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考虑航空发动机双转子中介轴承的耦合作用及陀螺力矩的影响,利用Lagrange方程建立了机动飞行条件下双转子-滚动轴承支承耦合系统动力学模型,对耦合双转子系统的动力学特性进行了理论与实验研究.结果表明:随着内外转子转速比增大,高压转子振动幅值减小,分岔点处转速增大,最大增幅近67.49%.机动飞行使转子的振动响应幅值增大,出现较多分频.在跃升和横滚飞行姿态下,高压转子响应主要表现为:随着跃升速度增加,高压转子振动幅值明显增加,最大增幅近409.24%,分岔点对应的速度增大;在横滚速度增大时,转子振动特性主要表现为从复杂的运动形态变换到单周期运动形态,转子的振动幅值明显增加.利用基础运动双转子模型实验台对跃升和横滚两种飞行姿态下耦合双转子系统的部分动力学特性进行了实验研究,实验结果与数值模拟结果有较好的一致性,证明了计算结果的正确性.
Considering the coupling effect of aero-engine double-rotor intermediate bearing and the influence of gyroscopic moment, the dynamics model of dual-rotor-rolling bearing support coupling system under maneuver flight was established by using Lagrange equation. The dynamics and dynamics of coupled twin-rotor system were studied theoretically and experimentally The results show that the amplitude of vibration of high-voltage rotor decreases with the increase of the speed ratio of rotor inside and outside, and the maximum speed increases about 67.49% at the bifurcation point. Under the jerk and roll attitude, the response of high-pressure rotor is mainly as follows: with the increase of jerk, the amplitude of vibration of high-voltage rotor increases obviously, the maximum increase is nearly 409.24% and the corresponding speed of bifurcation increases; When the roll speed increases, the vibration characteristics of the rotor mainly change from the complex motion form to the single-period motion form, and the vibration amplitude of the rotor increases obviously. By using the basic motion dual-rotor model test rig, Under the coupled two-rotor system, some dynamic characteristics are experimentally studied. The experimental results are in good agreement with the numerical simulation results. Calculate the correctness of the result.