Patent ID: 7493754
Filing Date: 2009-02-24
Classification: F01D,F02C,F02K,F05D,F16D

Abstract:
1. A method for assembling a gas turbine engine, the method comprising: providing a core gas turbine engine at least partially defined by a frame and having a drive shaft rotatable about a longitudinal axis of the core gas turbine engine; coupling a low-pressure turbine to a core turbine engine; coupling a counter-rotating fan assembly including a first fan assembly and a second fan assembly to the low-pressure turbine; coupling a booster compressor to the second fan assembly; securely coupling a gearbox to the frame so that the gearbox is circumferentially positioned about the drive shaft; rotatably coupling the first fan assembly to an input of the gearbox such that the first fan assembly rotates in a first direction by slidably coupling the input to a first portion of a bearing support structure using a first spline assembly and slidably coupling the first portion to a second portion of the bearing support structure using a second spline assembly; and rotatably coupling the second fan assembly to an output of the gearbox such that the second fan assembly rotates in a second direction opposite the first direction.