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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。
Aeroengine in the process of work to increase the amount of vibration and accompanied by a certain amount of interface wear problem, based on the structural characteristics of the established three-disc rotor-bearing system dynamics model, and the contact end surface coaxiality deviation and parallelism Based on the Lagrange equation, the dynamic differential equation of the rigid-rotor system considering the interface deformation is obtained. The results show that the interface deformation will make the rotor produce additional excitation force. The amplitude of the additional excitation force caused by the coaxiality deviation is proportional to the square of the rotation speed and only acts on the corresponding degree of freedom. The additional excitation caused by the parallelism deviation The force amplitude is only related to the system stiffness and parallelism deviation, and has nothing to do with the speed, and there is a certain component in the direction of bearing freedom.