Patent ID: 8402741

Claim:
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 inlet case includes an inlet case portion defining the inlet case flow path, and a bearing support portion is secured to the inlet case portion; 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 torque frame supporting multiple circumferentially arranged star gears intermeshing with a sun gear, the torque frame secured to the inlet case and the bearing support portion; 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 mounted to the bearing support portion.