In various embodiments, a cowl actuation system may comprise a cowl, an actuator, a bell crank, and a guide arm. The cowl may be configured to modulate at least a portion of the exhaust flow of a gas turbine engine. The bell crank may have a first end and a second end. The first end may be operatively coupled to the actuator. The second end may be operatively coupled to the cowl. The bell crank may be configured to pivot about a first point located between the first end and the second end. The first point may also be located along a diameter. The guide arm may have a third end and a fourth end. The third end may be mounted to a second point. The fourth end may be operatively coupled to the cowl. The second point may be located along the diameter.

The present disclosure provides a turbojet engine nacelle having a downstream section including a cowl which is ended with a hinged flap constituting a nozzle. In particular, the hinged flap is hingedly and translatably hinged to the cowl.

The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. The nacelle is notable in that it includes a shaped device for activation of the door, during their activation from a closed position to an open position of the door, to drive the door in a combined movement that is translational in the direction running upstream from the nacelle and rotary towards the exterior of the nacelle.

The present disclosure provides a variable section nozzle for an aircraft nacelle having a longitudinal axis. The variable section nozzle includes movable doors and at least one displacement device for displacing the movable doors between a reduced section position and a larger position. The movable doors include at least one first guide device and at least one second guide device, each operable to guide the displacement of the doors relative to a fixed structure of the nozzle. The second guide device is disposed downstream relative to the first guide device and each of the first and second guide devices provide a curvilinear path. In one form, the curvilinear paths are substantially circular and define a circular arc.

An aircraft engine variable area fan nozzle structure disposed abaft a thrust reverser, including a sleeve translatable over a cascade array, comprises two semi cylindrical segments that can be axially translated and radially tilted to enlarge the fan duct exhaust area in order to optimize exhaust pressure and associated noise in high thrust circumstances such as on take-off, and to constrict that area under lower thrust conditions such as cruise. A pair of angularly adjacent segments can be moved by an actuator anchored to the fixed engine framework and independently of the thrust reverser translating sleeve. The tilting movement is imposed by the pivoting links of each segment to carriages that ride in a non-linear trackway secured to a thrust reverser translating sleeve. The actuator can be of a dual concentric type which can independently drive the trust reverser and nozzle segments.

The present disclosure concerns a thrust reverser for an aircraft turbojet engine nacelle including at least one movable thrust reverser cowling, a means for locking the cowling, an outlet nozzle having a variable cross-section that is arranged in the downstream extension of said cowling and that is movable, and at least one actuator that includes an actuating rod capable of moving the variable nozzle and the movable cowling, remarkable in that the reverser is provided with a passive coupler.

A thrust reverser for a nacelle of an aircraft turbojet engine includes at least one movable thrust reverser cowl, a means for locking the cowl, a variable section outlet nozzle, and at least one actuator including an actuator rod. The thrust reverser is provided with a resilient coupler comprising a body which is rigidly connected to the thrust reverser cowl and a resilient return and abutment device that engages with the actuating rod of the actuator such as to resiliently return the nozzle to a neutral position. The return device is calibrated such that, when the cowl is unlocked, the return device opposes the relative movement of the actuating rod relative to the cowl, such as to enable the movement of the cowl and the nozzle, and when the cover is locked, the actuator drives the actuating rod against the return device to enable the movement of the nozzle.

A variable geometry exhaust nozzle arrangement includes a plurality of hingable exhaust petals defining a perimeter of an exhaust duct and an annular ring slidably engagable against a radially outer surface of each petal. The annular ring is coupled to a plurality of circumferentially spaced actuator arrangements, each including first and second circumferentially spaced parallel actuator arms pivotably coupled to the annular ring at a first end and to a slide arrangement at a second end. Each slide arrangement is mounted for linear sliding movement relative to the annular ring, such that sliding movement of each slide arrangement causes pivoting of the first and second actuator arms to thereby translate the annular ring in one or both of a longitudinal direction and a lateral direction.

The present disclosure concerns a thrust reverser for an aircraft turbojet engine nacelle including at least one movable thrust reverser cowling, a means for locking the cowling, an outlet nozzle having a variable cross-section that is arranged in the downstream extension of said cowling and that is movable, and at least one actuator that includes an actuating rod capable of moving the variable nozzle and the movable cowling, remarkable in that the reverser is provided with a passive coupler.

A thrust reverser for a nacelle of an aircraft turbojet engine is provided that includes a thrust reverser cowl movable along a direction parallel to a longitudinal axis of the nacelle and a variable section outlet nozzle extending from the thrust reverser cowl. The thrust reverser further includes an actuator, a first locking device to lock the thrust reverser cowl, a second locking device to lock the variable section outlet nozzle, and a reset lever. The reset lever is pivotally driven by a locking pin secured to the cowl and pivots from a rest position to a reset position.