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将挤压油膜阻尼器设计与转子动力学设计相结合,建立了航空发动机转子挤压油膜阻尼器设计方法和设计流程.转子参数为转子阻尼、临界转速配置、最大不平衡量、转子振动峰值,以及支承外传力等,挤压油膜阻尼器设计参数为轴颈偏心率、油膜半径间隙、油膜长度和鼠笼刚度.设计目标是控制转子临界峰值和支承外传力.其中转子阻尼与最大不平衡量为挤压油膜阻尼器设计的关键参数.利用一实验器,对该设计方法进行了数值仿真和实验验证,结果表明:转子振动响应临界峰值减振比例可达60%以上,说明所建立的设计方法是正确有效的,可为挤压油膜阻尼器设计提供指导.
Combining the design of squeeze film damper and rotor dynamics design, the design method and design flow of squeeze film damper of aeroengine rotor are established.The rotor parameters are the rotor damping, the critical speed configuration, the maximum imbalance, the rotor vibration peak, and Bearing external force, squeeze film damper design parameters for journal eccentricity, oil film radius gap, film length and squirrel cage stiffness.The design goal is to control the critical peak of the rotor and bearing external force which rotor damping and the maximum unbalanced amount of squeeze The key parameters of the design of the oil damper are discussed.The numerical simulation and experimental verification of this design method are carried out with an experimental instrument.The results show that the critical vibration damping ratio of the rotor can reach 60% or more, which shows that the design method Properly effective, can provide guidance for squeeze film damper design.