挤压油膜阻尼器转子系统突加不平衡瞬态响应分析  

Transient response analysis of squeezed film damper rotor system under sudden unbalance load

作　　者：何文博 潘豹 白杰 HE Wen-bo;PAN Bao;BAI Jie(Key Laboratory on Civil Aircraft Airworthiness and Maintenance,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学天津市民用航空器适航与维修重点实验室,天津300300

出　　处：《燃气涡轮试验与研究》2020年第1期36-40,共5页Gas Turbine Experiment and Research

基　　金：中央高校基金资助项目(No.3122017088)。

摘　　要：针对发动机转子在运转时可能发生叶片脱落故障,搭建了带挤压油膜阻尼器双盘转子模拟叶片脱落的转子实验台。对转子系统实验装置进行合理简化,利用仿真软件和实验测试验证了模型的合理性与有效性。仿真分析了转子系统参数和油膜参数对突加不平衡瞬态响应特性的影响。结果表明,油膜间隙、油膜长度和支承刚度比都会对加速响应特性产生影响,其中油膜间隙与振动响应幅值呈正相关,油膜长度与之呈负相关,支承刚度比与之关系不定;合理选择参数取值能够提升转子系统稳定性。It is possible that rotor blades might fall when engine runs.A rotor test bench with a squeeze film damper(SFD)was built to simulate falling of blades during operation.After simplifying the rotor sys tem,a simulation software and some tests were used to prove the availability of the model.The effect of rotor parameters and oil film parameters on unbalance transient response was analyzed.The results show that oil film clearance,oil film length and supporting stiffness ratio will affect the acceleration response characteris tics,and oil film clearance is positively correlated with the vibration response amplitude.The oil film length is negatively correlated with the vibration response amplitude.The correlation between supporting stiffness and vibration response amplitude is not clear.A reasonable choice of parameters can help to enhance rotor system stability.

关 键 词：航空发动机 悬臂转子 叶片脱落 挤压油膜阻尼器 瞬态响应 突加不平衡 

分 类 号：V231.96[航空宇航科学与技术—航空宇航推进理论与工程]