Snecma

Messier-Bugatti-Dowty

Safran

Safran Aircraft Engines

Snecma Moteurs

Office National D'etudes Et De Recherches Aerospatiales

Cnrs

Hurel Hispano

Fsp-One

Centre National De La Recherche Scientifique

Safran Landing Systems

Institut Polytechnique De Bordeaux

Hurel Hispano Le-Havre

Université De Bordeaux 1

Jean-Michel Patrick Maurice Franchet

Gilles Charles Casimir Klein

Dominique Magnaudeix

Gilbert Michel Marin Leconte

Richard Masson

Louis Salvat

Patrick Dunleavy

Pierre Eric Frayssines

Christian Garnier

Pierre Jean Sallot

Jean-Pierre Ferte

Gerald Sanchez

Patrick Petitpas

Mikael Dumont

Dominique Michel Serge Magnaudeix

Vikas Kumar

Michel Breton

Jean-Pierre Bergue

Alain Georges Henri Lorieux

Alain Lorieux

Jean-Francois Fromentin

Didier Locq

Yann Lepetitcorps

Jérôme Roger

Jean-Yves Guedou

Jean-François Fromentin

Patrick Gesmier

Philippe Francois Christian Sagot

Anne-Laure Rouffie

Dipankar Banerjee

Jean-Michel Quenisset

Stéphane André Leveque

Françoise Bertrand

Benoit Antoine Yves Marty

Edmond Paul Szkolnik

Olivier Daniel Lamy

Corinne Arvieu

Carine Duda

Jean-Loup Bernard Victor Strudel

Laurent Germann

Jean-Louis Paul Victor Despreaux

Tapash Nandy

Gérald Sanchez

Philippe Joffroy

Duda Carine

Daniel Gaston Lhomme

Delphine Vermaut

Benoît Sergent

Olivier Michaël Molinari

Guillaume Duclos

Eric Arquis

Denis Fleche

A method for manufacturing a metal bladed wheel of a turbomachine reinforced by an insert made of metal matrix composite material, includes winding the ceramic fibers around a mandrel in order to form the insert, the ceramic fibers being surrounded by a material constituting the matrix; and spark plasma sintering the insert with a powder of metal constituting the bladed wheel to be manufactured.

Method for manufacturing a composite turbomachine bladed disk (BLISK) with ceramic reinforcement

A Nickel-based superalloy, whose composition includes, in percent by weight of the total composition: Chromium: 10.0-11.25; Cobalt: 11.2-13.7; Molybdenum: 3.1-3.8; Tungsten: 3.1-3.8; Aluminium: 2.9-3.5; Titanium: 4.6-5.6; Niobium: 1.9-2.3; Hafnium: 0.25-0.35; Zirconium: 0.040-0.060; Carbon: 0.010-0.030; Boron: 0.01-0.030; Nickel: remainder as well as unavoidable impurities; the composition being free of tantalum.

Nickel-based superalloy

The invention concerns a method for coating a core () for producing a turbomachine part () by isostatic compacting, for example a leading-edge shield of a blade, the coating method comprising the steps of:&#x2014;S: covering the core () by means of a first solution comprising a first refractory component configured to oppose the diffusion of species, the first component comprising a metal oxide,&#x2014;S: covering the core () by means of a second solution comprising a second component designed to bind the first component in such a way as to form a homogeneous layer, the second component comprising a mineral binder;&#x2014;S: applying a heat treatment to the covered core () in such a way as to dry the solution and solidify the coating.

Coating for hot-shaping core

A device for generating a microstructure with a structure gradient in an axisymmetric mechanical part having a hollow center and initially possessing a uniform structure with fine grains, the device including a first heater system defining a first shell for receiving the mechanical part and suitable for heating the outer periphery of the mechanical part to a first temperature higher than the solvus temperature. The device further includes a second heater system defining a second shell arranged inside the first shell and suitable for heating the inner periphery of the mechanical part to a second temperature lower than the solvus temperature, with the space between the first shell and the second shell defining a housing suitable for receiving the axisymmetric mechanical part having a hollow center.

Device for generating a microstructure with a structural gradient in an axisymmetric part

A field of rotary blades, and more particularly to a method of fabricating a leading edge shield for protecting such a blade. The method includes at least steps of performing initial plastic deformation on at least one sheet from a pressure side sheet and a suction side sheet, using additive fabrication to add a reinforcement with a fiber insert on at least one of the pressure and suction side sheets, closing the pressure and suction side sheets around a core after the initial plastic deformation and after adding the reinforcement, performing subsequent plastic deformation by pressing the pressure and suction side sheets against an outside surface of the core after the sheets have been closed around the core, and extracting the core.

