on compressor performance were investigated at the design and off⁃design operating points.The results showed that the performance parameters of non⁃axisymmetric stagger angle cases were all lower than those of the uniform stagger angle cases, and the scatter range of the mass flow rate was wider at the near choking point.Non⁃axisymmetric stagger angle distribution made the pressure coefficients on the blade surface vary more greatly, which led to obvious decrease of the rotor efficiency.In the typical case with a small average deviation and a large standard deviation of the non⁃axisymmetric stagger angle distribution, because a blade among the passages greatly deviated from the stagger angle of the original blade, flow separation occurred within the range of 48%-82% blade span at the large flow rate condition, which decreased the outlet flow angle and efficiency.At the near stall point, compared with the original case, the corner separation at the hub of the typical case increased obviously.The diffusion factor at 10% blade span was 0.72% higher than the original high⁃loading design, which led to a decrease in the stall margin. © 2021, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：1999 / 2011
页数：12
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