Patent ID: 7770381

Claim:
A gas turbine engine, comprising: (a) a turbomachinery core operable for generating a first flow of pressurized combustion gases, the core having an exit plane; (b) a fan disposed upstream of the core adapted to extract energy from the core and generate a first flow of pressurized air; (c) a bypass duct surrounding the core which receives a portion of the flow of pressurized air from the fan; (d) a duct burner disposed in the bypass duct, upstream of the exit plane, for receiving the first flow of pressurized air and generating a second flow of pressurized combustion gases; (e) an exhaust duct disposed downstream of the core and operable to receive the first and second flows of pressurized combustion gases and to discharge the combined flows downstream; and (f) a mixer for receiving the first and second flows of pressurized combustion gases and discharging the combined flows to the exhaust duct, wherein an open area of the mixer is selectively variable.