Patent attributes
A gas turbine engine includes a gas generator with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. There is a duct located downstream of the gas generator. The duct is configured to move between a first position and a second position. A fan drive turbine is positioned downstream of a path of the products of combustion and passes over at least one gas generator turbine rotor when the duct is in the first position. The fan drive turbine is for driving a shaft and the shaft is for engaging gears to drive at least two fan rotors. An augmentor section is positioned downstream of a path of products of combustion and passes over at least one gas generator turbine rotor when the duct is in second position.
