油膜间隙对非同心型SFD-变转速转子系统动力特性的影响  

Effect of oil film clearance on dynamic characteristics of variable speed rotor with non-concentric SFD

作　　者：聂卫健 李坚 唐广 刘飞春 袁巍 NIE Weijian;LI Jian;TANG Guang;LIU Feichun;YUAN Wei(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Key Laboratory of Aero-engine Vibration Technology,Aero Engine Corporation of China,Zhuzhou 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中国航空发动机集团航空发动机振动技术重点实验室,湖南株洲412002

出　　处：《燃气涡轮试验与研究》2024年第6期1-8,共8页Gas Turbine Experiment and Research

基　　金：中国航发创新基金(CXPT-2022-031)。

摘　　要：为研究油膜间隙对非同心型挤压油膜阻尼器(NCSFD)-变转速转子系统动力特性的影响,以航空发动机变转速转子系统为研究对象,提出了转子动力学特性一致设计原则并设计了一套模拟转子,开展了不同油膜间隙下NCSFD-转子系统的动力特性分析和试验研究,结果表明模拟转子与真实转子的动力特性具有良好的一致性,0.10 mm的油膜间隙较为合理。此外,基于优选油膜间隙开展了转子系统的宽速域稳定性试验研究,结果表明转子在0.51n~1.00n(n为转子工作转速)范围内定转速下的振动位移变化量不超过4μm,振动加速度变化量不超过0.04g,具有较宽的稳定工作转速范围。本研究为航空发动机变转速转子工程设计和减振设计提供了参考。To study the influence of different oil film clearances on the dynamic characteristicsof a non-concentric squeeze film damper(NCSFD)variable speed rotor system,the variable speed rotor system of an aero-engine was taken as the research object,the consistent design principle of rotor dynamic characteristics was put forward,and a simulated rotor was designed.Analysis and experimental study on the dynamic characteristics of the rotor under different oil film clearances were carried out.The results show that the dynamic characteristics of the simulated rotor and the real rotor are in good agreement.Besides,it has been found that a 0.1 mm oil film clearance is more reasonable.In addition,based on the optimized oil film clearance,research on the wide-speed domain of the rotor system was carried out.In the range of 0.51n to 1.00n,the vibration displacement change does not exceed 4μm,the vibration acceleration change does not exceed 0.04g,and the rotor runs stably within a wide working speed range.The study provides a reference for the engineering design and vibration reduction design of variable speed rotors in aircraft engines.

关 键 词：航空发动机 非同心型挤压油膜阻尼器 非线性 油膜间隙 转子动力学 

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]