Numerical Study on the Influence of Small Inlet Distortion on the Aerodynamic Performance of the Compressor

YAN Song; ZHUO Liang; SHI Daolong; LAN Xiaobing; CHU Wuli

doi:10.19805/j.cnki.jcspe.2025.240236

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Numerical Study on the Influence of Small Inlet Distortion on the Aerodynamic Performance of the Compressor

更新时间：2026-10-10

- Numerical Study on the Influence of Small Inlet Distortion on the Aerodynamic Performance of the Compressor
- Chinese Journal of Power Engineering Vol. 45, Issue 7, Pages: 968-976(2025)
- 作者机构：
  
  1. 贵州航天林泉电机有限公司国家精密微特电机工程技术研究中心,贵州,贵阳,550081
  2. 西北工业大学动力与能源学院,陕西,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.19805/j.cnki.jcspe.2025.240236
  CLC：
- Online First：14 July 2025，
  
  Published：2025
- 稿件说明：
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晏松,卓亮,施道龙,兰小兵,楚武利. 进口微小畸变对压气机气动性能影响的数值研究动力工程学报, 2025, 45(7): 968-976 https://doi.

org/10.19805/j.cnki.jcspe.2025.240236
晏松,卓亮,施道龙,兰小兵,楚武利. 进口微小畸变对压气机气动性能影响的数值研究动力工程学报, 2025, 45(7): 968-976 https://doi. DOI： 10.19805/j.cnki.jcspe.2025.240236.

org/10.19805/j.cnki.jcspe.2025.240236 DOI：

摘要

利用数值模拟方法研究了径向进气方式产生的微小进口畸变强度对轴流压气机气动性能的影响。结果表明:径向进气方式会造成轴流压气机进口最大产生1.50%的总压畸变强度

并使得轴流压气机的失速裕度和峰值效率分别降低1.64%和0.66%;随着转子节流过程的进行

进口总压畸变强度越来越小

但对轴流压气机气动性能的影响越来越大;径向进气方式所产生的进口微小畸变使得叶顶区域来流速度降低

削弱了叶顶来流对叶顶泄漏流的影响

从而使得叶顶泄漏涡在转子节流过程中提前发生螺旋式破碎

导致叶顶区域的流通能力恶化

且叶顶区域的流动损失增加

从而使得转子的气动性能下降。

Abstract

A numerical simulation method was used to study the influence of small inlet distortion intensity caused by radial intake on the aerodynamic performance of axial flow compressor. Results show that the radial intake mode can cause a maximum total pressure distortion intensity of 1.50% at the inlet of the axial flow compressor

and reduce the stall margin and peak efficiency of the axial flow compressor by 1.64% and 0.66% respectively. During the rotor throttling process

the total pressure distortion intensity at the inlet becomes smaller

but the influence on the aerodynamic performance of the axial flow compressor becomes greater. The small inlet distortion caused by radial intake makes the inflow velocity in the blade tip region decrease

which weakens the influence of the inflow on the blade tip leakage flow

so that the tip leakage vortex spirally breaks in advance during the rotor throttling process

resulting in the deterioration of flow capacity in the tip region

and the flow loss in the tip region increases

thus reducing the aerodynamic performance of the rotor.

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Keywords

references

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