Linear stability model of rotating stall based on direct numerical techniques:PartⅡ——A simplified model and its applications

HOU Rui-wei; SUN Xiao-feng

Chinese

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Linear stability model of rotating stall based on direct numerical techniques:PartⅡ——A simplified model and its applications

更新时间：2026-07-07

- Linear stability model of rotating stall based on direct numerical techniques:PartⅡ——A simplified model and its applications
- Vol. 24, Issue 12, (2009)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
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HOU Rui-wei, SUN Xiao-feng. Linear stability model of rotating stall based on direct numerical techniques:PartⅡ——A simplified model and its applications[J]. 2009, 24(12).
DOI：

HOU Rui-wei, SUN Xiao-feng. Linear stability model of rotating stall based on direct numerical techniques:PartⅡ——A simplified model and its applications[J]. 2009, 24(12). DOI：

摘要

提出一个基于二维流动基础上的线性化旋转失速稳定性模型

该模型可以通过求解特征值来预测低速轴流压气机的失速边界.叶片几何对流动的影响用一个体积力模型来代替.给出了有限差分法和谱配置法两种离散特征方程的方式

并且在针对一台低速压气机和一台跨声压气机转子在低转速的情况进行了算例的验证

结果表明该模型能够比较准确的预测低速压气机失速边界.

Abstract

A two-dimensional linear stability model was presented

which can be used to estimate the inception point of rotating stall in axial flow compressors by solving the eigenvalues

the effects of the blade rows in compressors on the flow field have been modeled by body force source terms in the momentum equations.Two methods

finite difference and spectral collocation methods

have been used to discretize the eigenvalue equations.The validations of model have been performed in two different cases

and the results show that the simplified model is able to predict the stall onset point of low-speed axial compressors.

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庞焕杰

邱明

MAO Zhi-ming

HU Jun

ZHANG Huan

YAN Wei

HUANG Wei

Related Institution

河南科技大学机电工程学院

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics

College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics

Laboratory of Turbomachinery Experiment，Sichuan Gas Turbine Establishment，Aero Engine Corporation of China

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