Aircelle Limited

Safran Ceramics

Safran Nacelles

Safan Nacelles

Florent Bouillon

Bertrand Desjoyeaux

Alexandre Bellanger

Laurent Dubois

Davi Silva De Vasconcellos

Stéphane Bardin

Arnaud Delehouze

Laurent Georges Valleroy

François Taillard

John Moutier

Christophe Thorel

Benoît Carrere

Emmanuel Anfray

Franck Dupe

Caroline Coat

Pat Dunleavy

Frédéric Ravailler

A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.

Structural and/or acoustic panel of a nacelle of an aircraft propulsion assembly and related manufacturing method

A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.

Expandable cellular system for a sandwich panel

A structure for the nacelle of an aircraft propulsion unit includes a first skin and stiffeners arranged to hold acoustic treatment modules against the first skin. Each acoustic treatment module includes a honeycomb core and a second skin, such that the honeycomb core is sandwiched between the first skin and the second skin. Such a structure allows the structural reinforcement function provided by the stiffeners to be separated from the acoustic treatment function performed by the acoustic treatment modules which are simply bearing on the first skin.

Acoustic treatment structure for an aircraft propulsion unit nacelle

The present disclosure relates to a cell structure for an acoustic attenuation device for a nacelle of an aircraft propulsion assembly. This cell structure includes lateral partitions forming channels that each extend between a first end and a second end and skin elements arranged so that each channel is at least partly closed at the first end thereof by at least one skin element. Each skin element is connected to a respective lateral partition and can move relative to the other lateral partitions. A continuous skin can be assembled on this cell structure so as to at least partly close the channels at the second end thereof and to thus form an acoustic attenuation device.

Cell structure and acoustic attenuation device for a nacelle of an aircraft propulsion assembly

An aircraft nacelle includes: a thrust reverse device having movable cowls, and a supporting structure to support the thrust reverser device. The supporting structure includes: a base body extending along a longitudinal direction of the nacelle and made from a composite material, and a wall of the base body forming an unclosed cross section having an open portion to provide access to an inner surface of the supporting structure from outside, and a plurality of reinforcements which is made from a composite material, and attached on the inner surface along the longitudinal direction. In particular, the reinforcements are integrated in the inner surface of the supporting structure.

Thrust reverser supporting structure including composite reinforcements and a base having an unclosed cross section

The present disclosure relates to a beam, in particular for a cascade thrust reverser, including a skin made of a composite material and defining a closed section, wherein said beam is filled with a core material.

Beam for a cascade thrust reverser

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 supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame, the beam and the half-frame being formed of composite materials. The half frame has an open section, and the half-structure defines a structure selected from the group consisting of: the beam and the front half-frame form a one-piece part; the beam has an extension with an open section, the shape of which matches that of the front half-frame, the extension being attached to the half frame; and the front half-frame has an extension with an open shape, the shape of which matches the beam, wherein the extension is attached to the beam.

Nacelle for an aircraft engine

A stub frame for a cascade vane thrust reverser structure of an aircraft nacelle is attached to one or more cascade vanes. The stub frame includes an integral primary structure with a C-shaped longitudinal section, a secondary structure acting as a cascade edge and attached to the primary structure at one end, and transverse stiffeners connecting the two ends of the primary structure.

Stub frame for a cascade thrust reverser structure

The invention relates to a method for making an acoustic absorption panel in particular for the nacelle of an aircraft engine, the panel being of the type comprising a cellular core covered on one side with a so-called outer air-permissive skin and on the other side with a so-called inner perforated skin, the cellular core being formed by the edge-to-edge junction of a plurality of blocks with a cellular core (B, B). The method comprises the following steps: a) before the edge-to-edge junction of blocks with a cellular core (B, B), opening the cells (A, A) located on the edges of the blocks to be joined; and b) edge-to-edge dry joining the blocks (B, B) so that the open cells (A, A) engage into one another.

Growing community of inventors

Anglesqueville l'Esneval, France

Florent Bouillon