Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Frédéric Chelin

Alain Porte

Thierry Surply

Christophe Bourdeau

Jacques Lalane

Fabrice Gantie

Olivier Scholz

David Lambert

Dominique Haro

Lauren Davis

Patrick Oberle

Gregory Albet

Arnaud Hormiere

Wolfgang Rehm

Nicolas Boulet

Stéphane Dida

Grégory Albet

Olivier Chaume

Romain Cusset

Christophe Menier

Cedric Leconte

Nathalie Papin

Guillaume Clairet

Fabienne Montetagaud

Pascal Galletti

Jean Yves Thomy

Etienne Bertin

Yann Druon

Irene Moreno Gonzalez

Gabriel Galindo Fernandez

Cédric Leconte

An aircraft nacelle provided with a thrust reversal device which comprises at least one diversion system which is configured to divert, in the activated state, an airflow channeled in the nacelle toward a lateral opening of the nacelle, at least one orientation system comprising at least one transverse deflector which is configured to orientate the airflow diverted by the diversion system in the radial directions and toward the upstream end of the nacelle, and at least one longitudinal deflector which is secant to the transverse deflector(s) and which is oriented in a direction which forms an angle of less than 25° with the longitudinal direction.

Aircraft nacelle provided with at least one thrust reversal device comprising at least one longitudinal deflector, aircraft comprising at least one propulsion assembly composed of such a nacelle

An aircraft nacelle equipped with a thrust reversal device, which comprises: at least one longitudinal actuator for activating or deactivating the thrust reversal device, at least one deflection system configured to deflect an air stream channeled in the nacelle towards a lateral opening in the nacelle, in the activated state, at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system towards the upstream end of the nacelle, for each longitudinal actuator, a hollow longitudinal deflector, which is configured to house the longitudinal actuator and has an aerodynamic profile that has a leading edge oriented towards the deflection system.

Aircraft nacelle equipped with at least one thrust reversal device comprising at least one longitudinal deflector configured to house a longitudinal actuator

An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state; at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system toward the upstream end of the nacelle, at least one downstream deflector positioned at the downstream edge of the lateral opening and configured to deflect the air stream deflected by the deflection system toward the upstream end of the nacelle.

Aircraft nacelle equipped with at least one thrust reversal device comprising a downstream deflector, aircraft comprising at least one propulsion unit having such a nacelle

A deflector provided with a spoiler for a thrust reverser of an aircraft engine nacelle. The deflector, a lateral deflector or an orbital deflector, may be in an exhaust structure of a thrust reverser and comprises a deflector plate configured to act on an aerodynamic flow. The deflector plate has a concave upstream face and a convex downstream face, as well as an intake end and an exhaust end. The deflector is fitted with a spoiler rigidly connected to the exhaust end of the deflector plate and arranged transversely in relation to the deflector plate. The spoiler endowing the deflector with specific properties to act on the aerodynamic flow.

Deflector provided with a spoiler for a thrust reverser of an aircraft engine nacelle

A deflector for an ejection structure of a thrust reverser is disclosed including a deflector plate configured to act on an aerodynamic flow, the deflector plate having a concave upstream face, a convex downstream face, an inlet end, and an outlet end. The upstream face and the downstream face of the deflector plate have different curved profiles, the deflector has a particular profile giving it properties allowing it to act effectively on the aerodynamic flow so as to enhance the performance of the thrust reverser in which it is mounted.

Deflector provided with faces with different curvatures for a thrust reverser of an aircraft engine nacelle

An engine assembly comprising an engine and a pod surrounding the engine that is equipped, upstream according to the direction of entry of air into the engine, with a fan provided with blades, the pod having an upstream air intake. The engine assembly also comprises a display unit including at least one light ring arranged in the air intake upstream of the fan, the light ring including at least one row of light-emitting diodes and being configured to emit at least one light beam and to project it on the blades of the fan.

Engine assembly of an aircraft including a display unit

A process for the production of an acoustic treatment panel that includes an acoustically resistive layer (), at least one alveolar structure (), and a reflective layer (), as well as at least one channel that is bordered at least in part by a wall () that is secant with at least one wall of a cell of the alveolar structure (), includes elevating the temperature of the wall () and the ends of the cells of the alveolar structure () and injecting a pressurized gas into the channel () so as to expand the wall () of the channel so as to flatten it against the ends of the cells of the alveolar structure () in such a way as to produce a weld by continuous diffusion between the ends of the walls of the cells of the alveolar structure () and the wall () of the channel ().

Process for the production of an acoustic treatment panel that integrates channels juxtaposed with an alveolar structure

An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel wherein hot air circulates, as well as a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure, and a reflective layer, as well as ducts for channeling hot air with each one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises, upstream from the ducts, an annular channel which extends over at least a portion of the nacelle circumference, at least one conduit providing communication between said annular channel and the upstream annular channel, and a plurality of ducts that open into said downstream annular channel, the panel for acoustic treatment being connected to the front frame in regard to the annular channel.

Panel for the acoustic treatment comprising hot air ducts and at least one annular channel

An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery.

Aircraft nacelle including a rear frame inclined to the rear

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

An aircraft nacelle includes a wall that delimits an inside pipe () that channels a stream of air to a power plant, at the front a lip () and on the outside an outside wall () that delimits a cavity (), whereby the outside wall includes&#x2014;at its inside surface&#x2014;at least one stiffener () that is arranged in a transverse plane, characterized in that the at least one stiffener () includes at least one drainage opening that allows the flow of liquids through the stiffener () in the direction of a discharge opening () that is located away from the lip in such a way as to limit the risks of air being sucked inside the cavity ().

Aircraft nacelle comprising a reinforced outer wall

An aircraft nacelle including a pipe (), a peripheral wall (), a lip (), and a front frame () connecting the peripheral wall () and the pipe () and forming with the lip () a space () in which the hot air that is provided for frost treatment can circulate, with the pipe () including a coating () for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element () made of a heat-conducting material inserted between the lip () and the pipe () ensuring the continuity of the aerodynamic surfaces of the lip () and the pipe () and the propagation of heat from the space () toward the rear of the nacelle, whereby the at least one element () includes a coating () for acoustic treatment that is made of a heat-resistant material.

Aircraft nacelle including an optimised acoustic processing system

An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure () and a reflective layer (), between which are located&#x2014;in a direction that is essentially perpendicular to the longitudinal direction of the nacelle&#x2014;bands () of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes () for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer () up to the reflective layer () in such a way as to insulate the bands () of cells in the longitudinal direction.

Acoustic processing panel, more particularly adapted for an air intake in an aircraft nacelle

An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation.

Aircraft cover including means for limiting the scoop phenomena of pneumatic type

A repair part enables rapid and efficient repair of damaged metal structures, in particular airframe fuselage skins having internal and external faces, without necessitating any additional thickness compromising the transmission of waves. To this end, the repair part includes a double internal/external plate adapted to be fastened to the internal face and the external face of the metal structure, respectively. The repair part also includes a central hub connecting the internal plate and the external plate and forming a groove between the plates. The part is constituted of a single composite material block, and a glass ply, lining the groove, may be positioned between the plates and the structure. The hub may have passing through it at least one orifice adapted to allow connections to pass through the structure.

Growing community of inventors

Encausse, France

Frédéric Chelin