Abstract
When high-speed and lightweight rotors in jet engines or turbopumps used in space vehicles are subjected to base excitation such as turning or pitching motion, the rotors may be brought into contact with the casing, or the bearings may be damaged due to the vibration caused by gyroscopic moment or centrifugal force. In this paper, a dynamic analysis of a rotor system that comprises flexible suspensions, a flexible shaft, a flexible disk and flexible blades is performed by a finite-element method. The rotor is excited by a pitching motion of the frame, of which the axis is assumed to be distant from the center of mass of the rotor. The usefulness of modeling and the validity of the computational program are demonstrated by comparison with the experimental results obtained using a model rotor. The dynamic response of the system in the case of the turning motion of the frame is also calculated.
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