Page 150 - 《振动工程学报》2025年第9期
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第 38 卷第 9 期                       振 动 工 程 学 报                                       Vol. 38 No. 9
               2025 年  9 月                     Journal of Vibration Engineering                       Sept. 2025



                    带   初    始   弯   曲   柔   性    转   子   的   高   阶    无   附   加   试   重    平   衡   法



                             邓振鸿 , 罗华耿 , 邓旺群 , 聂卫健 , 林海东 , 张保强                                1
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               (1. 厦门大学航空航天学院,福建 厦门 361102; 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; 4. 北京航空航天大学能源与动力工程学院,北京 100191)
              摘要:在常规的低速平衡后,往往很难抑制柔性转子在高阶临界转速处的振动,尤其是存在初始弯曲的情况。本文介绍了一
              种针对初始弯曲柔性转子的低速动平衡方法,在不直接测量转子初始弯曲的情况下,结合转子的模态信息与低于临界转速下
              的测量与平衡数据,来估计抑制临界转速振动(包括初始弯曲和不平衡引起的)所需的不平衡校准量;在此基础上,针对高阶
              模态的平衡,提出了一种逐阶向前平衡的高阶无附加试重法,即利用不同平衡面上的低阶平衡配重作为试重,并结合测点模
              态比建立联系,从而避免了平衡高阶模态时因附加试重而破坏低阶临界转速的平衡。通过数值仿真和试验对所提方法进行
              了验证,结果表明,相比于传统的影响系数法,所提方法在所关心的转速域内有更好的振动抑制效果,且在保证平衡效果的同
              时避免了平衡测试过程中出现显著共振,提高了测量的安全性,从而为柔性转子的动平衡提供一种思路。
              关键词: 柔性转子;动平衡;临界转速;初始弯曲
                              +
              中图分类号:TH113.2 5        文献标志码:A        DOI:10.16385/j.cnki.issn.1004-4523.202309055


                      Higher order extra trial weight-free balancing method for flexible rotors
                                                   with initial bending

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                     DENG Zhenhong ,LUO Huageng ,DENG Wangqun ,NIE Weijian ,LIN Haidong ,ZHANG Baoqiang 1
              (1.School of Aerospace Engineering,Xiamen University,Xiamen 361102,China;2.AECC Hunan Aviation Powerplant Research Institute,
                     Zhuzhou 412002,China;3.Key Laboratory of Aero-engine Vibration Technology,Aero Engine Corporation of China,
                      Zhuzhou 412002,China;4.School of Energy and Power Engineering,Beihang University,Beijing 100191,China)
              Abstract:It is often difficult to suppress vibration of flexible rotors at high-order critical speeds through conventional low-speed balancing,
              especially in the case of the rotor with initial bending. In this paper,a low-speed dynamic balancing method for flexible rotors with initial
              bending is presented first. Combining the modal information of the rotor with the measurement data at speeds below the critical speeds,the
              low-speed dynamic balancing method is able to balancing the critical speeds without directly measuring the vibrations at the critical speeds and
              the initial bending of the rotor. Based on this,a mode-by-mode forward higher-order-extra-trial-weight-free method is proposed for balancing
              the higher modes simultaneously. In the proposed method,the lower-mode balancing weights on different balancing planes are used as trial
              weights and linked by the modal ratios of the measuring points. This avoids the potential severe vibration when pass through the critical speeds
              if any additional trial weights are used for balancing the higher-order modes. The proposed method is validated by numerical simulation and
              experimental  tests  respectively.  The  results  show  that  the  proposed  method  is  better  than  the  traditional  influence  coefficient  method  in
              balancing performance. In addition,it also avoids potentially high resonant vibration response,thus providing a safer approach for the high
              order dynamic balancing of flexible rotors.
              Keywords:flexible rotor;dynamical balancing;critical speed;initial bending


                  为了追求高功率、轻质化,现代工业机械的转子                         的最常见原因之一,为了抑制和消除这类振动,工业
              结构普遍采用细长化设计,使得其工作转速往往需                            上已经形成了成熟的动平衡产品和工艺。在常规的
              要跨过一阶甚至多阶临界转速;同时为了保证性能,                           动平衡中,转子是在通用平衡机上进行低速平衡的,
              其振动裕量的设计值却往往很小,这对转子的振动                            然而,对于工作转速高于其临界转速的转子,即柔性
              控制提出了十分高的要求。不平衡是引起转子振动                            转子而言,在低速下的平衡一般很难保证转子在较


                  收稿日期:2023-09-18;修订日期:2023-12-28
                  基金项目:中国航发产学研合作项目(HFZL2020CXY004,HFZL2020CXY009)
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