Vibration Response Analysis Of The Aviation Engine With Dual Rotors

In order to ensure the aviation engine run efficiently, stability, and reliably, get a long service life, Our should know clearly about the factors of the structure that have influence on the performance of the engine, and know how to improve the performance of the engine by changing these factors. The paper make a preliminary analysis on the vibration response of the structure.A dynamics model of the dual-rotor system with rubbing between its internal and external rotor is established firstly, then its vibration responses are analyzed in two main parts. One is about the counter-rotating dual-rotor system; the other is about the co-rotating dual-rotor system. The dynamic characteristics of the dual-rotor system with rubbing are studied with the gradually increase of the rotating speed by means of the time process figure, the bifurcate maps, the Poincare map and spectrum charts. The influences of the viscous damping coefficient, the rubbing stiffness, the rubbing clearance, the speed ratio of two rotors, unbalance mass and the support spring rigidity coefficient various factors including are analysed.The results indicate that the different motions including the periodic, quasi-periodic and multi-periodic appear in the dual-rotor system with the increase of the rotating speed. The motions become more complex with the decrease of the viscous damping coefficient. Along with the increase of the rubbing rigidity coefficient, the system will be easy to lose the stability through rubbing. If the rubbing clearance, the speed ratio and the unbalance mass are choosing reasonablym, the rubbing phenomenon can be effectively avoided . In a certain range, the motions of the system is more stabile with the increase of the support spring rigidity coefficient.