In order to study the whole aero-engine vibration

a generalized complex rotor-support-casing coupling dynamic model was established.In the model

the rotor and casing systems were modeled by means of the finite elements method;the support systems were modeled by the lumped parameter model

and the nonlinear factors of ball bearings and the squeeze film dampers were also included;the complex structures with multi-rotor and multi-casing was considered.A numerical integral method was used to obtain the system responses.Two aero-engine rotor testers were designed to verify the new model.The coupling dynamic model was established for the tester according to the new method

and the modal tests were carried out.The computation results were compared with the experiments results.The results indicate the effectiveness of the new method.