Patent ID: 8127531

Claim:
A nozzle system for a gas turbine engine having a longitudinal axis, the nozzle system comprising: a thrust reverser; a fan duct inner wall; a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, the fan duct inner and outer wall collectively defining a fan duct; and a fan nozzle defining at least a portion of the fan duct outer wall and having a nozzle aft edge, the fan duct inner wall and the nozzle aft edge collectively defining a fan duct throat area, the fan nozzle being configured to non-pivotably move outwardly relative to the longitudinal axis during axially aft translation thereof to vary the fan duct throat area; the fan nozzle being movable without activating the thrust reverser, the thrust reverser having movable blocker doors configured to block fan flow through the fan duct when the thrust reverser is activated.