Numerical investigation of boundary layer suction in an axial transonic compressor cascade

GE Zheng-wei; GE Zhi-mei; ZHU Jun-qiang; ZHANG Hong-wu; HUANG Wei-guang; DU Hui

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Numerical investigation of boundary layer suction in an axial transonic compressor cascade

更新时间：2026-07-07

- Numerical investigation of boundary layer suction in an axial transonic compressor cascade
- Vol. 22, Issue 8, (2007)
- 作者机构：
  
  1. 中国科学院工程热物理研究所,北京,100080
  2. 沈阳发动机设计研究所,沈阳,110015
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2007
- 稿件说明：
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GE Zheng-wei, GE Zhi-mei, ZHU Jun-qiang, et al. Numerical investigation of boundary layer suction in an axial transonic compressor cascade[J]. 2007, 22(8).
DOI：

GE Zheng-wei, GE Zhi-mei, ZHU Jun-qiang, et al. Numerical investigation of boundary layer suction in an axial transonic compressor cascade[J]. 2007, 22(8). DOI：

摘要

使用MISES程序数值模拟了跨声速吸附式压气机叶栅流场

重点研究了吸气量和吸气位置对跨声速压气机叶栅气动性能的影响.结果表明

叶栅来流马赫数和方向一定时

吸气位置和吸气量是相互关联的关键参数

不同的吸气位置对应着不同的最佳吸气量

且随着吸气位置向后缘远离激波

最佳吸气量呈逐渐增大之势.从吸气对叶片吸力面边界层的影响效果分析

理想的吸气位置应该是在靠近激波后附面层发展到一局部极大值即将进入过渡段的位置附近.

Abstract

Based on the numerical investigations on the performance of an axial transonic compressor cascade with different suction slot locations and suction mass-flow

it has been shown that for a given inlet Mach number and flow angle

there exist an optimal suction mass-flow corresponding to the suction slot location.And the optimal suction mass-flow increases as the suction slot moves far from the shock location towards the trailing edge.The perfect suction slot location should be at the beginning of the transition region where the boundary layer thickness has developed to a local maximum value downstream of the shock.

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