Snecma

Messier-Bugatti-Dowty

Safran Aircraft Engines

Safran Landing Systems

Gilles Klein

Richard Masson

Patrick Dunleavy

Dominique Magnaudeix

Jean-Michel Franchet

Louis Salvat

Christian Garnier

Alain Lorieux

Daniel Lhomme

Christophe Grosbois

Patrick Gesmier

Pierre Eric Frayssines

Jean-François Fromentin

Patrick Petitpas

Gilbert Leconte

Agathe Venard

Stéphane Leveque

Philippe Joffroy

Jean-Louis Despreaux

Jean Michel Franchet

Agathe Marie Venard

Jean- Michel Franchet

Mikaël Dumont

Fromentin Jean-François

Franchet Jean-Michel

During implementing a composite metal part by compaction of an insert having reinforcing fibers in a metal body or container, gas used for compaction may enter the cavity formed in the container for receiving the insert between a lid covering the insert and the container, which can prevent or degrade compaction and diffusion welding of fiber sheaths of the insert therebetween and/or with walls of the cavity. To solve this problem, the present method includes initiating isostatic compaction by a phase including raising and maintaining temperature, followed by a phase including hot-feeding pressurized gas, and machining an assembly to obtain the part. The temperature raising phase includes a diffusion pre-welding of material rigidly connecting the pressure-adjusted walls of the lid and the container. The method can be used for designing parts having a tensile and compression resistance, such as parts for aircraft landing gear.

Method for making a composite metal part having inner reinforcements in the form of fibers, blank for implementing same and metal part thus obtained

The present invention relates to a method of fabricating a metal link rod () that is longitudinally reinforced in its thickness by fiber reinforcement (), the method comprising the following steps: The invention also provides a link rod having a metal matrix in which reinforcing fibers are embedded that extend on either side of a longitudinal axis (X) of the link rod, the fibers leading into an edge face of the link rod.

Method for manufacturing a fiber-reinforced metal connecting rod, and resulting connecting rod

A process for manufacturing a component with an insert made of a composite is disclosed. The composite includes a metal matrix, within which ceramic fibers extend. The insert is made of a composite which is obtained from a plurality of coated filaments, each filament includes a ceramic fiber coated with a metal sheath. The process includes winding a bundle or bonded sheet of coated filaments around a body of revolution perpendicular to the axis of rotation of said body. The insert is then subjected to a hot isostatic pressing step in a container. The process is applied to the manufacture of aeronautical turbomachine components.

Process for manufacturing a component with an insert made of a composite consisting of a metal matrix and ceramic fibers

A process for manufacturing reinforcing parts () for leading edges () and/or trailing edges () of fan blades () is described. In particular, this invention relates to the use of the SPF/DB (&#x3c;&#x3c;Super Plastic Forming/Diffusion Bonding &#x3e;&#x3e;) process for this type of non-hollow part.

Process for manufacturing a reinforcing leading or trailing edge for a fan blade

A process for manufacturing a bonded sheet with a plurality of coated filaments, which include a ceramic fiber coated with a metal sheath, includes placing the filaments beside one another in one and the same plane, and welding the filaments together by laser spot welding.

Process for manufacturing a bonded sheet composed of ceramic filaments with a metal matrix, device for implementing said process, bonded sheet obtained by said process

A process for manufacturing a tubular component with an insert made of a metal matrix composite, within which ceramic fibers extend, includes a draping step, in which a bonded sheet of coated filaments is draped around a metal mandrel. Each filament includes a ceramic fiber coated with a metal sheath, and the filaments are bonded by spot welds.

Process for manufacturing a tubular component with an insert made of a metal matrix composite

A method of fabricating a hollow mechanical part includes a step of depositing an anti-diffusion substance in a predefined pattern on at least one face of primary parts to be assembled together. The depositing step is performed by applying a layer of anti-diffusion substance including a powder over a surface of the face of the primary parts; and by localized sintering of the anti-diffusion substance in the predefined pattern by the heating that results from localized application of a laser beam along a track.

Method of fabricating a hollow mechanical part by diffusion welding and superplastic forming

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Mery sur Oise, France

Gilles Klein