Patent ID: 7661260
Filing Date: 2010-02-16
Classification: F01D,F02C,F02K,F05D

Abstract:
1. A method for assembling a gas turbine engine assembly, said method comprising: coupling a fan assembly to a core gas turbine engine such that the fan assembly is upstream from the core gas turbine engine; coupling a low-pressure turbine downstream from the core gas turbine engine, wherein the low-pressure turbine includes a disk, a flange formed with said disk, and a plurality of splines formed in the flange; providing a shaft that includes a first end having a first outer diameter and a second end having a second outer diameter that is less than the first outer diameter, said second end further including a plurality of splines; coupling the shaft first end to the fan assembly; and coupling the shaft second end to the low-pressure turbine disk flange such that the shaft splines mesh with the flange splines such that torque is transmitted from the low-pressure turbine to the fan assembly via the shaft during engine operation.