Patent ID: 7921634

Claim:
A method of assembling a turbofan engine assembly comprises: providing a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine; coupling a booster compressor upstream from the core gas turbine engine; coupling an intermediate-pressure turbine downstream from the core gas turbine engine; directly coupling the booster compressor to the intermediate-pressure turbine using a first shaft, the intermediate-pressure turbine configured to rotate at a rotational speed that is less than a rotational speed of the high-pressure compressor and greater than a rotational speed of a low-pressure turbine; coupling a thrust bearing between the booster compressor and a fan frame, the thrust bearing configured to transmit thrust loads generated by the booster compressor and the intermediate-pressure turbine to the fan frame; coupling a counter-rotating fan assembly upstream from the booster compressor, the counter-rotating fan assembly including a first fan assembly configured to rotate in a first direction and a second fan assembly configured to rotate in an opposite second direction, wherein the first fan assembly and the second fan assembly each extend to a nacelle surrounding the first and second fan assembly; and coupling the low-pressure turbine downstream from the intermediate-pressure turbine, the low-pressure turbine configured to rotate in a single direction to drive the counter-rotating fan assembly.