Research on the effects of a transonic compressor rotor with axial skewedslots casing treatment at low Reynolds number

XIA Qin-bin; WANG Ru-gen; ZHOU Min; WANG Long; LI Yong; GUO Fei-fei

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Research on the effects of a transonic compressor rotor with axial skewedslots casing treatment at low Reynolds number

更新时间：2026-07-07

- Research on the effects of a transonic compressor rotor with axial skewedslots casing treatment at low Reynolds number
- Vol. 25, Issue 6, (2010)
- 作者机构：
  
  1. 空军工程大学工程学院,西安,710038
  2. 北京航空工程技术研究中心,北京,100076
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2010
- 稿件说明：
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XIA Qin-bin, WANG Ru-gen, ZHOU Min, et al. Research on the effects of a transonic compressor rotor with axial skewedslots casing treatment at low Reynolds number[J]. 2010, 25(6).
DOI：

XIA Qin-bin, WANG Ru-gen, ZHOU Min, et al. Research on the effects of a transonic compressor rotor with axial skewedslots casing treatment at low Reynolds number[J]. 2010, 25(6). DOI：

摘要

采用非定常数值方法对低雷诺数条件下50%

75%和100%三种不同轴向叠合量的轴向倾斜缝处理机匣结构对NASA Rotor 37跨声速压气机转子的扩稳效果进行了研究.结果表明

引入处理机匣后

附面层径向涡得到了很好的抑制

由附面层径向涡所引发的叶顶阻塞区大为减小

虽然又引发了由叶顶间隙涡对叶顶所造成的阻塞

但引入处理机匣后对压气机稳定性仍有较大的改善

能有效提高压气机转子的失速裕度.

Abstract

The effects of NASA Rotor 37 transonic compressor rotor with 50%

75% and 100% axial congruence skewed slots casing treatment at low Reynolds number were investigated by unsteady numerical simulation.The result shows that the boundary layer radial vortex is well controlled and the blockage zone due to boundary layer separation is notably reduced.It's also found that the blockage zone is caused due to the tip leakage vortex.The stall margin of the compressor rotor with axial skewed slots is obviously improved

contributing to the compressor stability.

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Related Author

XIA Qin-bin

WANG Ru-gen

ZHOU Min

WANG Ru-gen

BAI Yun

WANG Xue-de

WU Wei

Related Institution

The Engineering Institute, Air Force Engineering University

Engineering Institute, Air Force Engineering University

Aeronautic Equipment Institute of Air Force, Equipment Research Academy

School of Aerospace Engineering，Beijing Institute of Technology

Institute for Aero Engine，Tsinghua University

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