Patent ID: 7694505

Claim:
A method of assembling a gas turbine engine assembly, said method comprising: providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine; coupling a low-pressure turbine axially aft of the core gas turbine engine; coupling a fan assembly axially forward of the core gas turbine engine; and coupling a booster compressor to the low-pressure turbine; and coupling the fan assembly to the booster compressor via a gearbox and a drive shaft such that, upon rotation of the drive shaft in a first rotational direction, the booster compressor and the low-pressure turbine rotate in the first rotational direction at a first rotational speed and the fan assembly rotates in a second rotational direction at a second rotational speed, the first rotational direction different than the second rotational direction, the first rotational speed greater than the second rotational speed.