Aircelle Limited

Safran Nacelles

Safran Aircraft Engines

Societe Lorraine De Construction Aeronautique

Arts & Metiers Paris Tech

Ateliers Cini

Le Pole De Plasturgie De L'est

Pole De Plasturgie De L'est

Hervé Hurlin

Pierre Caruel

Olivier Kerbler

Bertrand Desjoyeaux

Hakim Maalioune

Marc Versaevel

Pierre Moradell-Casellas

Nicolas Dezeustre

Jean-Pierre Cauchois

François Gallet

Jean-Paul Rami

Louis Bettega

Olivier Gilo

Jean-Baptiste Goulard

Marius Mihaluta

Julien Drant

Alain D'Acunto

Patrick Martin

Henri-François Perrin

Ambre Allard

Loïc Le Boulicaut

François Perrin

Philippe Micheau

Alain Berry

Raymond Robert

Florence Castagnet

Jérome Cini

Richard Mangenot

An active device for attenuating the acoustic emissions of an aircraft turbojet engine includes circulation conduits for a pressurized air flow rate supplying rotary elements each having a pulsation system for the delivered air. The rotary elements are controlled in amplitude and phase and deliver, to outlet diffusers, a pulsed air flow rate with a pulsation at the frequency of the noise to be attenuated having an amplitude and a phase adjusted according to a local feedback law with microphones to attenuate the radiated acoustic power.

Active device for attenuating acoustic emissions for a turbojet engine including controlled turbines

The present disclosure provides a method of manufacturing a composite sandwich panel having a core formed of a plurality of cells extending vertically between a first skin and a second skin. The method includes creating at least one first strip and a second strip from a temporary material, each strip having at least one cavity having a succession of aligned half-cells, lining the cavity of the first strip with a fibrous ply, assembling the first strip and the second strip by interlocking the cavity of the first strip with the cavity of the second strip and trapping the fibrous ply therebetween, and trimming excess temporary material of the entirety of the strips formed during the preceding assembly step so as to form a new cavity which forms a succession of aligned half-cells.

Method of manufacturing a composite sandwich panel for an aircraft propulsion unit

The present disclosure provides a device for de-icing an air inlet lip of an aircraft nacelle. The device includes a pre-exchanger, an intake orifice of taking in low-pressure air downstream from a fan, and two high-pressure air intake orifices downstream from a compressor in addition to controlled valves and check valves installed in an air flow network. In particular, the pre-exchanger includes a low-pressure air outlet capable of opening into the air inlet lip of the aircraft nacelle via a pipe of the air flow network.

De-icing and conditioning device for an aircraft

A method for controlling a position of a variable nozzle of an aircraft includes the following steps: setting the variable nozzle in a position P(t) at a time tas a preliminary step; step A in which at each instant twith 1&#x3c;i&#x3c;N, an optimal position P(t) of the variable nozzle is determined according to magnitudes distinctive of the flight of the aircraft; step B measuring a time interval &#x394;tdefined as a difference between tand t; and step C by which a displacement of the variable nozzle in a position corresponding to the optimal position P(t) is authorized when the time interval &#x394;tis higher than a predetermined minimum threshold.

Method for controlling a variable nozzle section of an aircraft

A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods.

Variable-section nozzle, and aircraft turbojet engine nacelle equipped with such a nozzle

A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.

Turbojet engine nacelle

Growing community of inventors

Igny, France

Hervé Hurlin