Patent ID: 8511061
Filing Date: 2013-08-20
Classification: F01D,F02C,F02K,F05D

Abstract:
1. A gas turbine engine comprising: a core housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path; a shaft supporting a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path, wherein the shaft includes a main shaft and a flex shaft having bellows, the flex shaft secured to the main shaft at a first end and including a second end opposite the first end; a geared architecture coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture, wherein the geared architecture includes a sun gear supported on the second end; a first bearing supporting the shaft relative to the intermediate case; and a second bearing supporting the shaft relative to the inlet case, and the second bearing is arranged radially outward from the flex shaft.