Abstract: An exhaust nozzle for a gas turbine engine including a plurality of primary and secondary flaps which are pivotally positionable for varying the geometry of the nozzle and for providing thrust vectoring. Electromechanical actuators preferably are used to position the flaps. The inner surfaces of the primary flaps are preferably curved convexly to continually maintain the location of the nozzle throat on the primary flaps. Reverser doors can be added to permit thrust reversal and fairing flaps can be included outwardly of the primary and secondary flaps to maintain a smooth, aerodynamic flow.

Abstract: A gas turbine engine flight maneuverable nozzle for installation within an aircraft wing or the like is provided with pivotably connected convergent and divergent flaps partially defining an exhaust stream flow path. A third flap, pivotably connected to the divergent flap, partially defines the wing control surface contour. In the cruise and flight maneuver modes, an actuation system provides synchronous movement of the convergent and divergent flaps to control, in a predetermined relationship, the areas of the exhaust stream flow path throat and exit. A vectoring actuator, carried by the main actuator, overrides the main actuator in the flight maneuvering mode and causes the divergent flap to pivot downward, thus deflecting the exhaust stream. Simultaneously, the control surface contour defining flap is repositioned to increase the control surface camber thereby increasing lift. Flow separation from the wing control surface is prevented by the effect of super-circulation due to the exhaust stream.