Vibration dampening device for aircraft, has dampening ring formed of succession of arcs of circle with different radius and centers in state without constraint so that ring with diameter of groove, at constraint state, has circular shape

摘要

The device has a dampening rod (18) formed of a split ring mounted in an annular groove of an open rotor from side of rotational axis. The rod has ends (24) separated one from another, when the rod is at free state without constraints, and are closer to one another when the rod is constrained and is mounted on a groove of the rotor. The ring is formed of succession of arcs of circle (28, 30, 32) with different radii and centers (C1, C2, C3) in the free state without constraint so that the ring with the diameter of the groove, at constrained state, has a perfectly circular shape. Independent claims are also included for the following: (1) a rotor of a turbomachine (2) a compressor of a turbomachine (3) a turbomachine having a vibration dampening device.