Airbus Operations (s.a.s.)

Airbus France

Airbus UK Limited

Airbus Operations Gmbh

Cyril Bonnaud

Thierry Fol

Stéve Bedoin

Thierry Surply

Arnaud Hormiere

Neil John Lyons

Thomas Stevens

Florent Laporte

Anne Dumoulin

David Grossein

Stephanie Dantin

Marjorie Defos

Stéphane Dostes

Guillaume Drochon

Marjorie Clottes

Amadou AndréSylla

Tom Gibson

Frédéric Roche

The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear.

Aircraft propulsion system comprising an AFT pylon fairing with lateral walls that are profiled for injecting cool air along a thermal protection floor

The invention relates to a method for manufacturing an engine pylon () to be mounted between an engine () and an aircraft wing (), said method comprising: mounting a pylon box () around a main structure (), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator () onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators.

Engine pylon comprising a vortex generator, and method for the production thereof

According to the invention, the engine pylon for the suspension of a turbo engine under an aircraft wing is such that the trailing edge of the rear lower part of the engine pylon is shifted toward the root of the wing.

Engine pylon for the suspension of a turbo engine under an aircraft wing

A wing arrangement of an aircraft has a wing and at least one pylon for suspending an engine below the wing. The wing has a leading edge with a high-lift device, which is able to move between a deployed position in which the high-lift device projects forward of the leading edge, and which is interrupted in a forward intermediate region of the wing located at the leading edge, the pylon having a forward edge extending forward of the leading edge of the wing between a forward upper portion connected to the wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine. An element of narrow elongate shape protrudes longitudinally from the forward edge and, during flight at a high angle of attack of the aircraft, generates a vortex of aerodynamic flow that is propagated toward the forward intermediate region above the wing.

Airplane engine pylon comprising at least one protruding element to generate a vortex of the airflow

An aircraft with an outer surface from which flows an aerodynamic stream of cold air and includes at least one hot gas outlet, characterized in that it includes at least one device () for generating aerodynamic disturbances so as to mix hot gas and cold air, whereby the at least one device is connected to an outer surface () for protection against the heat and/or close to a hot gas outlet ().

Device for generating aerodynamic disturbances so as to protect the outer surface of an aircraft against elevated temperatures

Disclosed is a mast for the suspension of a bypass turbine engine beneath a wing of an aircraft in which the wing has at least one flap. The mast includes a rear fairing that protrudes rearward of a trailing edge of the wing and is mounted so as to tilt in a deployed downward position as the flap is deployed in a downward position. The rear fairing is positioned to enter a cold flow of the turbine engine, when deployed in the downward position. The rear fairing further supports at least one aerodynamic element that generates vortices that reduce, if not eliminates, vibrations to which the rear fairing is subjected.

Pylon for suspending a turboengine

The present invention provides a method of reducing the compressibility drag of wing, and it also provides a container implementing the method. The container () is provided successively with a front portion () in the vicinity of its leading edge (), then with an intermediate portion (), and then with a rear portion () in the vicinity of its trailing edge (), said rear portion () tapering progressively in a direction going from the leading edge () of the container towards its trailing edge (). Furthermore, said rear portion () is extended by connection means () enabling the container () to be connected under the wing () in such a manner that said tapering rear portion () is partially upstream from the leading edge () of the wing ().

Method of reducing the compressibility drag of a wing, and container implementing the method

A vortex-generating device is presented to reduce a thermal exposure of an aircraft to hot exhaust gases discharged from an aircraft engine. The engine also discharges cold air from a fan of the engine. The aircraft engine may be coupled to the aircraft via a support mast located on a main wing. A portion of the support mast of an aircraft engine is located near a hot gas flow being discharged from the engine. The vortex-generating device is positioned on a surface of the support mast. The device generates a vortex which crosses the hot gases and prevents the hot gas flow from reaching a heat sensitive portion of the support mast. This device is adaptable to the operating conditions of an already-built aircraft without any notable increased weight.

Vortex generator at hot gas output

A drain, for example for an aircraft engine support strut, arranged on the trailing edge of the rear secondary structure of the strut. The drain includes a conduit with a substantially horizontal axis and a substantially rectangular cross-section, taken in a plane parallel to the trailing edge, the conduit closed at an outer extremity by a terminal portion with a substantially ogival cross-section taken in the axis of the conduit and including at least one opening for drainage with an elongated shape on at least one of the opposing lateral walls.

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Toulouse, France

Cyril Bonnaud