Numerical simulation of single-stage transonic compressor with inlet distortion

GUO Jin; HU Jun; YIN Chao; TU Bao-feng

doi:10.13224/j.cnki.jasp.2016.03.018

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Numerical simulation of single-stage transonic compressor with inlet distortion

更新时间：2026-07-07

- Numerical simulation of single-stage transonic compressor with inlet distortion
- Vol. 31, Issue 3, Pages: 669-677(2016)
- 作者机构：
  
  1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京,210016
  2. 先进航空发动机协同创新中心,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2016.03.018
  CLC：
- Published：2016
- 稿件说明：
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郭晋, 胡骏, 尹超, 屠宝锋. 单级跨声速压气机进气畸变数值模拟[J]. 航空动力学报, 2016, 31(3): 669-677.

doi: 10.13224/j.cnki.jasp.2016.03.018
郭晋, 胡骏, 尹超, 屠宝锋. 单级跨声速压气机进气畸变数值模拟[J]. 航空动力学报, 2016, 31(3): 669-677. DOI： 10.13224/j.cnki.jasp.2016.03.018.

doi: 10.13224/j.cnki.jasp.2016.03.018 DOI：

摘要

基于彻体力模型的基本思想

发展了一套能够反映进气畸变对风扇/压气机气动性能影响的三维数值计算程序CSAC.首先详细研究了彻体力模型的具体建模方法

然后发展了相应的三维数值计算程序.利用该程序针对某单级跨声速压气机在均匀进气下的流场进行了计算验证

计算结果与雷诺平均Navier-Stokes(RANS)计算吻合得很好

流场主要参数分布与相关实验数据也有很好的一致性.利用该程序分别计算分析了进口存在稳态周向总压畸变及周向总温畸变的全环三维畸变流场

结果表明:压气机进口畸变流场存在大尺度、强三维特征

将导致压气机总压比及稳定裕度下降.所有计算结果均显示该模型能够在降低对计算资源和工程经验依赖的同时

有效分析进气畸变对压气机特性的影响.

Abstract

A three-dimensional numerical calculation code called CSAC based on body force model was developed and used to predict fan/compressor performance with inlet distortion. First

the modeling method to build body force model was studied. Then

a three-dimensional numerical calculation code was developed. A single-stage transonic compressor flow field with clean inlet was simulated with the code. The calculation results agreed well with the solutions of Reynolds-averaged Navier-Stokes(RANS) and experimental data. The compressor flow field with inlet steady circumferential total pressure distortion and circumferential total temperature distortion were simulated respectively with the code. The results showed that the flow field with inlet distortion in compressor had large scale and strong three-dimensional features

which led to the decrease of compressor total pressure ratio and stability margin. All results show that this model can effectively analyze the effect of inlet distortion on compressor while reducing the dependency on computational resources and engineering experience.

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Related Author

郭晋

胡骏

屠宝锋

尹超

金海良

银越千

LIU Yong-quan

LIU Huo-xing

Related Institution

南京航空航天大学能源与动力学院江苏省航空动力系统重点试验室

先进航空发动机协同创新中心

中国航空发动机集团湖南动力机械研究所

Shenyang Aeroengine Design and Research Institute, Aviation Industry Corporation of China

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

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