连接结构刚度非对称对高速转子动力特性影响

王东; 韩卓荦; 杨哲夫; 王永锋; 马艳红

doi:10.13224/j.cnki.jasp.20220995

连接结构刚度非对称对高速转子动力特性影响

doi: 10.13224/j.cnki.jasp.20220995

王东^{1, 3,},
韩卓荦²,
杨哲夫²,
王永锋^2,*, ,,
马艳红³

1.
中国航发沈阳发动机研究所，沈阳 110015
2.
北京航空航天大学能源与动力工程学院，北京 102206
3.
北京航空航天大学航空发动机研究院，北京 102206

基金项目: 国家重大科技专项（2017-Ⅳ-0011-0048, 2017-Ⅶ-0010-0104）；国家自然科学基金（52075018）

详细信息

作者简介:
王东（1983-），男，研究员，主要从事航空发动机结构设计及整机动力学研究。E-mail：2518916108@qq.com

通讯作者:
王永锋（1992-），男，博士，主要研究方向为航空燃气轮机结构动力学与振动控制。E-mail：wangyongfeng@buaa.edu.cn

中图分类号: V231.96
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出版历程
- 收稿日期: 2022-12-30
- 网络出版日期: 2024-06-14

Influence of unsymmetrical stiffness of joints on high-speed rotor dynamic characteristics

WANG Dong^{1, 3
,},
HAN Zhuoluo²,
YANG Zhefu²,
WANG Yongfeng^{2,*
, ,},
MA Yanhong³

1.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
2.
School of Energy and Power Engineering，Beihang University，Beijing 102206，China
3.
Research Institute of Aero-Engine，Beihang University，Beijing 102206，China

摘要

摘要:
针对界面连接转子系统的弯曲刚度非对称性产生机理及其对动力响应影响问题，基于欧拉-伯努利梁理论，提出了考虑转子非协调涡动影响的界面连接刚度非对称性的有限元素建模方法，并在带有中介轴承的双转子系统上开展了仿真与试验验证。结果表明：由于转子间交互激励作用，双转子系统产生非协调涡动，在相应的转子动力响应频谱中将出现明显的转速组合频率，而当组合频率靠近双转子共振模态频率时，转子非协调涡动程度加剧、组合频率幅值加大，可能对转子及支承结构造成严重损伤。
- 螺栓连接 /
- 界面损伤 /
- 刚度非对称 /
- 双转子系统 /
- 组合共振
Abstract:
A breathing model considering the effect of rotor whirl motion was established. Based on the Euler beam theory, a lumped parameter modeling method of the dual-rotor system taking asymmetric joint stiffness into account was proposed, and experiments on an aero-engine dual-rotor system supported by intermediate bearing was conducted. The results showed that the combination of two excitation frequencies appeared in the rotor response spectrum. The amplitude of the combination frequency could increase when the rotational speed was in the vicinity of the coupled vibration modes frequency, which may damage the supporting structures.
- bolted joints /
- interface damage /
- asymmetric stiffness /
- dual-rotor system /
- combined resonance

HTML

图 1 航空发动机转子典型法兰-螺栓连接结构图

Figure 1. Schematic diagram of typical bolted joints in aero-engine rotor systems

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图 2 变工况螺栓连接不可恢复变形

Figure 2. Unrecoverable deformation of bolted joints under variable working conditions

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图 3 不同损伤情况下单排螺栓周向剩余预紧载荷分布

Figure 3. Circumferential residual bolt preload distribution of a single row under different damage circumstances

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图 4 不同弯曲力矩下连接结构的弯曲刚度$k$周向分布

Figure 4. Circumferential distribution of bending stiffness $k$ of bolted joint under different loads

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图 5 非对称刚度示意图

Figure 5. Schematic diagram of the asymmetric stiffness

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图 6 后续用于研究的椭圆形刚度$k$分布

Figure 6. Circumferential distribution of bolted joint stiffness $k$ for investigation

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图 7 典型带有中介轴承的航空发动机双转子结构

Figure 7. Typical aero-engine dual-rotor structure designed with inter-shaft bearing

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图 8 双转子系统集总参数模型

Figure 8. Lumped parameter model of the dual-rotor system

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图 9 5#支点的响应特征（LP 6600, HP 10000）

Figure 9. Dynamic behavior of the 5# support（LP 6600, HP 10000）

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图 10 5#支点的响应特征（LP 9000, HP 12240）

Figure 10. Dynamic behavior of the 5# support （LP 9000, HP 12240）

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图 11 5#支点的响应特征（LP 9300, HP 12460）

Figure 11. Dynamic behavior of the 5# support （LP 9300, HP 12460）

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图 12 双转子系统模态振型（模态频率为96.2 Hz）

Figure 12. Modal shape of the dual-rotor system （modal frequency is 96.2 Hz）

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图 13 不同非对称程度的频域特征

Figure 13. Frequency spectrum characteristic of different asymmetric distribution conditions

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图 14 装配中预设的螺栓预紧力分布

Figure 14. Preload distribution of the studied bolted joint during assembling

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图 15 均匀预紧力时转子系统响应频谱图

Figure 15. Frequency spectrum response of the dual rotor system with symmetric bolt preloads

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图 16 双转子系统试验频谱瀑布图

Figure 16. Frequency spectrum waterfall diagram of the dual-rotor system experiment

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图 17 转子5#支点频谱图

Figure 17. Frequency spectrum of bearing 5# in the experiment of the dual rotor system

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表 1 试验螺栓连接结构参数

Table 1. Parameters of the investigated bolted jointed

参数数值

螺栓公称直径/mm 10
螺栓安装半径/mm 156.0
螺栓个数 24
螺距/mm 1.5
最小预紧力/N 20000
最大预紧力/N 33000

下载: 导出CSV

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