Airbus Operations (s.a.s.)

Airbus (sas)

Airbus France

Airbus Operations Gmbh

Airbus Corporation

Patrick Oberle

Guillaume Bulin

Alain Porte

Eric Haramburu

Frédéric Piard

Frédéric Chelin

Christian Fabre

Thierry Surply

Franck Oundjian

Vincent Billerot

Nicolas Devienne

Fabrice Gantie

Gregory Albet

Thomas Sauvalle

Benoit Letay

Nicolas Jolivet

Grégory Albet

Matthieu Ritter

Eric Masson

Stephane Pugliese

Fabre Christian

Joël Bourgault

Stéphane Pugliese

A nacelle for a dual-flow turbojet engine comprises a structure, a fixed cowl, a cowl translationally mobile on the structure, a window open between a secondary jet and the outside of the nacelle, and delimited by the fixed and mobile cowls, an outer thrust-reversing door rotationally mobile and a driving mechanism. The driving mechanism comprises a single power cylinder arranged at the level of a median plane and having a first end mounted articulated on the structure, a shaft with the second end of the power cylinder mounted articulated on the shaft, a first yoke joint secured to the outer thrust-reversing door and free to rotate on the shaft, and a second yoke joint secured to the mobile cowl, and where each of the two flanks of the second yoke joint has a groove in each of which the shaft is mounted to slide parallel to the median plane.

Nacelle of a turbojet engine comprising an outer thrust-reversing door

An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between &#x2153; and &#x2159; of the total chord between the stop point and the assembly point.

Air intake structure for an aircraft nacelle

A nacelle includes a fixed structure supporting a fixed cowl and a movable cowl, the movable cowl being movable translationally between a closing position and an opening position. A blocker door is movably mounted rotationally on the nacelle between a closed position and an open position. The nacelle includes a drive mechanism of the blocker door and of the movable cowl between the closed/closing position and the open/opening position of the blocker door/movable cowl, respectively, and vice versa, the drive mechanism includes at least one actuator fixed, to the fixed structure of the nacelle and, to a fitting fixed to the movable cowl. The drive mechanism includes, for each actuator, a flexible member having a first end fixed to the fixed structure of the nacelle and a second end fixed to the fitting.

Turbojet engine nacelle comprising a thrust reverser drive mechanism

An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment.

Air input structure for an aircraft nacelle

A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

Turbofan nacelle including a reverser flap

A nacelle comprising a fixed cowl and a movable cowl movable in translation, a window delimited by the fixed cowl and the movable cowl, a reverser flap movable in rotation and a drive mechanism coordinating the movements of the reverser flap with those of the movable cowl. The drive mechanism comprises two bearings fixed to the nacelle, for each bearing, a lever arm with one end movable in rotation on the bearing and one end articulated on the reverser flap, for each lever arm, a rail comprising a straight portion and a curved portion, for each lever arm, a rod with one end articulated on the lever arm, and for each rail, a slider that is movable in translation on the rail and is articulated to one end of the rod.

Jet engine nacelle having a reverser flap

An aircraft propulsion unit comprising a nacelle with a fan cowl locking and closing mechanism. The fan cowls of the nacelle can be closed by a single operator in accordance with the ergonomic standards defined for a single individual. A nacelle is provided with a lateral locking mechanism configured to keep one of the two fan cowls in the closed position, so as to reduce the spacing between the two lower sides of the fan cowls, whereas the presence of a stop between a first elastic member provided on one fan cowl and a second elastic member provided on the other fan cowl allows the operator to provide only that effort required to overcome the force exerted by a single spring at a time.

Aircraft propulsion unit comprising a nacelle provided with a fan cowl locking and closing mechanism

A control device for controlling a variable section nozzle of an aircraft power plant, the variable section nozzle including one or several movable parts capable of modifying the nozzle section and connected by a mechanical transmission chain to an actuator. The control device includes a system for regulating the power plant connected to a control member configured to control the actuator. The control device includes a single control member, an immobilization unit configured to immobilize all the movable parts which are deactivated only when the regulation system controls the positional change of the movable part or parts and a determination unit configured to determine the actual position of the movable part or parts.

Device for controlling a variable section nozzle of an aircraft

An internal wall of an air intake and a housing of a fan form a single tubular piece made from a fiber/resin composite material. A rear end has the single tubular component connected by a flange and bolts to an external cowl of the fan duct, such that the rear end of the tubular component is uniform and the flange is attached and fixed to the rear end.

Turbine engine for aircraft

The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet.

Turboreactor for aircraft

A nacelle, for an aircraft jet engine having a high bypass ratio, in which a jet engine having a longitudinal axis is mounted. The nacelle includes a wall that concentrically, and at least partially, surrounds the jet engine and together defines an annular duct. The nacelle further includes a displacement device that controllably displaces a portion of the nacelle wall in order to modify the section of the flow outlet passage and form at least one longitudinally extending opening. A device for forming a fluid barrier along the at least one longitudinally extending opening is provided to counteract the natural exhaust.

Nacelle with a displacement device for aircraft jet engine and aircraft including such nacelle

A system for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft, that includes first means for heat exchange between lubrication circuits of at least two of the aforementioned apparatuses and a heat-carrier fluid contained in a closed circuit, a second means for heat exchange between the heat-carrier fluid and at least one coolant, the first heat exchange means being arranged locally at each of the aforementioned apparatuses, the second heat exchange means being remote from the aforementioned first means, the closed circuit extending between at least two of the aforementioned apparatuses and the aforementioned second means.

System for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft

An aircraft nacelle in which a power plant is arranged delimits a duct for a flow which assists the thrust. The nacelle includes a device for reducing, canceling, or reversing the thrust that includes at least one flap that can have an active position in which it deflects&#x2014;in the direction of a radial opening&#x2014;at least a portion of the flow and an at-rest position in which the flap does not interfere with the flow, whereby the wall of the nacelle delimiting the duct includes at least one moving part that can occupy a first position in which it is interposed between the flow to be deflected and the flap and another position in which it releases the flap so as to allow the flap to change position and to move from the at-rest position to the active position.

Aircraft nacelle that incorporates a device for reversing thrust

A turbojet for an aircraft includes an engine housed in a nacelle and a thermal exchanger that can be traversed by a hot fluid designed to be cooled by thermal exchange with a cold fluid external to the thermal exchanger. The thermal exchanger is disposed in an internal volume of the nacelle, between an internal wall of the nacelle and an external wall of the engine, in such a way as to present two thermal exchange surfaces in the flow of the air stream from the turbojet. The disclosed embodiments also relate to an aircraft equipped with such a jet turbine engine.

Turbojet for aircraft

A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner flow, including at the downstream end of the nacelle wall a passage section of a flow outlet. The nacelle includes a displacement mechanism displacing on request a portion of the nacelle wall to modify the passage section of the flow outlet through which a major portion of the flow escapes, the displacement forming in the nacelle wall at least one opening through which a small portion of a leak flow, naturally escapes. The nacelle further includes a fluid device that uses a fluid for compelling the leak flow to flow along the outer face of the portion of the nacelle wall located downstream relative to the at least one opening.

Growing community of inventors

Verdun sur Garonne, France

Patrick Oberle