Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Stéve Bedoin

Cyril Bonnaud

Damien Prat

Lionel Diochon

Thierry Surply

Florent Laporte

David Grossein

Marjorie Clottes

Amadou AndréSylla

Guillaume Drochon

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

An aircraft engine assembly including a turboshaft engine with a propeller and an attachment pylon intended to be laterally attached on a rear portion of the structure of the aircraft is disclosed. The pylon has an outer surface forming an aerodynamic profile incorporating a trailing edge which is arranged upstream of the propeller of the turboshaft engine. The pylon includes a mobile rear flap at least partially defining the trailing edge and a controller which steers the incidence of the flap according to a law depending on the incidence of the aircraft.

Attachment pylon for aircraft turboshaft engine, comprising rear flaps with mobile incidence

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

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Toulouse, France

Stéve Bedoin