Snecma

Snecma Moteurs

Safran Aircraft Engines

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Safran

Messier-bugatti-dowty

Association Pour La Recherche Et Le Developpement Des Methodes Et

Chief Controller Research and Development Defence Research and

Safran Landing Systems

Jean-Michel Franchet

Gilles Klein

Alain Lorieux

Daniel Lhomme

Patrick Gesmier

Richard Masson

Patrick Dunleavy

Pierre Jean Sallot

Dominique Magnaudeix

Jean-Pierre Ferte

Christophe Grosbois

Jean-François Fromentin

Gilbert Leconte

Alain Lasalmonie

Jean-Loup B Strudel

Tapash Kumar Nandy

Ashok Kumar Gogia

Dipankar Banerjee

Thierry Eric Carisey

Agathe Venard

Stéphane Leveque

Philippe Joffroy

Jean-Louis Despreaux

Agathe Marie Venard

Fromentin Jean-François

A method for manufacturing a titanium aluminide blade of a turbine engine, including production of a titanium aluminide ingot, extrusion of the ingot through an opening in a die having one main arm and at least one side arm, such as to obtain a extruded ingot having the shape of a bar with a cross-section having one main arm and at least one side arm substantially perpendicular to the main arm, transverse cutting of the extruded ingot such as to obtain sections of extruded ingot, forging of each section of extruded ingot such as to obtain a turbine engine blade.

Method for manufacturing a TiAl blade of a turbine engine

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

The invention relates to a method of manufacturing a hollow blade for turbine engine comprising a foot and a rotor blade, the method comprising a production stage of two external parts () as well as an assembling stage via diffusion bonding of these two external parts so as to obtain a blade preform.

Method of manufacturing a hollow blade for a turbine engine

A method for manufacturing an assembly including a stack of at least two primary parts, the primary parts being joined together around their periphery with the exception of a place forming a passage so as to define between the two of them a cavity, and the primary parts having, facing the cavity, at least one face that is covered, in a pattern, with a stop-off product containing a binder that can be thermally degraded, and a sealed reservoir having an open end, the end being joined in a sealed manner to the passage in the stack so as to allow communication between the internal space of the reservoir and the cavity, the reservoir being placed under a partial vacuum, this being produced so as to be non-deformable at the temperature and at the pressure at which the diffusion bonding of the said stack takes place.

Assembly for the manufacture of a hollow mechanical part by diffusion bonding and superplastic forming, use of such an assembly and process for manufacturing such a mechanical part

A titanium-based intermetallic alloy having a high yield stress, a high creep resistance and sufficient ductility at ambient temperature has the following chemical composition as measured in atomic percentages:

Titanium-based intermetallic alloys

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Paris, France

Jean-Michel Franchet