• CN:11-2187/TH
  • ISSN:0577-6686

机械工程学报 ›› 2025, Vol. 61 ›› Issue (7): 349-360.doi: 10.3901/JME.2025.07.349

• 机械动力学 • 上一篇    下一篇

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柔性转子-辅助支承系统过临界动力学特性研究

马新星1,2, 张振果1,2, 李坚3, 曹鹏3, 华宏星1,2   

  1. 1. 上海交通大学振动、冲击、噪声研究所 上海 200240;
    2. 上海交通大学机械系统与振动全国重点实验室 上海 200240;
    3. 中国航发湖南动力机械研究所 株洲 412000
  • 收稿日期:2024-04-05 修回日期:2024-10-19 发布日期:2025-05-12
  • 作者简介:马新星,男,1993年出生,博士后。主要研究方向为转子动力学及振动控制。E-mail:xinxingma@sjtu.edu.cn
    张振果(通信作者),男,1985年出生,博士,副教授,博士研究生导师。主要研究方向为接触摩擦动力学及振动可靠性、智能结构/功能材料动力学与声振控制。E-mail:zzgjtx@sjtu.edu.cn
  • 基金资助:
    国家自然科学基金(52405121,52241501,51975354)和直升机传动系统能力提升预研专项资助项目。

Study on the Overcritical Dynamic Characteristics of Flexible Rotor-auxiliary Support System

MA Xinxing1,2, ZHANG Zhenguo1,2, LI Jian3, CAO Peng3, HUA Hongxing1,2   

  1. 1. Institute of Vibration, Shock and Noise, Shanghai Jiao Tong University, Shanghai 200240;
    2. State Key Laboratory of Mechanical System and Vibration, Shanghai Jiao Tong University, Shanghai 200240;
    3. AECC Hunan Aviation Power Plant Research Institute, Zhuzhou 412000
  • Received:2024-04-05 Revised:2024-10-19 Published:2025-05-12

摘要: 直升机超临界尾传动水平轴系面临过临界共振问题,现有的限幅装置无法有效规避剧烈碰摩,可能导致传动轴系振动超限,亟需开展尾传动轴系新型限幅装置设计和过临界动力学特性分析。为此,设计了一种柔性轴系辅助支承,以Jeffcott转子-辅助支承为研究对象,根据有限元方法及接触理论分别建立系统动力学模型及转轴-缓冲环碰摩力模型。对不同参数下转子升速幅频响应进行了数值模拟,通过轴心轨迹、分岔图及三维频谱图分析了接触诱发的非线性动力学特性。开展了辅助支承原理样机设计,通过实验验证了辅助支承抑制转子过临界共振的有效性,最大振幅可降低70%以上。结果表明,所设计的辅助支承具有良好的振动抑制效果,其性能受到间隙、板簧刚度及接触刚度等参数影响,通过刚度切换机制,可以显著降低转子过临界幅值,该研究可为直升机尾传动轴系减振设计提供理论指导。

关键词: 转子动力学, 辅助支承, 振动抑制, 碰摩, 非线性

Abstract: The helicopter supercritical taildrive horizontal shaft system facing overcritical resonance problems, and the existing amplitude-limit device fails to effectively avoid the violent rubbing, which may lead to the vibration of the tail drive shaft exceeding the limit, and there is an urgent need to carry out the design of a new limiting device for the tail drive shaft system and the analysis of the overcritical dynamic characteristics. To this end, a flexible shaft auxiliary support is designed, and the Jeffcott rotor-auxiliary support is taken as the research object, and the system dynamics model and the shaft-snubber ring rubbing force model are established according to the finite element method and contact theory respectively. A numerical simulation of the amplitude-frequency response of the rotor run-up under different parameters is carried out, and the contact-induced nonlinear dynamics are analyzed through the shaft orbits, bifurcation diagram, and three-dimensional spectrogram. The principle prototype design of the auxiliary support is developed, and the effectiveness of the protection bearing in suppressing the rotor over-critical resonance is verified through experiments, and the maximum amplitude could be reduced by more than 70%. The results show that the designed auxiliary support has a good vibration suppression effect, and its performance is affected by parameters such as clearance, leaf spring stiffness, and contact stiffness, and the rotor over-critical amplitude can be significantly reduced through the stiffness switching mechanism, and the study can provide theoretical guidance for the design of helicopter tail drive shaft system vibration reduction.

Key words: rotordynamics, auxiliary support, vibration suppression, rubbing, nonlinear

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