A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon connecting portion and extends in the aft direction from the first annular portion. A second annular portion is positioned aft of the first portion and coupled to the rail. The second portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage with the first annular portion in the closed position, thereby providing access to the engine core. A mating axial groove and rib connection is located between the first annular portion and the second annular portion.

A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon portion and extends in the aft direction from the stationary portion. A second annular portion is positioned aft of the first portion and coupled to the rail, the second portion being movable along an engine core centerline between a closed position and an open position, wherein the second annular portion is configured to engage with the first annular portion in the closed position to provide access to an engine core. The second annular portion includes a nozzle plug.

A thrust reverser of a bypass turbojet engine nacelle is disclosed, which includes movable cowls that move backwards with respect to a fixed front structure to uncover thrust reverser cascades and a variable secondary nozzle connected to the movable cowls by guide means allowing an axial sliding of the system which controls the movement of this variable secondary nozzle, wherein it includes cylinders bearing on the front structure for controlling reversal means of the displacement direction connected to the movable cowls, which move the variable secondary nozzle backwards when these cylinders output a forward stroke, as well as blocking devices which connect the secondary nozzle to the movable cowls when this nozzle is deployed.

A variable area nozzle for an aircraft engine includes a nozzle inner structure, a nozzle outer structure, an actuation system and a flowpath. The nozzle inner structure includes a nozzle wall and a nozzle sleeve. The nozzle wall includes a plurality of slots arranged circumferentially about the axis. Each of the slots projects radially through the nozzle wall. The nozzle sleeve axially overlaps and circumscribes the nozzle wall. The actuation system includes a carriage and an actuator. The carriage includes a hub and a plurality of struts arranged circumferentially about and connected to the hub. Each of the struts projects radially through a respective slot where the nozzle sleeve is attached to the carriage at an outer end of the carriage. The actuator is disposed radially within the inner nozzle wall and is coupled to the hub. The actuation system moves the nozzle sleeve axially along the nozzle wall.