Patent ID: 7096662

Claim:
An aircraft gas turbine engine exhaust section comprising: a variable throat area nozzle spaced axially downstream of an afterburner, the nozzle including a longitudinally extending upper nozzle wall spaced upwardly and aftwardly of a longitudinally extending lower nozzle wall, a sideways split and aftwardly swept nozzle ramp extending between the upper and lower nozzle walls, the upper and lower nozzle walls and the nozzle ramp extending transversely between first and second nozzle sidewalls, an outer nozzle wall spaced apart from the upper and lower nozzle walls, extending transversely between the first and second nozzle sidewalls, a nozzle flowpath defined between the upper and lower nozzle walls and the outer nozzle wall and the first and second nozzle sidewalls, a variable area throat extending substantially downwardly across the nozzle flowpath from the outer nozzle wall to the upper nozzle wall, an upper ramp section of the aftwardly swept nozzle ramp connected to the upper nozzle wall, and the upper nozzle wall being upwardly and downwardly pivotally connected to an aft end of the nozzle and operable to vary a throat area of the throat.