Airbus Operations (s.a.s.)

Airbus France

Airbus Operations Gmbh

Airbus Operations Sl

Olivier Barbara

Eric Bouchet

Alain Porte

Olivier Pautis

Frederic Journade

Damien Prat

Jesús Javier Vázquez Castro

Diego García Martín

Pascal Pome

Thomas Stevens

Stéphane Viala

Nicolas Antoine

David Donjat

St&eacute;phane Viala

Stephane Viala

Guillermo Hernaiz LÓPEZ

An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.

Aircraft engine assembly

To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

Assembly for aircraft, comprising a primary attachment-pylon structure fixed to a wing box by fasteners partially embedded in the primary structure

An aircraft air conditioning system includes a main air conditioning device which taps air off a turbine engine, and an auxiliary unit with a compressor that taps ambient air and conditions it to send to a distributing device in place of a main device, when the aircraft is in cruising flight or close to cruising flight.

Aircraft air conditioning system

According to the invention, on at least one of the faces (E,I) of said leading edge (), forward of the partition (), an action is exerted on the fluid flow (EF) so as to cause the latter to switch from the laminar state (EFL) to the turbulent state (EFT) in order to increase the thermal exchanges and minimize the thermal stresses on said leading edge.

Method of de-icing the leading edge of an aerodynamic surface and aircraft implementing such a method

An aircraft recovers the energy of conditioned air as it passes from a conditioned zone to outside the aircraft and uses the recovered energy to air condition the aircraft.

Aircraft including an air conditioning system

Rapid-opening door. According to the invention, on its face () immediately adjacent to the pressurized space (), the door () is provided with a projecting lip () in the vicinity of its free edge (), accelerating the opening of said door in the event of decompression of the space ().

Rapid-opening door

Air inlet cowl for a jet engine equipped with de-icing means

Growing community of inventors

Puylaurens, France

Olivier Barbara