Method of manufacturing a leading edge shield

A titanium-based intermetallic alloy includes, in atomic percent, 16% to 26% Al, 18% to 28% Nb, 0% to 3% of a metal M selected from Mo, W, Hf, and V, 0.1% to 2% of Si, 0% to 2% of Ta, 1% to 4% of Zr, with the condition Fe+Ni&#x2264;400 ppm, the balance being Ti, the alloy also presenting an Al/Nb ratio in atomic percent lying in the range 1.05 to 1.15.

Titanium-based intermetallic alloy

A method for producing a metal reinforcement for protecting a leading edge of a compressor blade of composite, including: creating a core that has a shape of an internal cavity of the reinforcement; creating an insert made of an alloy of a hardness greater than that of the reinforcement; shaping sheet metal by stamping with the creation, upstream of the core, a cavity between the metal sheets, which cavity is configured to accept the insert, positioning the sheets around the core with the insert placed in the cavity and securing the assembly together; creating a vacuum and closing the assembly by welding; consolidation by hot isostatic pressing; cutting the assembly to extract the core and separate the reinforcement; creating an external profile of the reinforcement by a final machining operation that reveals a material of the insert.

Method for creating a metal reinforcement with insert for protecting a leading edge made of composite

A method of making a metal reinforcing member that is to be mounted on a leading edge or a trailing edge of a composite blade of a turbine engine, the method including: shaping two metal sheets, positioning them on either side of a core including at least one recess that is to form a mold for a spacer for positioning the reinforcing member, assembling them together under a vacuum, conforming them against the core by hot isostatic compression, and cutting them to separate the reinforcing member and release the core.

Method of making a metal reinforcing member for a blade of a turbine engine

A device for metal coating of fibers, for example ceramic fibers, by a liquid process, the device including a crucible containing a liquid metal bath through which a fiber is drawn to be coated with the metal, and a cooling system positioned downstream from the metal bath to solidify the metal sheath created around the fiber by capillarity. The cooling system includes at least one nozzle for ejecting a compressed gas towards the coated fiber, and the system is sized such as to solidify the metal on the periphery of the coated fiber over a length of no more than 200 mm.

Device for obtaining ceramic fibers coated by a liquid process with a thick metal sheath

In structural reinforcement for a composite blade of a turbine engine, the reinforcement being for adhesively bonding to a leading edge of the blade and presenting over its full height a section that is substantially V-shaped, having a base that is extended by two lateral flanks, there is provided an assembly of a plurality of fiber bundles that is mounted in at least one housing in the base, which assembly defines fiber content that varies along the full height of the housing.

Metal structural reinforcement for a composite turbine engine blade

A method of reinforcing a mechanical part, for example a turbine engine part, the part being made by assembling together two portions, the method including: inserting reinforcing mechanisms of elongate shape at least in part in at least one recess formed in one of the portions and opening out into a junction surface between the portions; and assembling the two portions together.

Method of reinforcing a mechanical part

A metal reinforcing piece for mounting on a leading edge or trailing edge of a composite blade for a turbine engine is made by shaping two metal sheets, positioning them on either side of a core, assembling the two sheets together around the core under a vacuum, shaping them on the core by hot isostatic compression, and cutting them to separate the reinforcing piece and release the core. A predetermined roughness is given to at least a portion of the surface of the core and is transferred to a corresponding portion of an inside surface of the reinforcing piece by the hot isostatic compression.

Method of making a metal reinforcing piece

A device for shaping a metal sheet by die stamping, the device including first and second trunnions configured to be fastened respectively to two opposite ends of a sheet, the sheet being configured to be shaped by die stamping, wherein the first and second trunnions define respective first and second bearing surfaces configured respectively to guide turning of the trunnions, the first bearing surface defining a peripheral groove around a pivot axis of the first trunnion while the second bearing surface is smooth along a pivot axis of the second trunnion.

Device for shaping a metal sheet by die stamping

A method of manufacturing a mechanical component, and winding device to implementing the method. The component includes at least one insert of metal matrix composite, within which matrix ceramic fibers extend, the composite insert obtained from a plurality of coated filaments each including a ceramic fiber coated with a metal sheath. The method manufactures an insert preform by winding a bonded lap or bundle of coated filaments about a cylindrical component. At least some of the winding is performed in at least one rectilinear direction. The method further inserts the insert preform in a first container; performs hot isostatic compaction of the first container; and machines the first container to form a rectilinear insert.

Mechanical component comprising an insert made of composite

The invention provides a method of making a piece of metal reinforcement for mounting on the leading or trailing edge of a composite turbine engine blade, the method comprising the steps consisting in positioning two metal sheets () on either side of a core (), in shaping the sheets () on the core () by hot isostatic compression, and in cutting the sheets () in order to separate the reinforcement along at least one line of cut and in order to release the core. The core () has projecting sacrificial zones (), with the sheets () being cut along the sacrificial zones () without degrading the remainder of the core ().

Method of making a piece of metal reinforcement

Growing community of inventors

Paris, France

Jean-Michel Patrick Maurice Franchet