Abstract: Method for manufacturing a CMC, i.e. ceramic matrix composite material, part provided with at least one cutout, as well as to such a CMC part provided with at least one cutout, the method comprising the following steps: providing (E1) a fibrous reinforcement (10), forming (E2?) a cavity in a portion of the fibrous reinforcement (10), injecting (E3) a slip comprising at least a ceramic powder and a solvent, the slip being injected so as to impregnate the fibrous reinforcement (10?) and to fill the cavity of the fibrous reinforcement (10?), drying (E4) the obtained assembly, carrying out a densification (E6) by infiltration of a liquid densification material and solidification of said densification material, machining (E7) at least one cutout in the obtained blank (30) within the volume corresponding to the cavity of the fibrous reinforcement (10).

Abstract: A turbine stator blade made of ceramic matrix composite material includes a hollow blade profile and has a trailing edge and a leading edge, the blade including a first portion including an extrados face and a second portion distinct from the first portion including an intrados face, the first and second portions being connected to one another by a connection interface present at least on the trailing edge or leading edge, the connecting interface including a region of overlap between the first and second portions present on at least one longitudinal end of the blade profile and intended to be present outside a flow path of a gas stream of the turbine, the blade also including a platform present at a longitudinal end of the blade profile and that includes a first portion integral with the extrados face and a second part integral with the intrados face.

Abstract: A turbine stator blade made of ceramic matrix composite material includes a hollow blade profile and has a trailing edge and a leading edge, the blade including a first portion including an extrados face and a second portion distinct from the first portion including an intrados face, the first and second portions being connected to one another by a connection interface present at least on the trailing edge or leading edge, the connecting interface including a region of overlap between the first and second portions present on at least one longitudinal end of the blade profile and intended to be present outside a flow path of a gas stream of the turbine, the blade also including a platform present at a longitudinal end of the blade profile and that includes a first portion integral with the extrados face and a second part integral with the intrados face.

Abstract: Assembly in a turbine comprising: —at least one turbine ring made of a ceramic composite having a silicon carbide SiC matrix and fibers, the ring comprising a plurality of sectors (10) arranged circumferentially end to end, each of the ring sectors (10) comprises at least one circumferential edge (26, 28) provided with at least one slot (30a, 30b, 30c) opening circumferentially, —at least one sealing member being inserted for a first part into one of the slots (30a, 30b, 30c) of an edge of a first ring sector and for a second part into one of the slots (30a, 30b, 30c) of an edge of a second ring sector, circumferentially adjacent to the first ring sector, the assembly being characterized in that the sealing member is made of a ceramic matrix composite.

Abstract: A method for producing a hollow part made of a ceramic matrix composite material. The method includes shaping a hollow fibrous preform. A core of oxidizable material is housed or inserted into the preform. The method also includes consolidating the preform and extracting the core by oxidising the core.

Abstract: A method for producing a consolidated fiber preform intended for the manufacture of a part made of composite material, includes shaping a fiber texture in a heated metal mold, the texture being pre-impregnated with a transient or fugitive material, or shaping a fiber texture in a metal mold and injecting a transient or fugitive material into the fiber texture held in shape in the metal mold, cooling the mold, removing the set fiber preform from the mold, coating the fiber preform with a slurry containing a powder of ceramic or carbon particles, heat-treating the coated fiber preform so as to form a porous shell around the fiber preform by consolidation of the slurry and so as to remove the transient or fugitive material present in the fiber preform, consolidating the fiber preform by gas-phase chemical infiltration.

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 for producing a consolidated fiber preform intended for the manufacture of a part made of composite material, includes shaping a fiber texture in a heated metal mold, the texture being pre-impregnated with a transient or fugitive material, or shaping a fiber texture in a metal mold and injecting a transient or fugitive material into the fiber texture held in shape in the metal mold, cooling the mold, removing the set fiber preform from the mold, coating the fiber preform with a slurry containing a powder of ceramic or carbon particles, heat-treating the coated fiber preform so as to form a porous shell around the fiber preform by consolidation of the slurry and so as to remove the transient or fugitive material present in the fiber preform, consolidating the fiber preform by gas-phase chemical infiltration.

