Patent ID: 7296398

Claim:
A method for assembling a gas turbine engine, said method comprising: providing a first fan assembly configured to rotate in a first rotational direction; rotatably coupling a second fan assembly to the first fan assembly, wherein the second fan assembly is configured to rotate in a second rotational direction that is opposite the first rotational direction; coupling a first shaft to the first fan assembly and to a first turbine rotor that is configured to rotate in a first rotational direction; coupling a first turbine bearing assembly to the first turbine rotor; coupling a second shaft to the second fan assembly and to a second turbine rotor that is configured to rotate in a second rotational direction that is opposite the first rotational direction; coupling a second turbine bearing assembly between the first turbine rotor and the second turbine rotor; coupling a third turbine bearing assembly between the second turbine rotor and a turbine rear-frame; and coupling a lubrication system to the gas turbine engine such that a lubrication fluid is channeled through at least one shaft to lubricate at least one of the first fan assembly, second fan assembly, first turbine bearing assembly, second turbine bearing assembly, and third turbine bearing assembly.