碰摩引起的双转子系统弯扭耦合振动数值仿真  

Numerical Simulation of Bending-torsional Coupling Vibration of Double-rotor System Caused by Rub-impact

作　　者：李文扩 李舜酩[1] 王艳丰 滕光蓉 LI Wen-kuo;LI Shun-ming;WANG Yan-feng;TENG Guang-rong(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AECC Sichuan Gas Turbine Establishment,Sichuan Mianyang 621010,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航发四川燃气涡轮研究院,四川绵阳621010

出　　处：《航空发动机》2022年第5期124-129,共6页Aeroengine

基　　金：国家科技重大专项(2017-IV-0008-0045);国家自然科学基金(51975276);预研领域基金(61400040304)资助。

摘　　要：针对共腔结构的航空发动机双转子系统单点碰摩和局部碰摩引起的弯扭耦合振动问题,建立了含碰摩力、不平衡力、转速控制力矩的弯扭耦合动力学模型。采用4阶龙格-库塔法进行数值仿真分析,结合时域图、频域图、轴心轨迹图分析了转盘偏心距、碰摩刚度等参数变化以及碰摩类型、转速控制时延等对双转子系统弯扭耦合振动特性的影响。结果表明:偏心距和碰摩刚度的增大,会加剧碰摩,其特征频率的最大幅值分别增大了0.1×10^(-4) m和4×10^(-4) m左右;局部碰摩的振动响应要比单点碰摩的更加剧烈,其特征频率的幅值更大,特征频率的成分也更复杂;转速控制时延会使系统振动不稳定,且延迟时间越长,系统振动越不稳定。在航空发动机设计时应当充分考虑转速控制时延的影响。Aiming at the bending-torsional coupling vibration problem caused by single point rub-impact and local rub-impact in the aeroengine dual-rotor system with common cavity structure,a bending-torsional coupling dynamic model including rub-impact force,unbalance force and speed control torque was established.The numerical simulation analysis was carried out by using the fourth-order Runge Kutta method.Combined with the time domain diagram,frequency domain diagram and axis trajectory diagram,the effects of the parameters changes such as the eccentricity of the rotary table,the rub-impact stiffness,the type of rub-impact and the speed control time delay on the bending-torsional coupling vibration characteristics of the dual-rotor system were analyzed.The results show that the increase of ecentricity and rub-impact stiffness will deteriorate rub-impact,and the maximum amplitude of characteristic frequency increases about 0.1×10^(-4)m and 4×10^(-4)m respectively.The vibration response of local rub-impact is severer than that of single point rub impact,the amplitude of the characteristic frequency is larger,and the components of the characteristic frequency are more complex.The speed control time delay will make the system vibration unstable,and the longer the delay time is,the more unstable the system vibration is.The influence of speed control time delay should be fully considered in aeroengine design.

关 键 词：碰摩 双转子系统 转速控制时延 弯扭耦合振动 数值仿真 航空发动机 

分 类 号：V232.1[航空宇航科学与技术—航空宇航推进理论与工程]