Bifurcation on synchronous full annular rub of rigid-rotor elastic-support system
Bifurcation on synchronous full annular rub of rigid-rotor elastic-support system
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DOI：
10.1007/s10483-012-1591-7
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发表时间：
2012-07
影响因子：
--
通讯作者：
Hua Zhang;Yushu Chen;Jun Li
中科院分区：
文献类型：
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作者：
Hua Zhang;Yushu Chen;Jun Li
根据航空发动机转子系统的特点，将其简化为具有非线性弹性支承的非对称刚性转子系统。从拉格朗日方程出发，用平均化方法求解碰摩系统的控制方程，得到系统的分叉方程。然后，根据二维约束分叉理论，分别给出了有碰摩和无碰摩系统的转移集和分岔图，研究了系统偏心和阻尼对分叉行为的影响。最后，根据Lyapunov稳定性理论，确定了系统稳态碰摩解的稳定域、静态分叉边界和Hopf分叉，讨论了系统参数对系统运动演化的影响。研究结果可为航空旋翼系统的设计提供一定的参考。
An aero-engine rotor system is simplified as an unsymmetrical-rigid-rotor with nonlinear-elastic-support based on its characteristics. Governing equations of the rubbing system, obtained from the Lagrange equation, are solved by the averaging method to find the bifurcation equations. Then, according to the two-dimensional constraint bifurcation theory, transition sets and bifurcation diagrams of the system with and without rubbing are given to study the influence of system eccentricity and damping on the bifurcation behaviors, respectively. Finally, according to the Lyapunov stability theory, the stability region of the steady-state rubbing solution, the boundary of static bifurcation, and the Hopf bifurcation are determined to discuss the influence of system parameters on the evolution of system motion. The results may provide some references for the designer in aero rotor systems.