The present disclosure provides a rear nacelle assembly for a turbojet having at least one thrust reversal device to redirect air circulating from upstream to downstream in a flow path of a turbojet and a mast that connects the nacelle to a structure of an aircraft. In one form, the thrust reverser device includes a cradle having a first longeron and a second longeron extending longitudinally opposite sides of the mast. The first and second longeron each include a device for slideably guiding the cowl and the cascade. In another form, a rear portion and a front portion of the cradle connects to the mast by a rear connecting device and front connecting device, respectively, such that the cradle is adapted to follow the movements of the turbojet.

The present disclosure provides a nacelle rear assembly for turbojet engine including at least one thrust reverser device to redirect air flow circulating from upstream to downstream in a flow path of the turbojet engine and a mast to link the nacelle to a structure of the aircraft. In one form, the nacelle extends longitudinally from forth to back along an axis and includes a cradle fastened on the mast. In one form, the cradle includes a first longeron and a second longeron extending longitudinally on either side of the mast. The first and second longeron each include a sliding guide device for sliding of a movable cowl and of a cascade of the thrust reverser device.

A link setting assembly according to an exemplary aspect of the present disclosure includes, among other things, a fixture including at least one platform mount and at least one linkage mount. The at least one linkage mount is spaced-apart from the platform mount by a distance corresponding to a predetermined link length.

A clevis for use in a toggle mechanism of a ram air turbine actuator is provided comprising a first side; a second side parallel to the first side; a first set of parallel pivot holes; second set of parallel pivot holes; a set of parallel through holes; and a helicoil blind hole. The second side rigidly connected to the first side via at least one brace perpendicular to the first side and the second side. The helicoil blind hole being located in the first side and extending into the at least one brace. The first side having a first hole of the first set of parallel pivot holes, a first hole of the second set of parallel pivot holes, and a first hole of the set of parallel through holes. The second side having the hole pattern reflective of the first side, composed of second holes.

Power transmission members, such as synchronous joint members, are each formed by sintering a compact which is molded from a mixture containing metal powder and a binder, as an injection material, by metal powder injection molding. Flow promotion recesses configured to facilitate a flow of the mixture to areas corresponding to power transmission surfaces or the like when the compact is molded are formed in each of two side surfaces of each power transmission member.

A thrust reverser for a gas turbine engine includes a frame, a first reverser door pivotally mounted to the frame, and a second reverser door pivotally mounted to the first reverser door.

A turbocharger for a combustion engine has an adjusting device for matching its operating behavior to the operating behavior of the combustion engine, an actuating actuator, and a transmission element. The transmission element is coupled between the actuating actuator and the adjusting device. The transmission element has a one-part component body, which in each case extends from a first coupling point to a second coupling point along a longitudinal axis and, in each of its end regions, has a coupling element for coupling to the actuating actuator and to the adjusting device. The respective coupling element is designed as an integral part of the component body in the form of a ball receptacle of a ball joint connection in the component body.

A turbofan having a nacelle including a slider mobile in translation between advanced and retracted positions to open a window between a duct and the exterior, a plurality of blades, each being mobile in rotation on the slider between stowed and deployed positions, and a maneuvering system that moves each blade and includes, for each blade, a shaft mobile in rotation on the slider and on which the blade is fixed, an arm having a first end fixed to the shaft and a second end, an arc which is coaxial with the longitudinal axis and is rotatably mounted on the slider, about the longitudinal axis, a lever mounted in articulated fashion between the arc and the second end of the arm, and an actuation system which rotates the arc in one direction and in the other.

A nacelle comprising a fixed structure with a fixed cowling and a cowling movable in translation between closed and open positions, to open an opening between a duct and the exterior. A blocking door is rotatably movable on the movable cowling between a stowed position and a deployed position. A deployment system comprises an arm with a first end articulated on the blocking door and a second end that bears a stop, a slider fixed to the arm, a linear guide system is fixed on the fixed structure and guides the slide, and a cam. The stop is configured to lie against the cam when the movable cowling reaches an intermediate position from the closed position and to be guided by the cam to drive the rotation of the arm about the slider when the movable cowling moves from the intermediate position to an open position.

A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis; and a damper pivot support that extends from a rim of the rotor disk, the damper pivot support comprising an aperture that defines a pivot axis parallel to the axis. A method to dampen a rotor blade of a gas turbine engine, includes independently pivoting a first damper and a second damper of a damper assembly about the pivot axis to respectively contact a first blade and a second blade in response to centrifugal force below a platform of the respective first blade and second blade.