Nonlinear vibration response of a complex aeroengine under the rubbing fault

Rolling bearing and squeeze film damper will introduce structural nonlinearity into the dynamic model of aeroengine. Rubbing occur due to clearance reduction design engine. The coupling fault make engine present rich vibration responses. This paper aims analyze nonlinear behavior whole aeroengine including rolling under rubbing fault. Firstly, a turboshaft with support is established; force, oil force are introduced dual-rotor–casing six points. Secondly, linear part verified by characteristics three-dimensional finite element model. Finally, varying compliance vibration, damping effect bifurcation mechanism analyzed in detail which clearance, speed ratio stiffness considered. Results show that case excite more significant low-speed region expand rotating range chaotic high-speed compared case.