A CALCULATION OF SECONDARY FLOWS AND DEVIATION ANGLES IN MULTISTAGE AXIAL-FLOW COMPRESSORS

Li Shiming; Chen Maozhang

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A CALCULATION OF SECONDARY FLOWS AND DEVIATION ANGLES IN MULTISTAGE AXIAL-FLOW COMPRESSORS

更新时间：2026-07-07

- A CALCULATION OF SECONDARY FLOWS AND DEVIATION ANGLES IN MULTISTAGE AXIAL-FLOW COMPRESSORS
- Vol. 8, Issue 2, (1993)
- 作者机构：
  
  1. 清华大学热能系动控室
  2. 北京航空航天大学,100084
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：1993
- 稿件说明：
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Li Shiming, Chen Maozhang. A CALCULATION OF SECONDARY FLOWS AND DEVIATION ANGLES IN MULTISTAGE AXIAL-FLOW COMPRESSORS[J]. 1993, 8(2).
DOI：

Li Shiming, Chen Maozhang. A CALCULATION OF SECONDARY FLOWS AND DEVIATION ANGLES IN MULTISTAGE AXIAL-FLOW COMPRESSORS[J]. 1993, 8(2). DOI：

摘要

在含完全径向掺混作用多级轴流压气机子午二维流场计算基础上

基于Adkins-Smith二次流模型

发展了能计算各个叶片排出口截面上二次流以及相应的落后角计算方法。二次流包括通道涡、尾涡、叶顶间隙漏泄涡、静叶端部带冠叶片间隙漏泄流和叶片边界层及其尾迹中的径向位移速度。由于得出了二次流场的解析解

使得实际计算简单而迅速。在离设计工况不远以及无大分离泡出现情况下

所得二次流场的几种大尺度涡场与试验大体一致

落后角计算与试验相符。

Abstract

A secondary flow model and a method for calculating blade deviation angle have been developed for multistage axial flow compressors.This model is a modification of Adkins-Smith model.The secondary flow vorticities are modeled based on the cal culated meridional flow including different kinds of spanwise mixing effects.The secondary flows are obtained on the fanlike surface downstream the blade rows with a standard separation of variables approach which yields a complex series.The secondary flow model includes effects of blade passage vortex

blade trailing edge vortex

blade en d clearances

blade end shrouding

blade boundary layer and wake centrifugation.The deviation angles are related to the calculated cross passage secondary velocities and a modified Carter ’s rule.Good agreement has been obtained between experimental data and the calculated results in the cases of design-point-type applications for which significant regions of separated flow are not present.

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