Abstract: The invention relates to a method for producing a hollow part made of a ceramic matrix composite material comprising the steps of: shaping a hollow fibrous preform, a core of oxidizable material being housed or inserted into the preform (E1); consolidating said preform (E3, E4); and extracting the core by oxidising said core (E5).

Abstract: Method for manufacturing a CMC, i.e. ceramic matrix composite material, part provided with at least one cutout, as well as to such a CMC part provided with at least one cutout, the method comprising the following steps: providing (E1) a fibrous reinforcement (10), forming (E2?) a cavity in a portion of the fibrous reinforcement (10), injecting (E3) a slip comprising at least a ceramic powder and a solvent, the slip being injected so as to impregnate the fibrous reinforcement (10?) and to fill the cavity of the fibrous reinforcement (10?), drying (E4) the obtained assembly, carrying out a densification (E6) by infiltration of a liquid densification material and solidification of said densification material, machining (E7) at least one cutout in the obtained blank (30) within the volume corresponding to the cavity of the fibrous reinforcement (10).

Abstract: An aluminization process by vapor phase deposition for high-temperature oxidation protection of a metal turbomachine part. The part including a cavity into which a metal component is introduced and assembled from an opening in the part. A halide is formed by reaction between a halogen and a metal donor containing aluminum, then the halide is transported by a carrier gas in order to come into contact with the metal part, wherein the metal component has first, before the implementation of the process, been surface-enriched with aluminum in order to serve as an aluminum donor.

Abstract: An aluminization process by vapor phase deposition for high-temperature oxidation protection of a metal turbomachine part. The part including a cavity into which a metal component is introduced and assembled from an opening in the part. A halide is formed by reaction between a halogen and a metal donor containing aluminum, then the halide is transported by a carrier gas in order to come into contact with the metal part, wherein the metal component has first, before the implementation of the process, been surface-enriched with aluminum in order to serve as an aluminum donor.

Abstract: An aluminization process by vapor phase deposition for high-temperature oxidation protection of a metal turbomachine part. The part including a cavity into which a metal component is introduced and assembled from an opening in the part. A halide is formed by reaction between a halogen and a metal donor containing aluminum, then the halide is transported by a carrier gas in order to come into contact with the metal part, wherein the metal component has first, before the implementation of the process, been surface-enriched with aluminum in order to serve as an aluminum donor.

Abstract: A method of aluminization by deposit in the vapor phase for protection against oxidation at high temperature of a metal part of a turbomachine. The part includes a cavity with an opening that can be accessed from the outside. A halide is formed by reaction between a halogen and a metal donor containing aluminum, then the halide is transported by a carrier gas to come into contact with the metal part, the metal donor being placed at least partly in the cavity. The metal donor is in the form of a pellet obtained by hot sintering under pressure of a mixture of metal powder.

Abstract: A method of aluminization by deposit in the vapor phase for protection against oxidation at high temperature of a metal part of a turbomachine. The part includes a cavity with an opening that can be accessed from the outside. A halide is formed by reaction between a halogen and a metal donor containing aluminum, then the halide is transported by a carrier gas to come into contact with the metal part, the metal donor being placed at least partly in the cavity. The metal donor is in the form of a pellet obtained by hot sintering under pressure of a mixture of metal powder.

Abstract: An aluminization process by vapor phase deposition for high-temperature oxidation protection of a metal turbomachine part. The part including a cavity into which a metal component is introduced and assembled from an opening in the part. A halide is formed by reaction between a halogen and a metal donor containing aluminum, then the halide is transported by a carrier gas in order to come into contact with the metal part, wherein the metal component has first, before the implementation of the process, been surface-enriched with aluminum in order to serve as an aluminum donor.