Abstract: A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; impregnating the fiber texture for a first time with a first slip containing first refractory particles; eliminating the liquid phase from the first slip so as to leave within the texture only the first refractory particles; impregnating the fiber texture for a second time with a second slip containing second refractory particles; eliminating the liquid phase from the second slip so as to leave within the texture only the second refractory particles and obtain a fiber preform filled with the first and second refractory particles; and sintering the first and second refractory particles present in the fiber preform in order to form a refractory matrix in the preform.

Abstract: An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade.

Abstract: A method of making a fiber preform, and the preform, for fabricating a turbine engine blade out of composite material, the method including: making a single-piece fiber blank by three-dimensional weaving with layers of longitudinal yarns interlinked by yarns of layers of transverse yarns; and shaping the fiber blank to obtain a single-piece fiber preform including a portion forming an airfoil preform and at least one portion forming a platform preform. During weaving, yarns of a first group of longitudinal yarns are extracted from the fiber blank beside one of side faces of the blank to form a portion corresponding to a blade platform preform, and yarns of a second group of longitudinal yarns are inserted into the fiber blank with mutual crossing of the yarns of the first group and the yarns of the second group.

Abstract: A method of injection molding a part made of composite material is provided. The method includes placing a preform in a mold; injecting a resin into the mold so as to impregnate the preform; unmolding the part after curing the resin; and subjecting the resin and the preform to pressure inside the mold while the resin is curing.

Abstract: A fiber structure reinforcing a composite material part woven as a single piece by multilayer weaving between plural first and second layers of yarns. The fiber structure includes a portion of decreasing thickness that presents: plural yarn withdrawal parts in surface continuity, with yarns interrupted from the first plural layers of yarns underlying the layer of yarns of the first plural layers of yarns situated in the surface of the structure; and plural yarn withdrawal parts in surface discontinuity, with yarns interrupted from the first plural layers of yarns situated at the surface of the structure, each interrupted yarn replaced in the surface of the structure by a yarn of a layer of yarns underlying the first plural layers of yarns. The yarns of the second plural layers of yarns situated in the surface of the fiber structure are continuous over at least the entire portion of decreasing thickness.

Abstract: A method for the production of a fibrous metal structure by weaving with metal weft yarns and metal warp yarns. The method includes weaving the fibrous structure by successive weaving of metal clasps that are used as weft yarns. For the purpose of weaving, each of the arms of each of the metal clasps is introduced into at least one shed, each shed being formed by two warp yarns.

Abstract: A fiber structure for reinforcing a composite material part, the structure being woven as a single piece by multilayer weaving between a first plurality of layers of yarns extending in a first direction and a second plurality of layers of yarns extending in a second direction. The second plurality of layers of yarns includes at least one layer of variable-weight yarns, each variable-weight yarn including a separable assembly of individual yarns, each having a determined weight. The fiber structure includes at least one portion of reduced thickness in which the variable-weight yarn presents a weight that is less than the weight that it presents prior to the reduced thickness portion.

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 yarn 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.

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 yarn 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.

Abstract: A fiber preform for a hollow turbine engine vane, and a method of fabricating such a hollow vane are provided. The preform includes a first fiber structure including a main longitudinal portion for forming a pressure side wall of an airfoil; a second fiber structure including a main longitudinal portion for forming a suction side wall of the airfoil; each of the first and second fiber structures includes a first interlinking zone extending along the front edge of its main longitudinal portion, which first zones are integral with each other and form a first interlinking portion, and a second interlinking zone extending along the rear edge of its main longitudinal portion, the second zones being integral with each other and forming a second interlinking portion. The main longitudinal portions of the first and second fiber structures are dissociated so as to leave a gap between the main longitudinal portions forming an airfoil hollow.

Abstract: A fiber preform for a hollow turbine engine vane, the preform including a main fiber structure obtained by three-dimensional weaving and including at least one main part, wherein the main part extends from a first link strip, includes a first main longitudinal portion forming a pressure side wall of an airfoil, an U-turn bend portion forming a leading edge or a trailing edge of the airfoil, a second main longitudinal portion facing the first main longitudinal portion and forming a suction side wall of the airfoil, and terminating at a second link strip. The first and second link strips are secured to each other and form a link portion of the main fiber structure. The main longitudinal portions are spaced apart so as to form a gap between the main longitudinal portions forming a hollow in the airfoil.

Abstract: The invention relates to fiber reinforcement for making an elongate mechanical part (10) out of composite material having a lug (14) at at least one end for receiving a pin for making a pivot connection with another part, the fiber reinforcement being made from a central fiber structure (106; 106?) for forming a core that is obtained by three-dimensional weaving, from a peripheral fiber structure (16; 16?) that is to form a belt surrounding the central structure so as to form at least one empty cylindrical space in the lug of the part, and from at least one annular fiber structure (112; 112?; 112?) that is to form a ring that is formed inside the empty space provided between the central structure and the peripheral structure.

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 reinforcing fiber structure for a composite material part is woven as a single piece by multilayer weaving between plural layers of weft yarns and plural layers of warp yarns arranged in adjacent manner between two faces of the structure. The fiber structure includes at least one arcuate portion extending over one of the faces of the fiber structure, the arcuate portion including at least some of the warp yarns continuous with at least two adjacent warp yarn layers present on one of the faces of the structure. The warp yarns of the arcuate portion are of a length that is longer than the warp yarns of at least two underlying warp yarn layers of the structure. In addition, the warp yarns of the arcuate portion are not interlinked with other warp yarns of the fiber structure.

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 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 reinforcement for the leading edge or trailing edge of a turbomachine blade, the method including cutting a plurality of metal foils from a flexible metal sheet, corresponding substantially to the developed length of the leading or trailing edge metal reinforcement; producing a plurality of metal pockets, each pocket being produced from two of the metal foils obtained during the cutting; stacking the metal pockets one inside the other, such as to form a preform of the leading or trailing edge metal reinforcement; and hot isostatic pressing the preform, causing the metal pockets to bond to one another, so as to produce the leading or trailing edge metal reinforcement.

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.