基于分岔理论的轴流式压气机旋转失速主动控制技术

王健; 李应红; 张东方; 汪诚

基于分岔理论的轴流式压气机旋转失速主动控制技术

空军工程大学工程学院, 西安 710038

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出版历程
- 收稿日期: 2006-06-09
- 修回日期: 2006-11-03
- 刊出日期: 2007-07-28

Investigation on active control of rotating stall in axial flow compressors via bifurcation theory

The Engineering Institute, Air Force Engineering University, Xi'an 710038, China

摘要

摘要: 旋转失速是轴流式压气机的一种基本气动不稳定工作现象, 首先通过对Moore-Greitzer压缩系统模型的非线性动力学分岔分析, 发现旋转失速是由亚临界的音叉分岔所造成;其次提出了一种基于分岔理论的非线性主动控制算法, 采用压气机压比作为输入测量信号, 节流阀位置作为输出激励信号;最后采用分岔软件AUTO进行了计算机数值仿真, 仿真结果表明, 提出的非线性主动控制算法使得音叉分岔由亚临界转变为超临界, 从而消除了旋转失速迟滞环, 以及扩大了压气机的稳定工作范围.此外, 由于控制系统仅仅需要一维布局的传感器和激励器, 因此同时具备了较好的工程应用前景.
- 航空、航天推进系统 /
- 旋转失速 /
- Moore-Greitzer压缩系统模型 /
- 音叉分岔 /
- 迟滞环
Abstract: Rotating stall is a fundamental aerodynamic instability phenomenon of axial flow compressors.Firstly,the results of nonlinear dynamic bifurcation analysis on Moore-Greitzer compression system model showed that rotating stall was induced by subsonic pitchfork bifurcation;secondly,an active nonlinear feedback control law was proposed which using compressor pressure ratio as input measuring signal and throttle valve position as output actuating signal;Finally,computer simulation in bifurcation software AUTO was carried,and the simulation results showed that the proposed active nonlinear feedback control law translated the pitchfork bifurcation from subsonic to supersonic,which could eliminate the hysteresis loop associated with rotating stall and extend the stable operating range of axial flow compressors.Moreover,the proposed control system only used 1-dimensional sensor and actuator,so it could be easily applied in the engineering field.
- aerospace propulsion system /
- rotating stall /
- Moore-Greitzer compression system model /
- pitchfork bifurcation /
- hysteresis loop

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参考文献(5)

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