Abstract: The invention relates to a method for manufacturing a composite platform (30) for a fan of an aircraft turbine engine, wherein said platform comprises an elongate wall (32) and is configured to extend between two fan blades (3), said wall comprising an outer aerodynamic surface (32a) and an inner surface (32b), on which a fastening tab is located (34), said fastening tab being configured to be fixed to a fan disc (2). The invention is characterized in that it comprises the steps of: a) preparing fabrics or sheets which are pre-impregnated with a resin, b) depositing the fabrics or sheets in a mold, c) positioning a metal reinforcement (36) in the mold on the fabrics or sheets, the reinforcement being integrally formed with said fastening tab, d) depositing the fabrics or sheets on a part of the reinforcement, and e) closing and heating the mold for solidification of the assembly formed by the fabrics or sheets and the reinforcement.

Abstract: The invention relates to a method for manufacturing a composite platform (30) for a fan of an aircraft turbine engine, wherein said platform comprises an elongate wall (32) and is configured to extend between two fan blades (3), said wall comprising an outer aerodynamic surface (32a) and an inner surface (32b), on which a fastening tab is located (34), said fastening tab being configured to be fixed to a fan disc (2). The invention is characterized in that it comprises the steps of: a) preparing fabrics or sheets which are pre-impregnated with a resin, b) depositing the fabrics or sheets in a mold, c) positioning a metal reinforcement (36) in the mold on the fabrics or sheets, the reinforcement being integrally formed with said fastening tab, d) depositing the fabrics or sheets on a part of the reinforcement, and e) closing and heating the mold for solidification of the assembly formed by the fabrics or sheets and the reinforcement.

Abstract: A process for manufacturing a cylindrical composite component comprises includes producing a fibrous texture in the form of a strip by three-dimensional or multi-layer weaving, winding the fibrous texture on several superimposed lathes on a mandrel with a profile corresponding to that of the component to be manufactured so as to form a fibrous preform, densifying the fibrous preform by a matrix. When the fibrous texture is wound on the mandrel, a web including a fugitive material filled with carbon nanotubes is interposed between the adjacent turns of the fibrous texture.

Abstract: A composite platform for a fan of an aircraft turbine engine. The platform includes an elongate wall and is configured to extend between two fan blades. The wall includes an aerodynamic outer surface and an inner surface, on which a fastening tab is located, wherein the fastening tab is configured to be attached to a fan disc. The fastening tab is integrally formed with a metal reinforcement which has a plate having an elongate shape and which extends over more than 50% of the longitudinal extent of the wall, the wall being produced by overmolding a resin on the plate so as to be integrated into the wall.

Abstract: A vane for a turbine engine includes a body in the form of an aerodynamic profile formed by a shell produced from a composite material formed from a three-dimensional textile of reinforcement fibres consolidated by a hardened resin. The shell forms a pressure surface and a suction surface of the vane connected to each other while forming on one side a leading edge and on the opposite side a trailing edge of the vane, and a core including a core body surrounded by the shell. The core is produced from non-porous plastics material, and the core body is in the form of an aerodynamic profile and delimits at least one closed cavity of the core.

Abstract: A manufacturing method for a component made from composite material, in particular of a turbomachine, includes the steps of producing a preform with a fibrous reinforcement comprising a first fibrous portion and a second fibrous portion, and injecting a pressurized matrix into an injection chamber of an injection mold, in which the preform is arranged. The method further includes the steps of polymerizing the preform and positioning a flexible pocket that encloses a fluid and that is arranged between the first fibrous portion and the second fibrous portion before the injection step. The fluid is configured to apply an additional pressure to the preform of the fluid during the polymerization step.

Abstract: A composite platform for a fan of an aircraft turbine engine. The platform includes an elongate wall and is configured to extend between two fan blades. The wall includes an aerodynamic outer surface and an inner surface, on which a fastening tab is located, wherein the fastening tab is configured to be attached to a fan disc. The fastening tab is integrally formed with a metal reinforcement which has a plate having an elongate shape and which extends over more than 50% of the longitudinal extent of the wall, the wall being produced by overmolding a resin on the plate so as to be integrated into the wall.

Abstract: A vane for a turbine engine includes a body in the form of an aerodynamic profile formed by a shell produced from a composite material formed from a three-dimensional textile of reinforcement fibres consolidated by a hardened resin. The shell forms a pressure surface and a suction surface of the vane connected to each other while forming on one side a leading edge and on the opposite side a trailing edge of the vane, and a core including a core body surrounded by the shell. The core is produced from non-porous plastics material, and the core body is in the form of an aerodynamic profile and delimits at least one closed cavity of the core.

