Effects of non-axisymmetric IGV wakes on a low speed axial compressor

LIU Jian-yong; LI Zhi-ping; LU Ya-jun; ZENG Tao

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Effects of non-axisymmetric IGV wakes on a low speed axial compressor

更新时间：2026-07-07

- Effects of non-axisymmetric IGV wakes on a low speed axial compressor
- Vol. 24, Issue 8, (2009)
- 作者机构：
  
  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重点实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
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LIU Jian-yong, LI Zhi-ping, LU Ya-jun, et al. Effects of non-axisymmetric IGV wakes on a low speed axial compressor[J]. 2009, 24(8).
DOI：

LIU Jian-yong, LI Zhi-ping, LU Ya-jun, et al. Effects of non-axisymmetric IGV wakes on a low speed axial compressor[J]. 2009, 24(8). DOI：

摘要

在轴对称尾流撞击实验的基础上

进行了多种非轴对称尾流撞击实验研究.当合理安排进口导叶的数目和周向分布形式时

进口导叶(IGV)的非轴对称尾迹能对下游转子流场产生有益的非定常耦合激励作用.与轴对称尾流撞击方案相比

非轴对称尾流撞击方案在保持了有益的高频激励信号的同时

引入了合适的低频方波激励信号和其他有益的副频激励信号

使得导叶尾迹更容易与压气机中的复杂涡系产生耦合激励作用

例如通道涡、间隙涡和尾迹分离涡等.实验结果显示

非轴对称尾流撞击方案B能使压气机的最高效率提高1.2%

总压升和稳定裕度也略有增加.

Abstract

Based on the axisymmetric wake impact experiment

several non-axisymmetric wake impact experiments were carried out.When the number and circumferential positions of inlet guide vanes(IGV) were logical

the wakes of non-axisymmetric IGVs could make beneficial unsteady excitation on downstream rotor field.In these experiments

some suitable non-axisymmetric wake impact plans worked better than the axisymmetric wake impact plan.As compared to the axisymmetric wake impact plan

the non-axisymmetric wake impact plan could supply multi-frequency exciting signals.In addition to the beneficial high-frequency signal

the non-axisymmetric plan B generated a low-frequency square-wave exciting signal and some beneficial secondary signals.Based on the unsteady cooperative flow theory

the exciting wakes in non-axisymmetric plan were easier to cooperate with complicated vortices in a compressor

such as clearance vortices

passage vortices and separated vortices.The non-axisymmetric wake impact plan B in this paper could make the max efficiency increase by 1.2%

total pressure rise and stall margin rise by a little.

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Related Author

LIU Jian-yong

YUAN Wei

LU Ya-jun

Jie GAO

Honghui XIANG

Senlin WU

Jun ZHANG

Zhenrong WEN

Related Institution

National Key Lab on Aero-Engine, School of Jet PropulsionBeijing University of Aeronautics and Astronautics

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

Sichuan Province Engineering Technology Research Center of Turbomachinery of Aero⁃engine and Gas Turbine

School of Aeronautics and Astronautics， Shanghai Jiao Tong University

Science and Technology on Altitude Simulation Laboratory,Sichuan Gas Turbine Establishment,Aero Engine Corporation of China

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