Patent ID: 8006479

Claim:
A gas turbine engine system, comprising: a first nozzle section associated with a gas turbine engine bypass passage; a second nozzle section having a plurality of positions relative to the first nozzle section such that there is a gap between the first nozzle section and the second nozzle section in at least one of the positions; a moveable door at least partially between the first nozzle section and the second nozzle section for selectively opening and closing the gap, wherein an entire radially outer surface of the moveable door is radially inward of a radially outer surface of the first nozzle section and a radially outer surface of the second nozzle section, wherein the movable door is located radially outwards of the gas turbine engine bypass passage relative to the engine centerline axis; and a thrust reverser blocker door for thrust reversing connected for movement with the moveable door.