Patent ID: 6494032
Filing Date: 2002-12-17
Classification: F01D,F05B,F16C

Abstract:
A ducted fan gas turbine engine having a longitudinal axis and fixed structure and including a propulsive fan, a compressor, a first shaft and a second shaft, said propulsive fan being mounted on said first shaft and said compressor being mounted on said second shaft, said shafts being normally coaxial both with each other and with said engine longitudinal axis, axially spaced apart first and second bearing members being provided to respectively support said first and second shafts at their upstream ends, first and second support means being provided to respectively support said first and second bearing members from said fixed structure of said engine, and axial sleeve means being provided to interconnect said first and second bearing members and additionally interconnect said first and second support means, the interconnection between said first support means and said axial sleeve means being frangible, said second support means comprising an axially flexible and radially stiff frustoconical member to facilitate axial flexibility thereof and said first support means comprising a frustoconically shaped member.