Patent ID: 6109022
Filing Date: 2000-08-29
Classification: F01D,F05B,F16C

Abstract:
A ducted fan gas turbine engine having a longitudinal axis and including a propulsive fan and a first shaft, said propulsive fan mounted on said first shaft, a second shaft and a compressor 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, said shafts being respectively supported at their upstream ends by said first and second bearing members, said engine having fixed structure, radially frangible support means, and radially resilient support means, said first bearing member being supported from said fixed structure of said engine by said radially frangible support means, and said second bearing member being supported from said fixed structure of said engine, and additionally interconnected with said first bearing member, by said radially resilient support means.