Abstract: A process for manufacturing a one-piece axisymmetric part includes: superposition, around a rotating cylindrical mandrel of at least respectively inner and outer metal-coated composite fibrous structures, wound in first and second crossed directions on the mandrel; arranging, between the crossed inner and outer fibrous structures, at least one layer of metallic wire; then placing a blank of the part, formed by the fibrous structures and the layer of metallic wire, in a tool to apply to the blank a hot isostatic pressing treatment, and to obtain the part.

Abstract: A method for producing a solid part, including weaving a three-dimensional fibrous structure, the weaving being carried out with metal braids consisting of a plurality of metal strands mutually twisted about the longitudinal axis of the braid; and performing hot isostatic pressing on the fibrous structure causing the agglomeration of the metal braids of the fibrous structure so as to produce a solid part.

Abstract: A method for making a metallic part, includes positioning at least one metallic coil formed from flexible metal foil including a plurality of notches, on a shaping tool, the at least one coil being manually deformable when cold along three directions in space (X, Y, Z); hot isostatic pressing the at least one metallic coil in a tool causing compaction of the metallic coil so as to obtain the metallic part.

Abstract: A method for manufacturing a metal part by producing a preform with a fibrous structure of metal fibers, and subjecting the preform to hot isostatic pressing in a tool until a solid part is obtained, the tool including at least one first element including a cavity for molding the part. The first tool element is elongate in a direction between two ends, and the fibrous structure is at least partially formed by winding at least one metal wire around the first tool element in the direction, from one end to the other. The method can be used, for example, for manufacturing reinforcement parts for a fan blade of a turbojet engine.

Abstract: A method of fabricating a single-piece part for a turbine engine by diffusion bonding, the method including making a blank for the part around a mandrel, the blank including a plurality of coaxial and superposed annular layers of independent rings of metal wire that are stacked on one another around the mandrel, and subjecting the blank to hot isostatic pressing to obtain a single-piece part, and optionally machining the part.

Abstract: A method for manufacturing an integral rotationally symmetrical part, which includes producing a blank of the part around a cylindrical mandrel, the blank including at least one fibrous structure made of composite ceramic fibers coated with metal, followed by a diffusion-welding treatment of the blank by hot isostatic pressing, and optionally machining the thus-treated blank to obtain the part. The blank includes at least a first metal-wire layer between the mandrel and the composite fibrous structure, and at least a second metal-wire layer arranged around the composite fibrous structure to cover the composite fibrous structure.

Abstract: A method of fastening structural metal reinforcement on a portion of a gas turbine blade made of composite material and an injection mold for performing the method, the method including positioning the structural metal reinforcement in an injection mold, positioning the portion of the blade onto which the structural metal reinforcement is to be fastened in the injection mold, the portion of the blade and the structural metal reinforcement being positioned relative to each other in their final relative position while leaving between them a gap, injecting adhesive into the gap between the structural metal reinforcement and the portion of the blade onto which the structural metal reinforcement is to be fastened, and polymerizing the adhesive.

Abstract: 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.

Abstract: A method for manufacturing a cylindrical part from composite material, and a molding device to implement the method, the method including: installation of a fibrous structure on a horizontal mandrel; formation of an annular enclosure for molding around the fibrous structure and the mandrel; supply of the enclosure with resin via a first axial end, while keeping a second axial end of the enclosure at a pressure lower than a supply pressure of the resin. The second end includes at least two sectors of vents in a form of ring sectors, each being independently kept at a pressure lower than the supply pressure.

Abstract: The invention relates to a method of injection molding a part (1) made of composite material, the method consisting in placing a preform in a mold, in injecting a resin into the mold so as to impregnate the preform, and in unmolding the part (1) after curing the resin, the method being characterized in that it also consists in subjecting the resin and the preform to pressure inside the mold while the resin is curing, e.g. by injecting a gas under pressure into the mold via a plurality of points (2, 4, 5, 6).

Abstract: A method of fabricating a single-piece part for a turbine engine by diffusion bonding, the method including making a blank for the part around a mandrel, the blank including a plurality of coaxial and superposed annular layers of independent rings of metal wire that are stacked on one another around the mandrel, and subjecting the blank to hot isostatic pressing to obtain a single-piece part, and optionally machining the part.

