高速转子试验支座振动优化设计与验证  

Vibration optimization design and experiment for high-speed rotor test support

作　　者：聂卫健 邓旺群 唐虎标 刘文魁 庄周柱 NIE Weijian;DENG Wangqun;TANG Hubiao;LIU Wenkui;ZHUANG Zhouzhu(School of Energy and Power Engineering,Beihang University,Beijing 102206,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Key Laboratory of Aero-engineVibration Technology,Aero Engine Corporation of China,Zhuzhou 412002,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京102206 [2]中国航发湖南动力机械研究所,湖南株洲412002 [3]中国航空发动机集团航空发动机振动技术重点实验室,湖南株洲412002

出　　处：《燃气涡轮试验与研究》2023年第5期11-16,共6页Gas Turbine Experiment and Research

基　　金：中国航发创新基金(CXPT-2022-031)。

摘　　要：针对燃气发生器转子在动力特性试验过程中出现的转接支座振动加速度过大现象,开展原因分析和转接支座振动优化研究。采用有限元法建立了支座模态计算模型,得到前5阶模态振型和频率,确定支座在转子工作转速范围内存在多阶有害共振频率是振动过大的主要原因;设计了3种结构的试验支座并进行了对比分析,对优选支座分别进行了不带燃气发生器转子和带燃气发生器转子的试验验证。结果表明,优选支座在转子工作转速范围内不存在有害共振频率,高转速下的振动加速度大幅降低;研究成果为航空发动机转子动力学试验提供了保障,可推广至其他转子试验支座设计。In view of the phenomenon that the vibration acceleration of the adapter support was too large during the dynamic characteristic test of a gas generator rotor,the cause analysis and vibration optimization research of the adapter support were carried out.The finite element method was used to establish the support modal calculation model,and the first five stages modal vibration modes and frequencies were obtained.It was determined that the main reason for the excessive vibration of the support was that there were multiple harmful resonance frequencies within the operating speed range of the rotor.Three kinds of test support structure were designed and compared,and the preferred scheme was verified by tests with and without gas generator rotor respectively.The results indicate that the selected support does not have harmful resonance frequencies within the operating speed range of the rotor,and the vibration acceleration at high speeds is significantly reduced.The research provides a guarantee for the rotor dynamics test of aircraft engines and can be extended to the design of other test supports.

关 键 词：高速转子 试验支座 动力特性试验 振动模态 有限元 试验验证 航空发动机 

分 类 号：V231.96[航空宇航科学与技术—航空宇航推进理论与工程]