Airbus Operations (s.a.s.)

Airbus (sas)

Airbus France

Airbus Operations Gmbh

Franck Crosta

Damien Prat

Olivier Pelagatti

David Grossein

Amadou André Sylla

Christophe Cail

Amadou Andre Sylla

A method and device for displaying at least one position indicator for an aircraft. The display device includes at least one unit for generating information for determining, during a flight of the aircraft, a control value representative of the movement by a first pilot of his joystick relative to at least one of the roll and pitch axes of the aircraft, at least one computation unit for computing a piloting command representative of the control value determined by the unit for generating information, and one display unit for displaying at least one symbol on at least one screen intended for the second pilot and directly visible by the latter, the symbol representing the position indicator and being displayed on the screen in a position illustrating the piloting command on the screen.

Method and device for displaying at least one position indicator for an aircraft

Disclosed is a turbofan engine for an aircraft. An inner fan cowl of the turbofan engine bounds an annular cold-stream duct proximate to the engine's central hot-stream generator, and an outer fan cowl bounds the annular cold-stream duct proximate to an outer nacelle cowl. An annular boss is provided along the inner fan cowl, with the annular boss having a rounded cross section that projects with respect to a smooth shape configuration of the inner fan cowl. The annular boss is configured to locally change speed of a cold stream flow in the annular cold-stream duct from a subsonic range to a supersonic range and to originate a first shockwave characteristic in a succession of shockwave characteristics, with the first shockwave characteristic being inclined from its origin toward the rear portion of the turbofan engine.

Aircraft turbofan engine

Disclosed is a method for producing a modified aircraft bypass turbojet engine having reduced sound output, in which the method is based on modifying an initial configuration of a rear portion of the turbojet engine to produce a modified rear portion of the turbojet engine. The modified rear portion includes a modified outer convex rear part shaped with a modified concave inner rear part that delimits an intermediate space beyond an initial cold stream outlet orifice. The intermediate space has a thickness at least equal to the thickness (E) of a sound deadening coating, which is placed in the intermediate space.

Method for reducing sound output at the back of a turbo engine and turbo engine improved by this method

An improved bypass turbojet engine includes a particularly shaped hot flow nozzle arranged about a particularly shaped type of boss. The boss is bulbous in shape and is connected by a first connecting surface to a turbine casing. The hot flow nozzle is formed as a single skin that extends in a rearward direction from an engine cowl, with the hot flow nozzle being connected to the engine cowl along a second connecting surface. The hot flow nozzle and the bulbous boss are positioned relative to one another to delimit a nominal nozzle throat section and a nominal outlet section for hot flow from a hot flow generator. The hot flow nozzle single skin is also approximately bulbous in shape and widens from the second connecting surface in a direction toward the engine cowl's external wall.

Dual flow turboshaft engine and improved hot flow nozzle

According to the invention, a plurality of embossments () having a rectangular section is provided at the inner periphery of the outlet opening () of the fan duct (), said embossments being separated by longitudinal channels () having a convergent (C) and a divergent (D) for the cold flow ().

Turboshaft engine with reduced noise emission for aircraft

A turboengine that reduces rear noise emissions has a thickness of a rear part of a sound-attenuating coating, which is borne internally by an external fan cowl, that is increased toward a front part of the sound-attenuating coating. An increased-thickness zone is connected to a pan of the coating, located in a critical area of a jet nozzle, by a surface having a curved profile.

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Leguevin, France

Franck Crosta