Patent ID: 7681399

Claim:
A method for operating a turbofan engine assembly including a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and a first core cowl baffle positioned within the fan nozzle duct and a second core cowl baffle wherein a portion of the second core cowl baffle is repositionable with respect to the first core cowl baffle, said method comprising: varying an operating speed of the fan assembly from a first operating speed to a second operating speed; and selectively positioning a portion of the second core cowl baffle between a first operational position and a second operational position with respect to the first core cowl baffle to vary a throat area of the fan nozzle duct to facilitate improving engine efficiency at the second operating speed.