摘要
针对航空发动机在工作过程中振动量增大且伴随有一定的界面磨损问题,在结构特征分析的基础上建立了三盘转子-支承系统动力学模型,并将接触端面同轴度偏差以及平行度偏差进行参数化描述,基于Lagrange方程得到考虑界面变形的高压刚性转子系统动力学微分方程。结果表明,界面变形将使得刚性转子系统产生附加激振力,同轴度偏差引起的附加激振力幅值与转速平方成正比,仅作用在相应自由度上;平行度偏差引起的附加激振力幅值仅与系统刚度和平行度偏差量有关,与转速无关,且其在支承自由度方向上存在一定分量。
In order to analyze the problems of vibration increasing and interface wear of aero engine during work,the dynamic models of rotor-bearing system with three disks were established on the basis of the structural feature analysis. A parametric description has been made to analyze the coaxial and parallelism deviation of contact interface,and the dynamic differential equation for rigid high pressure rotor system was obtained by the Lagrangian method considering the interface deformation. The results exhibit that the interface deformation will cause the additional excitation force in the rigid rotor system,where the amplitude of the additional excitation force caused by the coaxial deviation is proportional to the square of the speed,and only applies to the corresponding degree of freedom; the amplitude of the additional excitation force caused by the parallelism deviation is only related with the rigidity and the deviation magnitude regardless of the speed,and it also applies to the support freedom.
作者
金海
刘继兴
张大义
洪杰
JIN Hai;LIU Jixing;ZHANG Dayi;HONG Jie(School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;AECC Shenyang Engine Design and Research Institute, Shenyang 110015, China;Collaborative Innovation Center of Advanced Aero-Engine, Beijing 100083, China)
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2018年第6期1294-1302,共9页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金(51575022
51475021)~~
