Aircelle Limited

Safran Nacelles

Christophe Thorel

Guy Bernard Vauchel

Bertrand Desjoyeaux

Xavier Cazuc

Florent Bouillon

John Moutier

Laurent Albert Blin

Mathieu Preau

Loïc Hervé André Le Boulicaut

Simon Verger

Stéphane Bardin

Jean-Fabrice Marcel Portal

The present disclosure concerns an acoustic attenuation panel for an aircraft turbojet engine nacelle and a method for manufacturing this panel. The acoustic attenuation panel includes an alveolar central core interposed between an acoustic front skin comprising perforations and a rear skin, the acoustic attenuation panel including a front structure and a rear structure. The front structure includes the acoustic front skin and a first network of alveolar walls, the rear structure including the rear skin and a second network of alveolar walls, the first and second networks of alveolar walls being complementary so as to form, in an assembled position, the alveolar central core, the front structure and the rear structure being positioned opposite to each other and so that the network of alveolar walls of a structure is spaced from the skin of the other structure facing it by a clearance d.

Acoustic attenuation panel for an aircraft jet engine nacelle

A unit for an aircraft thruster is provided that includes a first ferrule configured to be attached to a second ferrule and a first connection flange configured to be secured to a second corresponding connection flange secured to the second ferrule. The connection flange includes a portion forming a plane extending along a radial direction with respect to the first ferrule. A link between the first ferrule and the corresponding connection flange is offset to a distance from said plane corresponding to a length for damping a shear-generating flexural moment, generated by fluxes of forces passing through the first ferrule.

Unit for an aircraft thruster

A lip of an air inlet of a turbojet pod intended to be fastened to an air inlet downstream structure includes at least one electric heating element for defrosting. The electric heating element being fitted with at least one electrical connector able to be connected to at least one corresponding electricity supply connector of the downstream structure. The lip breaks down into at least two identical structures set end-to-end on a periphery of the air inlet.

Modular air inlet lip with electric defrosting for a turbojet pod

The present invention relates to a nacelle for a turbojet, comprising an air inlet structure capable of channelling a flow of air to a turbojet fan and a middle structure () comprising a casing () designed to encircle said fan, with the air inlet structure attached to it, said structure having a peripheral inside surface at least partly equipped with a sound-attenuating structure () extending without geometrical interruption around at least part of the casing, said structure being characterized in that a gap () is provided between the sound-attenuating structure and the casing.

Air inlet shroud structure

Growing community of inventors

Le Havre, France

Christophe Thorel