Abstract: A method for manufacturing a turbomachine blade made of ceramic matrix composite component includes at least a structural part and a functional part secured to the structural part, the method including obtaining an assembly including a first preform of the functional part that is mounted on a second preform of the structural part or on the structural part, the first preform including a fibrous reinforcement of short fibres, and the second preform or the structural part comprising a woven fibrous reinforcement, and densification of the first preform of the assembly by infiltration with a molten composition.

Abstract: A method for manufacturing a turbomachine blade made of ceramic matrix composite component includes at least a structural part and a functional part secured to the structural part, the method including obtaining an assembly including a first preform of the functional part that is mounted on a second preform of the structural part or on the structural part, the first preform including a fibrous reinforcement of short fibres, and the second preform or the structural part comprising a woven fibrous reinforcement, and densification of the first preform of the assembly by infiltration with a molten composition.

Abstract: An assembly for a turbine includes a plurality of sectors which are adjacent to one another, each sector including at least one connecting edge of composite material with a ceramic matrix, each connecting edge including at least one groove and a sealing tongue present in each groove. Each sealing tongue has a laminated structure comprising a plurality of strips the lower strip and the upper strip of the laminated structure, each being formed by a film of monolithic ceramic material.

Abstract: A porous ceramic structure intended to form the reinforcement of a ceramic matrix composite component, the structure having a connected porosity delimited by an internal surface which includes a plurality of first points, each first point being associated with a second point aligned with this first point along a normal to the internal surface taken at the first point, the structure being divisible into a plurality of unit volumes of a size less than or equal to 5 mm3 in each of which: a characteristic pore length, corresponding to the maximum of the distance separating each first point from its associated second point, is less than or equal to 0.5 mm; and a porosity ratio is greater than or equal to 50%.

Abstract: A method of fabricating a CMC part, includes coating a plurality of tows with an interphase by transporting the tows through a treatment chamber in which a gas phase is injected, the tows being tensioned during their transport and the interphase being formed by vapor deposition from the injected gas phase; forming a fiber preform by performing three-dimensional weaving using the tows coated with the interphase; and forming a consolidated fiber preform by treating the fiber preform by chemical vapor infiltration to form a consolidation phase on the interphase, the consolidation phase comprising silicon carbide and having a Young's modulus greater than or equal to 350 GPa.

Abstract: A process for manufacturing a part made of composite material with a matrix at least predominantly made of ceramic includes producing a fibrous structure by three-dimensional or multilayer weaving; shaping the fibrous structure to form a fibrous preform core; depositing an interphase on the fibers of the preform core; consolidating the preform core by partial densification of the core including the formation of a matrix phase by chemical vapor infiltration or by a liquid process; depositing a powder of ceramic particles in the porosity of the preform core; draping one or more layers of pre-impregnated non-woven fibers over all or part of the outer surface of the preform core; heat treatment of the preform core and of the pre-impregnated layer(s) to form a hybrid fibrous preform; further densifying by infiltration of the hybrid fibrous preform with an infiltration composition containing at least silicon to obtain a ceramic matrix composite part.

Abstract: A method of fabricating an element (25) out of composite material, the element comprising three arms (22, 23, 24) arranged in a triangle. The method comprises the operations of: fabricating a three-dimensionally woven preform from reinforcing fibers and including through slots defining two arms (22, 23) and two half-arms that are all parallel and contiguous in pairs, each arm (22, 23) having one end whereby it is connected to a half-arm and another end whereby it is connected to the other arm (22, 23); shaping the preform by deploying it and by uniting its two half-arms in order to give it a triangle configuration; securing together the half-arms by stitching with reinforcing fibers; and injecting resin into the preform and polymerizing the resin.

Abstract: A method of fabricating a connecting rod (6) out of composite material using three-dimensional fabric of woven reinforcing fibers, the connecting rod (6) extending in a main direction. The method comprises the steps of: cutting out one or more base pieces (7, 8) from a three-dimensional fabric; cutting out one or more reinforcing pieces (9, 10) from a three-dimensional fabric; installing the various pieces (7, 8, 9, 10) on a support in order to shape them; securing the various pieces (7, 8, 9, 10) to one another by stitching (12, 13, 14, 15) using reinforcing fibers in order to constitute a reinforcing fiber preform; installing the preform on a mandrel; and injecting resin into the preform and polymerizing the resin.

Abstract: A method of fabricating an element (25) out of composite material, the element comprising three arms (22, 23, 24) arranged in a triangle. The method comprises the operations of: fabricating a three-dimensionally woven preform from reinforcing fibers and including through slots defining two arms (22, 23) and two half-arms that are all parallel and contiguous in pairs, each arm (22, 23) having one end whereby it is connected to a half-arm and another end whereby it is connected to the other arm (22, 23); shaping the preform by deploying it and by uniting its two half-arms in order to give it a triangle configuration; securing together the half-arms by stitching with reinforcing fibers; and injecting resin into the preform and polymerizing the resin.