Snecma

Safran Aircraft Engines

Dominique Magnaudeix

Jean-Michel Patrick Maurice Franchet

Gilles Charles Casimir Klein

Gilbert Michel Marin Leconte

Jean-Michel Franchet

Gilles Klein

Richard Mathon

Gilles Charles Klein

Jean-Michel Patrick Franchet

Gilbert Michel Leconte

Gilbert Leconte

Matthieu Arnaud Gimat

Bruno Jacques Gerard Dambrine

Thierry Godon

Yann Marchal

Raoul Jaussaud

Marc-Emmanuel Techer

Didier Queant

Emilie Lesizza

Denis Pingon

Noemie Souhaite

Matthieu Gimat

Noémie Souhaite

A repair method for repairing an assembly including a main body and an old reinforcement, the assembly including an initial hole passing through the old reinforcement and at least a portion of the main body, the method including removing the old reinforcement; positioning a plug in the initial hole in the main body; fastening a new reinforcement on the main body, the new reinforcement covering the plug; and forming a new hole passing through the new reinforcement and at least a portion of the main body.

Repair of an assembly comprising a main body and a reinforcement

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 for forming a preform for a hollow turbomachine component is provided. The method includes positioning a sheet made of woven fibers on a base equipped with a longitudinal impression; positioning a mandrel in the longitudinal impression to clamp the sheet between the base and the mandrel, the mandrel having a thickness that increases between a proximal end and a distal end; locking the distal end of the mandrel into position; placing a proximal block resting on the base; forming two flaps of the sheet around the flanks of the mandrel; resting two lateral blocks on the base on either side of the mandrel; locking the lateral blocks into position to form an assembly; drying the assembly to form a preform including a flat base, from which two flaps extend perpendicularly; and adjusting the flaps to the dimensions of the mandrel by trimming excess material.

Method for producing preforms

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

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 producing tooling for molding a part by resin transfer molding, including: producing a model of the part; producing a countermold with an outside surface presenting an indentation complementary to a first side of the model; placing the model in the indentation of the countermold; draping a plurality of superposed textile layers that are impregnated with thermosetting resin on the model and on the outside surface of the countermold to shape a first half-shell; curing the first half-shell; separating the countermold from the model and from the first half-shell; draping a plurality of superposed textile layers on the first half-shell and the first side of the model, to shape a second half-shell; and curing the second half-shell.

Method of producing tooling for resin transfer molding

A method for manufacturing a thick turbine engine part in a composite material by injection of resin under pressure. A fiber preform is positioned in a mold, a resin composition is injected into the mold, the resin composition is polymerized in the mold so as to obtain the part, and the part is removed from the mold. Prior to the injection of the resin composition, a mold release shim is inserted between the fibrous preform and a wall of the mold, and between the polymerization of the resin composition and the removal of the part from the mold, the mold release shim is extracted.

Method for manufacturing a turbine engine part by injection of resin under pressure

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

The invention provides an injection mold core () for making a composite material part having a closed box, the core being in the shape of a wedge that is to be inserted inside a closed box () of at least one fiber preform into which a matrix-precursor fluid is to be injected, the core presenting both an opening right section () through which the core is to be unmolded from the box of the preform after the matrix has set, and also a maximum right section () of greater size than the opening right section, the core comprising at least three distinct elements () that are assembled together, each core element presenting a maximum right section of size that is smaller than the opening section.

Injection mold core for making a part out of composite material, the part having a closed box

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

A method of fabricating a turbine engine blade out of composite material includes three-dimensionally weaving yarns to make a preform including root and airfoil portions that are connected together by oblique side faces for forming bearing surfaces enabling the root to bear against an assembly slot in a rotor disk. The method also includes compacting the preform in a mold having a cavity with first oblique side faces corresponding to the above-mentioned side faces of the preform, and second oblique side faces bearing against the root portion of the preform and at angles of inclination opposite to those of the first oblique side faces. Further, the method includes vacuum injecting a resin into the mold and polymerizing the resin.

Method of fabricating a turbine engine blade out of composite material

The invention provides tooling and a method for hot forging pieces of sheet metal that are to form metal reinforcement mounted on the leading or trailing edge of a turbine engine blade, by means of bottom and top matrices each presenting a twisted elongate surface for use in shaping an initially plane piece of sheet metal, the shaping surface of the bottom matrix presenting a high portion, a low portion, and two end zones. The bottom matrix includes studs for positioning and guiding the piece, the studs being situated at the periphery of the corresponding shaping surface.

Growing community of inventors

Yerres, France

Dominique Magnaudeix