带挤压油膜阻尼器悬臂转子系统的突加不平衡响应分析  

Sudden Unbalance Response Analysis of Cantilever Rotor System with Squeeze Film Damper

作　　者：白杰 潘豹 何文博 BAI Jie;PAN Bao;HE Wen-bo(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：《科学技术与工程》2018年第24期299-305,共7页Science Technology and Engineering

基　　金：中央高校基金(3122017088)资助

摘　　要：以典型涡扇发动机带挤压油膜阻尼器(SFD)的低压悬臂转子结构为基础,通过合理简化模型,对转子系统中的轴承、挤压油膜阻尼器和突加不平衡量进行了相关分析和说明;并用实验得到前两阶临界转速结果验证模型的合理性;然后仿真模拟得到突加不平衡对旋转中的风扇盘在不同工况下的不平衡响应,其中包括在恒定转速下突加不平衡和转子在增速过程通过双稳态区域时施加不平衡时转子响应的特点。通过改变突加不平衡量的大小、相位和油膜间隙等影响因素来分析响应曲线的变化并得出结论。研究结果表明:在恒定转速下,系统参数的改变对突加不平衡有较大的影响;对于加速通过双稳态响应区,突加不平衡发生在不同转速区,不平衡响应走的路径也不同。Based on the low pressure cantilever rotor structure of a typical turbofan with squeeze film damper(SFD),do some analysis and description about the rotor system bearings,SFD and the sudden unbalance through reasonable simplified model,the rationality of the model through the first two natural frequencies obtained by experiment was verified.The simulation results show that sudden unbalance affect rotating disk unbalance response under different operating conditions,including sudden unbalance at constant rotating speed and the fan disk unbalance response during the rotor speed up through the bi-stable region.By changing the size of sudden unbalance,phase and oil film clearance and other influencing factors to analyze the response curve changes and draw conclusions that rotor system parameters have great influence on the sudden unbalance response at constant rotating speed.Depending on the starting rotating speed point of sudden unbalance,the response will follow the response route of large solution or small solution.

关 键 词：挤压油膜阻尼器 悬臂转子 双稳态 瞬态过程 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]