Patent ID: 9650954
Date: 2017-05-16
CPC Classifications: B64D,F01D,F02C,F02K,F05D

Claim:
1. A gas turbine engine comprising: at least three fans rotors, wherein each of the at least three fan rotors is connected to a respective fan shaft; a gas generator with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section, and there being a fan drive turbine positioned downstream of a path of the products of combustion having passed over said at least one gas generator turbine rotor, said fan drive turbine driving a shaft and said shaft engaging at least three gears to drive respective said at least three fan rotors through said respective fan shaft, wherein each one of the at least three fan rotors, the respective fan shaft and respective one of said three gears are enclosed in a respective fan casing and wherein said at least three fan rotors, include at least two distinct diameters of fan rotors.