Patent ID: 7685808
Filing Date: 2010-03-30
Classification: F02C,F02K,F05D,Y02T

Abstract:
1. A method of assembling a gas turbine assembly said method comprising: providing a core gas turbine engine including a high-pressure compressor, a combustor, a low-pressure turbine, and a high-pressure turbine; coupling a counter-rotating fan assembly including a first fan assembly and a second fan assembly to the core gas turbine engine such that air discharged from the counter-rotating fan assembly is channeled directly into an inlet of the gas turbine engine compressor via a passage without passing through a booster compressor; coupling a gearbox between the low-pressure turbine and the second fan assembly such that the second fan assembly rotates at a rotational speed that is different than the rotational speed of the first fan assembly; coupling the counter-rotating fan assembly to the low-pressure turbine such that the low-pressure turbine rotates the counter-fan assembly; and coupling a downstream end of the compressor against the combustor such that air discharged from the compressor is channeled to the combustor.