Airbus Operations (s.a.s.)

Airbus (sas)

Airbus Operations Gmbh

Airbus Corporation

Lionel Czapla

Frédéric Piard

Rémi Amargier

Benjamin Thubert

Kotaro Fukasaku

Frédéric Ridray

Emmanuel Vardelle

Alexis Pissavin

Christophe Labarthe

Thierry Gaches

Jorge Alejandro Carretero Benignos

Bastian Sabathier

Olivier Pautis

Florian Ravise

Pascal Gardes

Frédéric Vinches

Jérôme Milliere

Franck Alvarez

Pascal Pome

Mathieu Belleville

Alistair Forbes

Lionel Sillieres

Julien Le Fanic

Pierre-Olivier Martin

Alain Porte

Laurent Lafont

Frederic Journade

Laurent Cazeaux

Delphine Jalbert

Frédéric Goupil

Antoine Cousin

Frédéric Journade

Laurent Caliman

Pascal Gougeon

Benedikt Bammer

Théophile Horde

Benoît Penven

José Goncalves

Laurent Tizac

Denis Brossard

Mathieu Kaleta

Romain Joubert

Jérôme Cassagne

Nicolas Jolivet

Claire Maffre

Julie Cazalis

Jérôme Gaillardo

Mathieu Mahe

Antoine Abele

Nandakumar Devasigamani

Milan Tasic

Theophile Horde

Abhishek Verma

Laurent Presseq

Jean-Victor Lapeyre

Emmanuel Mermoz

Philippe Mogilka

A device for coupling a propulsion system to an engine pylon of an aircraft, the device comprising a baseplate comprising a base suitable for being fastened to the propulsion system, and a first wall extending substantially perpendicularly to the base. The first wall of the baseplate interacts with first and second sleeves, a pair of flanges and a fasteners to the engine pylon. The fasteners comprise two adjacent fastening screws extending parallel to each other.

Device for coupling a propulsion system to an engine pylon of an aircract, and corresponding aircraft

A module between a dihydrogen tank and an engine in an aircraft. The module comprises outer and inner boxes, a pipeline between the tank and the engine through the boxes, pressure limiters mounted on the pipeline and the inner box, an exhaust pipeline between the pressure limiters and the outside, shut-off valves mounted on the pipeline at the outer box, a detector for detecting a leak of the pipeline or of the outer box and a controller configured to control each shut-off valve as a function of the information delivered by the detector.

Module for a dihydrogen supply system for an aircraft engine

A device for coupling a propulsion system to an engine pylon of an aircraft, the device comprising a baseplate comprising first and second parts of the baseplate placed against each other so as to form a base suitable for being fastened to the propulsion system, and a first wall extending substantially perpendicularly to the base. The first wall of the baseplate interacts with a sleeve, a pair of flanges and fasteners to the engine pylon.

Device for coupling a propulsion system to an engine pylon of an aircraft, and corresponding aircraft

A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective cylinder fastened to the frame or to the casing by fastening means and positioned around the casing and between the supply pipe and the turbine. With such an arrangement, if a blade of the turbine became detached it would meet the protective cylinder blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

Powerplant for an aircraft

A propulsion assembly for an aircraft, having a T-shaped chassis with a horizontal structure and a vertical structure, a gearbox fastened to a front of the chassis, and a propulsion system having the following propulsion elements: an electric motor driving the components of the gearbox, a fuel cell, a tank and a cooling system, wherein the propulsion elements are fastened beneath the horizontal structure and against the vertical structure by fastening means.

Propeller propulsion system with T-shaped chassis

A propulsion assembly having a combustion chamber and a turbine, a nacelle with a front cowl facing the turbine, with a window passing through it, and a rear cowl to the rear of the turbine, a fire barrier between the front cowl and the rear cowl, a dihydrogen supply pipe meandering from the inside of the rear cowl, then in a sealed manner through the fire barrier, then through the window as far as the combustion chamber, wherein the supply pipe has an intermediate section between the fire barrier and the window, and a plate fastened in a sealed manner to the intermediate section and fastened in a sealed manner to the front cowl around the window.

Propulsion assembly for an aircraft

A propulsion assembly for an aircraft having a chassis in the form of a cage with bars, a turbine, a dihydrogen supply pipe winding inside a nacelle as far as the rear of the turbine, with a radial step towards the outside of the nacelle, a rail with a radial step towards the outside of the nacelle, a bypass pipe connected between the two radial steps outside the nacelle, and a protection plate fastened to the bars, and an absorber between the protection plate and the related bar.

A propulsive assembly comprising a nacelle delimiting an internal volume, a T-shaped frame comprising a first wall fixed to the wing and a second wall that is vertical and that divides the internal volume into two sub-volumes, a dihydrogen consumer device, for each sub-volume, a dihydrogen processing system, a supply line connected between the processing system and the consumer device, and an input line connected between the processing system and a dihydrogen tank. Also an aircraft with a wing and such a propulsive assembly.

Aircraft propulsive assembly comprising a nacelle with a t-shaped frame

A supply system for an aircraft, wherein the supply system has a supply module with outlet pipes, feed pipes connected to dihydrogen tanks, and means for channeling the dihydrogen in the feed pipes towards the outlet pipes, a distribution module having introduction pipes connected to the outlet pipes via heaters, distribution pipes connected to an engine, and means for channeling the dihydrogen in the introduction pipes towards the distribution pipes, and a control unit which commands the means of the supply module and of the distribution module depending on the information provided by the detection means. Also an aircraft with such a supply system.

Dihydrogen supply system for an aircraft engine

A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective plate fastened to the frame and positioned between the casing and the supply pipe. With such an arrangement, if a blade of the turbine became detached it would meet the protective plate blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.

Propulsion unit with propeller and electric motor comprising an adapted primary structure, and aircraft having at least one such propulsion unit

A propulsive assembly for an aircraft with an engine system with a core in a casing and having a combustion chamber and a turbine with blades, a supply line supplying dihydrogen, an injector manifold equipped with injectors which dip into the combustion chamber, and a distribution network with several bypass lines distributed around the casing, a rear manifold connected to the supply line and to the bypass lines and a front manifold connected to the bypass lines and to the injector manifold, in which the rear manifold is at the rear of the turbine and the front manifold is at the front of the turbine.

Propulsive assembly for aircraft

A casing system mounted between an upstream solenoid valve of an upstream pipe and a downstream solenoid valve of a downstream pipe and which has a casing divided by a separation wall into a first volume which is placed under reduced pressure and a second volume, a heat exchanger which is fixed inside the casing with a first inlet which is arranged in the first volume and which is connected to the upstream pipe and a first outlet which is arranged in the second volume and which is connected to the downstream pipe, and a control unit which closes the solenoid valves if the deviation between two successive values of the pressure in the first volume or in the second volume is greater than a threshold.

Casing system containing a heat exchanger for reheating dihydrogen

A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

Propeller propulsion unit for an aircraft

A structure for an aircraft is disclosed including comprising at least one node which having first and second plates which are pressed against two opposite faces of a first reinforcement, and to which upstream and downstream reinforcements positioned on either side of the first reinforcement are connected. A connection system connecting the first and second plates is disclosed including at least one boss projecting from a surface of one of the plates pressed against the first reinforcement, for each boss, a housing recessed relative to a surface of the other plate pressed against the first reinforcement, configured to house the boss, and at least one fastening element, passing through the first reinforcement, connecting the first and second plates and spaced apart from the boss.

Reinforced lattice structure and aircraft comprising at least one such structure

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Cornebarrieu, France

Lionel Czapla