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 哈尔滨工程大学学报  2019, Vol. 40 Issue (4): 774-780  DOI: 10.11990/jheu.201709051 0

### 引用本文

LU Huawei, WANG Xu, ZHENG Yuchen, et al. Effects of asymmetric boundary layer suction on vortex structures of highly loaded compressor cascades[J]. Journal of Harbin Engineering University, 2019, 40(4), 774-780. DOI: 10.11990/jheu.201709051.

### 文章历史

Effects of asymmetric boundary layer suction on vortex structures of highly loaded compressor cascades
LU Huawei , WANG Xu , ZHENG Yuchen , ZHANG Haixin
College of Marine Engineering, Dalian Maritime University, Dalian 116026, China
Abstract: In order to improve the vortex structure in the highly-loaded compressor cascades, to achieve the purpose of reducing the loss and improving the aerodynamic performance.This study investigates the asymmetric boundary layer suction on a highly-loaded compressor cascades by using the CFD methods which was validated by an experiment.Q criterion was used in vortex determination to analyze the total pressure loss and vorticity that the original and suction cascades.Furthermore, the model of vortex structures was established.The original blade exhibited loss of corner vortex mainly formed by blending of passage vortex and concentrated shed vortex.The strength of passage vortex in the suction side was weakened evidently through asymmetric suction.After asymmetric suction near the separation point, the total pressure loss in the corner of the suction side decreased considerably, and the loss of non-suction side migrated rapidly along the spanwise and pitchwise directions.
Keywords: highly loaded compressor cascades    boundary layer suction    vortex structures    end wall    total pressure loss    Q criterion    corner separation

1 研究方案与数值方法 1.1 叶型参数与研究方案

1.2 数值计算方法 1.2.1 网格划分与边界条件的设定

1.2.2 数值方法校核

 $\xi = ({P_{t, {\rm{in}}}}-{P_{t.{\rm{out}}}})/({P_{t, {\rm{in}}}}-{P_{{\rm{in}}}})$ (1)

2 计算结果分析 2.1 单侧抽吸对损失的影响

 Download: 图 5 出口截面总压损失系数云图 Fig. 5 The contour of outlet total pressure loss coefficient
 Download: 图 6 原型及不同方案出口截面总压损失系数变化 Fig. 6 The varation of outlet total pressure loss coefficient on different schemes

 Download: 图 7 不同轴向截面处总压损失系数云图 Fig. 7 The contour of total pressure loss coefficient on different axial sections
 Download: 图 8 不同轴向截面总压损失系数变化 Fig. 8 The varation of total pressure loss coefficient on different axial sections
2.2 单侧抽吸对轴向涡量的影响

 ${\Omega _x} = \frac{{\partial w}}{{\partial y}}-\frac{{\partial v}}{{\partial z}}$ (2)

 Download: 图 9 不同截面轴向涡量云图 Fig. 9 The contour of axial vorticity on different axial sections
2.3 单侧抽吸对旋涡结构的影响

Q准则于1988年由Hunt等[15]提出，通过观察Q等值面云图可以更为直观地了解叶栅流道内旋涡结构所在的位置及发展变化过程，其定义为：

 $Q = ({\Omega _{ij}}{\Omega _{ij}}-{S_{ij}}{S_{ij}})/2$ (3)

 Download: 图 10 采用总压进行着色的Q等值面图(Q = 10 000) Fig. 10 The iso-suface of Q colored by total pressure (Q = 10 000)

2.4 叶栅通道旋涡模型