Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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 (1) on either side of a core (2), in shaping the sheets (1) on the core (2) by hot isostatic compression, and in cutting the sheets (1) in order to separate the reinforcement along at least one line of cut and in order to release the core. The core (2) has projecting sacrificial zones (13), with the sheets (1) being cut along the sacrificial zones (13) without degrading the remainder of the core (2).

Abstract: A method for manufacturing a straight insert intended to be incorporated in a metal container by HIC includes placing coated wires in a rectilinear juxtaposition over a predefined length in a straight gutter-shaped tool and joining the coated wires together. The insert includes a bundle of coated wires that are joined together and have a predefined length. The wires are made from metal-coated ceramic fibers.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A method of depositing a coating of a first metal alloy on a fiber extending in a main direction, including: a) heating a first mass of a first metal alloy above its melting temperature; and b) moving the fiber through the liquid first mass to be covered by a coating of a non-zero thickness over the entire periphery of the fiber; and prior to a): i) providing a second mass of a second metal alloy having a higher melting temperature than the first alloy; j) heating the second mass to above its melting temperature to be in its liquid state and then moving the fiber through the second alloy such that the second alloy is taken up under visco-capillary conditions and the fiber becomes covered over a portion by a coating of the second alloy of non-zero thickness; and k) cooling the second coating until it becomes solid.

Abstract: A method of manufacturing a mechanical component, a mechanical component thus obtained, and a winding device designed for implementing the method of manufacture. The mechanical component includes at least one insert made of metal matrix composite, within which matrix ceramic fibers extend, the composite insert being obtained from a plurality of coated filaments each including a ceramic fiber coated with a metal sheath, the method including manufacturing at least one insert by winding a bonded lap or bundle of coated filaments about a component of revolution. At least some of the winding is performed in a rectilinear direction.

Abstract: A method of coating ceramic material fibers in metal using a liquid technique and a device implementing the method. The method maintains a charge of molten metal in levitation in a substantially spherical shape inside a crucible and causes a tensioned ceramic material fiber to travel at a predetermined speed between a bottom pulley and a top pulley disposed on either side of the crucible such that a portion of fiber is immersed in the charge to be covered in a metal coating. During coating, the portion of fiber that is immersed in the charge is shifted as a function of the remaining volume of the charge such that the instantaneous height of fiber that is immersed in the charge remains substantially constant throughout the coating operation.

Abstract: A method reinforcing an axisymmetric annular metal part by including a winding of composite material. A metal blank for the part is prepared, a cavity is formed therein that opens out into a coaxial inside face thereof, and that presents a right cross-section of axial extent that decreases from the inside towards the outside, a reinforcing yarn is wound in the cavity, the cavity is closed, the assembly is subjected to a hot isostatic compression process, and the blank is machined to obtain a final part.

Abstract: 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.

Abstract: A method for producing a metal insert for protecting a leading or trailing edge of a compressor vane of an aeronautical machine made of a composite material, by stamping sheets and diffusion bonding between the sheets. The method includes: initially shaping the sheets by stamping to approximate the sheets to a shape of a suction side and pressure side of the insert; producing a core shaped inner cavity of the metal insert to be manufactured, one of the surfaces thereof reproducing an inner shape of the suction side of the insert and the other surface reproducing an inner shape of the pressure side of the insert; positioning the sheets around the core and securing the assembly; applying a vacuum and sealing the assembly by bonding; assembling the assembly by hot isostatic compression; cutting the assembly to extract the core and separate the insert; producing an outer profile of the insert by a final machining.

Abstract: 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.

Abstract: A method of manufacturing an elongate insert configured to be integrated by CIC in a metal container, including coated yarns bonded together, the coated yarns being formed from metal-coated ceramic fibers. The method includes placing the coated yarns side by side in a bundle and pulling the fiber bundle through a shaping element so as to compact the fiber bundle transversely while forming the fiber bundle so as to have a defined cross section. A metal part incorporating a fibrous insert can be manufactured by the CIC technique.

Abstract: 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.

Abstract: 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.

Abstract: 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 (1) on either side of a core (2), in shaping the sheets (1) on the core (2) by hot isostatic compression, and in cutting the sheets (1) in order to separate the reinforcement along at least one line of cut and in order to release the core. The core (2) has projecting sacrificial zones (13), with the sheets (1) being cut along the sacrificial zones (13) without degrading the remainder of the core (2).

Abstract: A method of manufacturing an elongate insert configured to be integrated by CIC in a metal container, including coated yarns bonded together, the coated yarns being formed from metal-coated ceramic fibers. The method includes placing the coated yarns side by side in a bundle and pulling the fiber bundle through a shaping element so as to compact the fiber bundle transversely while forming the fiber bundle so as to have a defined cross section. A metal part incorporating a fibrous insert can be manufactured by the CIC technique.