摘要
为解决航空发动机双转子系统无法避开临界转速的问题,提高双转子系统容忍振动的能力,根据带中介轴承双转子系统的“可容模态”优化设计方法,以某型带中介轴承双转子发动机相似模型为初始模型进行优化设计,并以此搭建一套双转子实验器系统。通过模态测试、响应测试、连续变转速以及长时间“共振”实验,先后验证了带中介轴承双转子系统的“可容模态”优化设计方法的准确性、有效性、稳定性和可靠性。研究发现,双转子实验器测试结果与计算结果临界转速误差最高3.06%、模态振型误差最高9.6%;工作范围内任意转速下,即使频繁穿越临界转速,振动幅值均不超过50µm;在6阶临界转速处各完成了不少于3790s的“共振”实验,所容忍的不平衡量最大为设计不平衡量的5.2倍,振幅平稳,且可容度评价函数值越高,容忍共振能力越强。实验结果充分验证了带中介轴承双转子系统的“可容模态”优化设计方法是可行的。
In order to solve the problem that the dual-rotor system of aero-engine cannot avoid the critical speed,and improve the vibration tolerance of the dual-rotor system,according to the optimization design method for the workable mode of dual-rotor system with inter-shaft bearing,the similar model of a dual-rotor engine with inter-shaft bearing is used as the initial model for optimization design.Based on the optimization results,a dual-rotor test rig system was built.The accuracy,effectiveness,stability and reliability of the optimization de⁃sign method for the workable mode of dual-rotor system with inter-shaft bearing were verified by modal test,re⁃sponse test,continuous variable speed experiment and long time resonance experiment.According to research findings,the maximum error of the critical speed between the experimental results and the calculation results of the dual-rotor test rig system is 3.06%,and the maximum error of the modal shape is 9.6%.The vibration ampli⁃tude is less than 50µm at any speed even though the critical speed is frequently passed in the working range.The resonance experiments at the sixth critical speed are completed at no less than 3790s.The maximum tolerated amount of unbalance mass is 5.2 times the designed amount.The amplitude is stable,and the higher the tolerabil⁃ity evaluation function is,the higher the tolerance to resonance is.The results indicate that the established optimi⁃zation design method of workable mode for aero-engine dual-rotor system with inter-shaft bearing is effective.
作者
王瑞
廖明夫
雷新亮
程驰
王理
石斌
WANG Rui;LIAO Ming-fu;LEI Xin-liang;CHENG Chi;WANG Li;SHI Bin(College of Energy and Power,Northwestern Polytechnical University,Xi’an 710129,China;AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China;AECC Shenyang Engine Institute,Shenyang 110015,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2023年第5期240-256,共17页
Journal of Propulsion Technology
基金
国家科技重大专项(2017-Ⅳ-0001-0038)
关键词
航空发动机
双转子系统
可容模态
优化设计
实验验证
Aero-engine
Dual-rotor system
Workable mode
Optimization design
Experimental ver⁃ification