Abstract: The invention relates to a gas turbine fan casing (10) comprising an annular casing wall (12) centered on a longitudinal axis (X-X) of the casing and at least one fastening belt (100) mounted on the periphery of the casing wall to fasten equipment on the casing, each fastening belt comprising two distinct annular flanges (102, 104) each having an L-shaped straight section, said flanges being fastened to each other and maintained on the wall of the casing by tightening of the inverted cone type.

Abstract: A process for manufacturing a one-piece axisymmetric part includes: superposition, around a rotating cylindrical mandrel of at least respectively inner and outer metal-coated composite fibrous structures, wound in first and second crossed directions on the mandrel; arranging, between the crossed inner and outer fibrous structures, at least one layer of metallic wire; then placing a blank of the part, formed by the fibrous structures and the layer of metallic wire, in a tool to apply to the blank a hot isostatic pressing treatment, and to obtain the part.

Abstract: A method for manufacturing an integral rotationally symmetrical part, which includes producing a blank of the part around a cylindrical mandrel, the blank including at least one fibrous structure made of composite ceramic fibers coated with metal, followed by a diffusion-welding treatment of the blank by hot isostatic pressing, and optionally machining the thus-treated blank to obtain the part. The blank includes at least a first metal-wire layer between the mandrel and the composite fibrous structure, and at least a second metal-wire layer arranged around the composite fibrous structure to cover the composite fibrous structure.

Abstract: A process for manufacturing a metal part such as a metal reinforcement for the blade of a turbine engine, which includes: manufacturing a three-dimensional metal structure made up of an insert which exhibits properties which allow superplastic forming and diffusion welding to be carried out, and of multiple metal wires encircling the periphery of the insert, where the metal structure forms a preform of the metal part; positioning the metal structure in a forming tool and hot-pressing the three-dimensional metal structure which causes agglomeration of the metal structure so as to obtain the compact metal part.

Abstract: A method for producing a metal component such as a metal turbomachine blade reinforcement, includes positioning a plurality of metal staples in a forming tool having a die and a punch; and hot isostatic pressing the plurality of metal staples causing the agglomeration of the metal staples so as to obtain a solid component.

Abstract: A reinforcing fiber structure woven as a single piece for fabricating a composite material part and including: first and second fiber substructures, each fiber substructure including at least one independent portion obtained by multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns that are independent from the other substructure; and an assembly portion between the least first and second fiber substructures in which a plurality of adjacent layers of warp yarns of the first fiber substructure are interlinked by at least some of the warp yarns of the second fiber substructure.

Abstract: A method for manufacturing a metal part by producing a preform with a fibrous structure of metal fibers, and subjecting the preform to hot isostatic pressing in a tool until a solid part is obtained, the tool including at least one first element including a cavity for molding the part. The first tool element is elongate in a direction between two ends, and the fibrous structure is at least partially formed by winding at least one metal wire around the first tool element in the direction, from one end to the other. The method can be used, for example, for manufacturing reinforcement parts for a fan blade of a turbojet engine.

Abstract: A method for producing a reinforced metal part, includes: cutting out a plurality of metal foils from at least one flexible metal sheet, the foils substantially corresponding to the blank of said metal part to be produced; rigidly connecting at least one metal reinforcing wire to at least one metal foil, the metal wire being positioned depending on the orientation of the desired structural reinforcement; making a plurality of reinforced metal pockets, each metal pocket being made from two reinforced metal foils; positioning the plurality of reinforced metal pockets in shaping equipment; performing a isostatically hot-pressing of the reinforced metal pockets, causing the metal pockets and the metal reinforcing wire to be bonded together so as to produce the metal part incorporating the structural reinforcement.

Abstract: A fiber structure made as a single piece by multilayer weaving using a method including weaving warp yarns of at least a first set of layers of warp yarns with weft yarns including at least some that are woven with extra length so as to have warp yarn end portions available that extend beyond the zone of weaving, the warp yam end portions being returned to be woven with warp yarns by being reinserted in layers of warp yarns, and a hollow, or tubular, portion being formed by looping the first woven set of layers of warp yarns back onto itself and applying traction to the ends of the reinserted weft yarns so that a fiber preform for a part including a hollow portion can be obtained as a single piece.