两级低速轴流压气机内周向总压畸变特征变化

成文韬; 刘永文

doi:10.19805/j.cnki.jcspe.2025.240023

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两级低速轴流压气机内周向总压畸变特征变化

动力设备与系统 | 更新时间：2026-01-27

- 两级低速轴流压气机内周向总压畸变特征变化
- Characteristics of Circumferential Total Pressure Distortion in a Two-stage Low-speed Axial Compressor
- 动力工程学报 2025年45卷第4期页码：514-521
- 作者机构：
  
  上海交通大学机械与动力工程学院,上海,200240
- 作者简介：
  
  [ "成文韬(1999—),男,四川广安人,硕士研究生,研究方向为叶轮机械、流体力学,E-mail:wtcheng99@sjtu.edu.cn" ]
- 基金信息：
  
  航空发动机及燃气轮机基础科学中心资助项目(P2021-A-I-003-002)
- DOI：10.19805/j.cnki.jcspe.2025.240023
  中图分类号： TK471
- 网络出版：2025-04-28，
  
  纸质出版：2025
- 稿件说明：
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成文韬,刘永文. 两级低速轴流压气机内周向总压畸变特征变化动力工程学报, 2025, 45(4): 514-521 https://doi.

org/10.19805/j.cnki.jcspe.2025.240023
成文韬,刘永文. 两级低速轴流压气机内周向总压畸变特征变化动力工程学报, 2025, 45(4): 514-521 https://doi. DOI： 10.19805/j.cnki.jcspe.2025.240023.

org/10.19805/j.cnki.jcspe.2025.240023 DOI：

摘要

轴流压气机在实际运行过程中面临复杂的进气畸变情况

其中周向总压畸变能够严重地降低其性能和气动稳定性。为此

以某台带进口导叶的两级低速轴流压气机为对象

依据国内关于轴流压气机总压畸变试验的规范

使用畸变挡板制造总压畸变

通过试验和数值模拟计算了总压畸变对压气机性能的影响。针对压气机内周向压力分布受叶片扰动影响的特点

提出用傅里叶分析的方法量化描述周向畸变特征

分析了周向总压畸变在压气机内沿轴向的发展情况

包括畸变的强度、相位、范围和径向位置等。结果表明:在远离失速工况时

畸变强度在经过各级叶珊后均大幅下降

但在近失速时没有明显的下降;畸变区域在经过两级动叶的做功后会沿着转动方向偏转一定角度;越往下游

畸变强度最大的区域越靠近叶尖部位;在近失速工况

畸变强度最大的区域出现在叶尖部位

且在第一级叶尖处观察到严重的不稳定流动现象

如叶顶泄漏流和二次流动

这加剧了畸变的程度。

Abstract

Axial flow compressors always face complex inlet distortion conditions during actual operation

among which circumferential total pressure distortion can significantly degrade the performance and aerodynamic stability. To address this issue

a two-stage low-speed axial flow compressor with inlet guide vanes was used as the research object. A distortion baffle was used to create total pressure distortion according to the domestic standards for total pressure distortion tests of axial flow compressors. The impact of total pressure distortion on compressor performance was investigated through experiments and numerical simulations. A method using Fourier analysis was proposed to quantitatively describe the circumferential distortion characteristics

since the circumferential pressure distribution within the compressor was affected by blade disturbances. The development of circumferential total pressure distortion along the axial direction within the compressor was analyzed

including the intensity

phase

extent

and radial position of the distortion. Results show that the intensity of distortion decreases significantly after passing through each stage of the blade under conditions far from stall

while no noticeable decrease is observed under near-stall conditions. The distortion zone deflects a certain angle along the rotation direction after passing through the two stages of the rotor blades. The closer it is to the downstream

the closer the maximum distortion zone is to the blade tip. Under near-stall condition

the maximum distortion zone appears at the blade tip

and serious unstable flow phenomena

such as tip leakage flow and secondary flow

is observed at the first-stage blade tip

which exacerbates the degree of distortion.

关键词

Keywords

references

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