Patent ID: 6079200
Filing Date: 2000-06-27
Classification: F01D,F04D,F05B,F16C,Y02T

Abstract:
A ducted fan gas turbine engine including a propulsive fan mounted on a shaft, which shaft is normally coaxial with said engine longitudinal axis, a bearing support structure, said fan shaft being supported radially by said bearing support structure, radially frangible connection means, said bearing support structure being in turn supported from fixed structure of said engine by said radially frangible connection means, and restoration means comprising a plurality of generally radially extending spokes interconnected at their radially inner extents by a common member which in turn engages said fan bearing support structure, each of said radially extending spokes slidingly engaging in a corresponding aperture in part of said engine fixed structure located radially outwardly of said fan bearing support structure, said spokes having sufficient resilience in bending as to ensure that they cooperate with said engine fixed structure to exert a radially inward restoration force upon said fan bearing support structure, and hence said fan shaft, subsequent to any radial excursion of at least part of said fan shaft relative to said engine longitudinal axis following any fracture of said frangible connection means.