Abstract
This contribution addresses on the theoretical and experimental observations of nonlinear vibration performance of the aero engine drum undergoing repeated impact between the rotor and stator vane segment. By assuming the drum as a rotating thin-wall cylindrical shell, the governing equations of motion of rotating shell under tip rubbing force have been derived in frame of Lagrange equation and verified via the experiment. A fixed point rubbing force model between the clearance of elastic drum and stator vane segment is proposed based on the linear collision force relation. Particularly, an experimental scheme of rotating shell system with unilateral contact is established to simulate the rubbing process of rotating flexible drum and rigid segment. Finally, the influence of rotating speed is investigated in detail and several interesting phenomenon have been confirmed by both analysis and experiment. Overall, the present investigation may suggest an efficient guidance for design of rotating thin-wall shell structures in aero engine and turbo machines.
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