Aircelle Limited

Safran Nacelles

John Moutier

Bertrand Desjoyeaux

Xavier Cazuc

Franck Maze

Thierry Deschamps

Florent Bouillon

Christophe Thorel

Stéphane Bardin

Emmanuel Anfray

Herve Simon

Bertrand Desjoyaux

The present disclosure related to a method for manufacturing a structure with cellular cores that can be used in a structural panel of a turbojet nacelle, including at least one block of cellular cores. The at least one block of cellular cores includes a central portion with core honeycomb cells, and two side portions each including side honeycomb cells. The side honeycomb cells have edge honeycomb cells situated on edges of a side part of a block, and adjacent honeycomb cells. In particular, the method includes: A) forming junction walls on the side honeycomb cells by opening the edge honeycomb cells, the junction walls being capable of interacting for forming a junction area; B) unfolding the junction walls thus formed in step A; and C) joining the junction walls thus unfolded in step B and belonging to two different side portions end-to-end.

Method for manufacturing a structure with cellular cores for a turbojet nacelle

The present disclosure provides a method for manufacturing a sound attenuation panel having a first cellular core structure and a second cellular core structure joined in a junction area (J). The method includes: a) a joining edge of the first cellular core structure is joined to a corresponding joining edge of the second cellular core structure, thereby forming the junction area; b) the first cellular core structure and the second cellular core structure are placed between an inner skin and an outer skin of the panel. In particular, the method further has a step prior to step a), in which one junction reinforcement is inserted between the joining edge of the first cellular core structure and the corresponding joining edge of the second cellular core structure in the junction area.

Method for manufacturing a sound attenuation panel

The invention relates to a honeycomb core structure () for use in a structural panel for a jet engine nacelle, comprising at least one block with a honeycomb core (A, B) having a central part () with core honeycomb cells () and at least two lateral parts () each comprising a number of honeycomb joining cells () of which at least one part of the honeycomb joining cells () has at least one additional wall () to form a join, the honeycomb core block(s) (A, B) being connected by at least one joint zone () formed by punching two additional walls () superimposed one or the other and provided by honeycomb joining cells () belonging to the distinct lateral parts (). The invention further relates to a structural panel and a nacelle comprising such a structure () and a method for producing such a structure ().

Honeycomb core structure for use in a structural panel for a 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

The present disclosure relates to a method for repairing a portion of an acoustic panel for a nacelle of an aircraft turbojet engine. The panel includes an acoustic skin in which a plurality of acoustic holes are drilled, a solid skin, and a cellular acoustic structure. The cellular acoustic structure, being arranged between the acoustic skin and the solid skin, has a plurality of cells, each of which has one or more drainage openings arranged in one or more of the walls forming each cell. The method includes a step of: defining a part of the acoustic panel to be cut; forming a cutting area closed by the acoustic skin; injecting a resin through the acoustic holes; positioning a replacement cellular acoustic structure in the cutting area and on the acoustic skin; forming a solid replacement skin on the replacement cellular acoustic structure.

Growing community of inventors

Le Havre, France

John Moutier