变转速动力涡轮转子模拟系统设计及试验  

Design and experiment of variable speed power turbine rotor simulation system

作　　者：张羽薇 王四季[1] 张晋琪 王虎 廖明夫[1] ZHANG Yuwei;WANG Siji;ZHANG Jinqi;WANG Hu;LIAO Mingfu(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2025年第1期326-338,共13页Journal of Aerospace Power

摘　　要：针对变转速涡轮转子工况复杂、振动突出的问题,建立变转速动力涡轮转子支承布局和挤压油膜阻尼器优化设计技术。基于结构相近、动力学相似的理论,设计搭建了模拟某型发动机的转子试验系统,实现对优化设计方案下的临界转速分布、振型模态与转子振动响应特性验证。开展了阻尼器结构参数的减振特性分析,为变转速动力涡轮转子的挤压油膜阻尼器设计提供支撑。研究结果表明:转子试验系统临界转速计算最大误差为5%,模态振型最大误差为7%,验证了动力学特性计算方法的准确性。通过进行转子支承结构和阻尼器优化,转子振动幅值下降67.3%,变转速工作范围内运行更平稳,验证了所提出的变转速动力涡轮转子减振方案的有效性,为变转速涡轴发动机动力涡轮转子动力学方案和减振设计提供参考。In view of the complex working conditions and prominent vibration of the variable speed turbine rotor,the optimization design technology of the variable speed power turbine rotor support layout and squeeze film damper was established.Based on the theory of similar structure and dynamics,a rotor experimental system simulating a certain type of engine was designed and built to verify the critical speed distribution,vibration mode and rotor vibration response characteristics under each scheme.The experimental analysis of the impact of damper structural parameters was carried out to provide support for the design of squeeze film damper of variable speed power turbine rotor.The research results showed that the maximum error in calculating the critical speed of the rotor experimental system was below 5%,and the maximum error in modal vibration mode was below 7%,which verified the accuracy of the dynamic characteristics calculation method.Through optimization of the rotor support structure and damper,the vibration amplitude of the rotor was reduced by 67.3%,and the operation was more stable within the working range of variable speed,which verified the effectiveness of the proposed variable speed turbine rotor vibration reduction scheme,thus laying a foundation for the dynamic design experimental verification research.

关 键 词：变转速涡轮转子 支承布局 挤压油膜阻尼器 试验分析 减振 

分 类 号：V231.92[航空宇航科学与技术—航空宇航推进理论与工程]