航空发动机双转子模态动平衡方法研究  

Research on mode dynamic balancing method of dual-rotor aero-engine

作　　者：周旋 黄江博 廖明夫[1] 况钧耀 ZHOU Xuan;HUANG Jiangbo;LIAO Mingfu;KUANG Junyao(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129

出　　处：《航空动力学报》2023年第11期2688-2700,共13页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅳ-0001-0038)。

摘　　要：针对双转子系统低压激励和高压激励振动模态的正交性受转速比影响,提出了以定转速比转子模态替代实际工作转速线下的转子模态进行双转子系统N_(1)+N_(2)和N_(1)+N_(2)+4平面模态动平衡的方法。推导了N_(1)+N_(2)和N_(1)+N_(2)+4平面模态动平衡法的平衡条件,给出了模态不平衡质量和正交校正质量组的计算式,并以某型航空发动机双转子系统为例,给出了N_(1)+N_(2)模态动平衡方法平衡各阶模态的过程。最后在双转子实验系统上进行了动平衡验证实验,实验研究发现在定转速比的条件下动平衡的减振效果最大可达72.4%;当高、低压转子转速控制率为实际工作转速线时,在工作转速范围内,各阶临界转速处的振动幅值总量都降低到120μm以下,满足设计要求。实验结果表明提出的双转子航空发动机模态动平衡方法是可行的。In view of the dual-rotor system with two sets of vibration modes of low-pressure rotor excitation and high-pressure rotor excitation,the orthogonality of the two vibration modes was affected by the speed ratio,so N_(1)+N_(2)plane and N_(1)+N_(2)+4 plane mode dynamic balance method of the dual-rotor system was proposed by replacing the rotor mode under the actual operating speed line with the rotor mode under the constant speed ratio.On the basis of the known modal orthogonality theory of the dual-rotor system,the equilibrium conditions of the two-rotor system N_(1)+N_(2)and N_(1)+N_(2)+4 plane mode dynamic balance methods were deduced,and two dynamic balance methods of the calculation equations of the unbalanced mass and the orthogonal correction mass group were given.What’s more,taking a certain type of aeroengine dual-rotor system as an example,the process of balancing each order mode was given by the N_(1)+N_(2)mode dynamic balancing method.Finally,the dynamic balance verification experiment was carried out on the dual-rotor test system.The experimental study found that the vibration reduction effect of dynamic balance method can reach up to 72.4%under the condition of constant speed ratio;when the high and low pressure rotor speed control rate was the actual working speed line in the working speed range,the total vibration amplitude at each critical speed was reduced to below 120μm,meeting the design requirements.The experimental results showed that the proposed mode dynamic balancing method for the dual-rotor aeroengine is feasible.

关 键 词：模态动平衡 不平衡响应 航空发动机 双转子系统 转速比 

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]