Patent ID: 8696312
Filing Date: 2014-04-15
Classification: F02C,F16C

Abstract:
1. A damping system for a gas turbine engine comprising: at least one bearing mounted to a rotor shaft; a support connected to an outer race of the bearing, the support comprising a wall secured to a casing of the gas turbine engine at a connection portion, the wall having a first surface positioned against a surface of the casing with the first surface being in a non-parallel relation with the rotational axis of the rotor shaft, a cavity defined in the first surface by a narrowing of a thickness of the wall, the cavity containing a damping fluid to dampen elastic deformation of the wall at the cavity resulting from axial oscillations of the rotor shaft, and an abutment in the first surface adjacent to the cavity and separated from the connection portion of the wall by the cavity to limit an amplitude of the elastic deformation of the wall by abutment with the casing; and at least one seal between the support/bearing and the casing to contain the damping fluid in the cavity.