| 突加基础冲击激励下转子系统振动特性试验 |
| |
| 引用本文： | 陈伟,吴泽宇,韩佳奇,刘璐璐,罗刚,赵振华.突加基础冲击激励下转子系统振动特性试验[J].航空动力学报,2023,38(4):878-888. |
| |
| 作者姓名： | 陈伟 吴泽宇 韩佳奇 刘璐璐 罗刚 赵振华 |
| |
| 作者单位： | 1.南京航空航天大学 能源与动力学院航空发动机热环境与热结构工业和信息化部重点实验室，南京 210016 |
| |
| 基金项目： | 国家科技重大专项（2017-Ⅳ-0006-0043) |
| |
| 摘 要： | 针对着舰过程中航空发动机转子系统受到的突加基础冲击激励的问题，基于典型小涵道比涡扇发动机结构特征相似原则设计转子-支承-机匣系统试验器，对突加基础冲击激励下转子系统振动特性进行试验研究。结果表明：突加基础冲击激励瞬时具有显著的冲击效应，转子系统瞬态振动响应加剧并激起转子的正反进动和横向振动模态。转子系统轮盘处振幅比随基础冲击速度的增加而非线性增长，突加纵向基础冲击激励比突加横向基础冲击激励更能影响转子系统的振动特性。
|
| 关 键 词： | 转子系统 基础激励 振动试验 瞬态响应 轴心轨迹 |
| 收稿时间： | 2021-09-24 |
Test on vibration characteristics of rotor system under sudden base shock excitation |
| |
| Institution: | 1.Aero-engine Thermal Environment and Structure Key Laboratory of Ministry of Industry and Information Technology，College of Energy and Power Engineering， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China2.State Key Laboratory of Mechanics and Control of Mechanical Structures， Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China |
| |
| Abstract: | A rotor-supporting-casing system test rig was designed to investigate the vibration response of turbofan rotor in time domain and frequency domain under sudden base shock excitation during the process of landing, based on the equivalence principle of structural characteristics of the typical low bypass ratio turbofan engine. Results showed that sudden base shock excitation led to significant impact on rotor, the aggravation of rotor’s transient response, the positive and negative precession and flexural resonance. The amplitude ratio of the disk of rotor system increased nonlinearly with the increase of the impact velocity of base, and the longitudinal sudden base shock excitation had more influence on the vibration characteristics of the rotor system than the transverse sudden base shock excitation. |
| |
| Keywords: | |
|
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
