Experimental study of the mechanism of improving stall margin of low speed axial-flow compressor with micro-injection under rotating inlet distortion

ZHANG Jing-xuan; LUO Ma; NIE Chao-qun; LIN Feng; CHEN Jing-yi

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Experimental study of the mechanism of improving stall margin of low speed axial-flow compressor with micro-injection under rotating inlet distortion

更新时间：2026-07-07

- Experimental study of the mechanism of improving stall margin of low speed axial-flow compressor with micro-injection under rotating inlet distortion
- Vol. 25, Issue 1, (2010)
- 作者机构：
  
  1. 北京航空航天大学能源与动力工程学院,北京,100191
  2. 中国航空工业集团公司中国航空动力机械研究所,株洲,412002
  3. 中国科学院工程热物理研究所,北京,100190
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2010
- 稿件说明：
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ZHANG Jing-xuan, LUO Ma, NIE Chao-qun, et al. Experimental study of the mechanism of improving stall margin of low speed axial-flow compressor with micro-injection under rotating inlet distortion[J]. 2010, 25(1).
DOI：

ZHANG Jing-xuan, LUO Ma, NIE Chao-qun, et al. Experimental study of the mechanism of improving stall margin of low speed axial-flow compressor with micro-injection under rotating inlet distortion[J]. 2010, 25(1). DOI：

摘要

对旋转畸变条件下轴流压气机的失稳特性进行了实验研究

结果表明

畸变影响区内叶顶泄漏流的前缘溢出造成了旋转失速的提前发生

缩减了压气机的失稳裕度.叶顶微喷气方法有效地提高了旋转畸变条件下轴流压气机的失稳裕度

其原因在于

实施叶顶微喷气后

临近失速时

压气机顶部畸变区诱发的分离团受到抑制

减少了其诱发旋转失速的可能性

从而实现扩稳目的.

Abstract

An experimental investigation was carried out in the paper to clarify the flow mechanism of how micro-injection improves the stall margin of a low speed axial-flow compressor under rotating inlet distortion.The results show that

in distorted sectors

the tip leakage flow is pushed forward to the leading edge;as the mass flow rate is decreased

tip leakage flow would spill out of the blade passage and trigger the rotating stall.Micro-injection can inhibit the formation of distortion disturbances and then delay the occurrence of rotating stall.

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Related Institution

华中科技大学能源与动力工程学院

先进航空发动机协同创新中心

北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室

Collaborative Innovation Center for Advanced Aero-Engine

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

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