航空发动机整机振动耦合动力学模型及其验证

陈果

航空发动机整机振动耦合动力学模型及其验证

陈果

南京航空航天大学民航学院, 南京 210016

基金项目: 国家自然科学基金(50705042); 航空科学基金(2007ZB52022); 国家安全重大基础研究项目(613139)

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- 文章访问数: 1991
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出版历程
- 收稿日期: 2011-03-07
- 修回日期: 2011-06-23
- 刊出日期: 2012-02-28

A coupling dynamic model for whole aero-engine vibration and its verification

CHEN Guo

College of Civil Aviation College, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 针对航空发动机整机振动,建立了一种通用的复杂转子-支承-机匣耦合动力学模型.在模型中,利用有限元方法对转子和机匣系统进行建模.支承系统采用集总参数模型,计入了滚动轴承和挤压油膜阻尼器的非线性,定义了多种支承和连接方式,以适应多转子和多机匣的复杂结构建模.运用数值积分获取系统非线性动力学响应.针对两个实际的航空发动机转子实验器,建立了整机耦合动力学模型,进行了整机模态实验验证,结果表明了航空发动机整机振动耦合动力学建模方法的正确有效性.
- 航空发动机 /
- 整机振动 /
- 耦合动力学 /
- 数值仿真 /
- 有限元 /
- 模态分析
Abstract: In order to study the whole aero-engine vibration,a generalized complex rotor-support-casing coupling dynamic model was established.In the model,the rotor and casing systems were modeled by means of the finite elements method;the support systems were modeled by the lumped parameter model,and the nonlinear factors of ball bearings and the squeeze film dampers were also included;the complex structures with multi-rotor and multi-casing was considered.A numerical integral method was used to obtain the system responses.Two aero-engine rotor testers were designed to verify the new model.The coupling dynamic model was established for the tester according to the new method,and the modal tests were carried out.The computation results were compared with the experiments results.The results indicate the effectiveness of the new method.
- aero-engine /
- whole aero-engine vibration /
- coupling dynamic /
- numerical simulation /
- finite element analysis /
- model analysis

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参考文献(12)

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