Abstract: A fibrous texture in the form of a web includes a first portion extending in a longitudinal direction between a proximal part and an intermediate part. One or more layers of warp threads or strands present on the side of an inner face of the fibrous texture include threads or strands of glass fibers, the threads or strands of the other layers of warp threads or strands including threads or strands of carbon fibers. The fibrous texture further includes a second portion extending in the longitudinal direction between the intermediate part and a distal part of the fibrous texture. One or more of the plurality of layers of warp threads or strands present on the side of an outer face of the fibrous texture include threads or strands of glass fibers. The warp threads or strands are continuous over the entire length of the fibrous texture.

Abstract: A process for manufacturing a cylindrical composite component comprises includes producing a fibrous texture in the form of a strip by three-dimensional or multi-layer weaving, winding the fibrous texture on several superimposed lathes on a mandrel with a profile corresponding to that of the component to be manufactured so as to form a fibrous preform, densifying the fibrous preform by a matrix. When the fibrous texture is wound on the mandrel, a web including a fugitive material filled with carbon nanotubes is interposed between the adjacent turns of the fibrous texture.

Abstract: A fibrous structure having the form of a band extending in a longitudinal direction (X) over a given length between a proximal part and a distal part and in a lateral direction (Y) over a given width between a first side edge and a second side edge, the fibrous structure having a three-dimensional or multilayer weave between a plurality of layers of warp yarns or strands extending longitudinally and a plurality of layers of weft yarns or strands extending laterally, wherein a first portion of the fibrous structure present between the proximal part and an intermediate part of the fibrous structure includes carbon fiber weft yarns or strands and wherein a second portion of the fibrous structure present between the intermediate part and the distal part includes glass fiber weft yarns or strands.

Abstract: A strip-shaped fibrous texture has a three-dimensional or multi-layered weaving between a plurality of layers of warp yarns or strands and a plurality of layers of weft yarns or strands extending in the lateral direction. The fibrous texture includes a first section extending along the longitudinal direction from a proximal portion of the texture and in which one or more layers of the plurality of layers of weft yarns or strands consist of a plurality of groups of yarns or strands each including at least one carbon fiber yarn or strand and one glass fiber yarn or strand. The carbon fiber yarn or strand and the glass fiber yarn or strand of each group of yarns being woven together according to the same weaving pattern or weave. The fibrous texture further includes a second section present between the first section and a distal portion of the fibrous texture.

Abstract: A fibrous texture in the form of a web includes a first portion extending in a longitudinal direction between a proximal part and an intermediate part. One or more layers of warp threads or strands present on the side of an inner face of the fibrous texture include threads or strands of glass fibers, the threads or strands of the other layers of warp threads or strands including threads or strands of carbon fibers. The fibrous texture further includes a second portion extending in the longitudinal direction between the intermediate part and a distal part of the fibrous texture. One or more of the plurality of layers of warp threads or strands present on the side of an outer face of the fibrous texture include threads or strands of glass fibers. The warp threads or strands are continuous over the entire length of the fibrous texture.

Abstract: A fibrous structure having the form of a band extending in a longitudinal direction (X) over a given length between a proximal part and a distal part and in a lateral direction (Y) over a given width between a first side edge and a second side edge, the fibrous structure having a three-dimensional or multilayer weave between a plurality of layers of warp yarns or strands extending longitudinally and a plurality of layers of weft yarns or strands extending laterally, wherein a first portion of the fibrous structure present between the proximal part and an intermediate part of the fibrous structure includes carbon fiber weft yarns or strands and wherein a second portion of the fibrous structure present between the intermediate part and the distal part includes glass fiber weft yarns or strands.

Abstract: An annular cover for a lubrication chamber of a rotary bearing of a turbomachine. The cover includes a wall that is generally circular and flared with an orifice that is designed to receive a transmission shaft opposite an assembly surface for the cover, and at least one duct communicating with the inside of the wall and extending along the wall as far as the assembly surface. The duct is formed in the thickness of the body of the wall which is made from the same material, and which includes a composite material with a thermoplastic matrix and carbon fibers.

Abstract: The present invention relates to a method for making a preform for a composite with a thermoplastic matrix, said preform comprising one or several layers of reinforcement fibers sewn on a support by means of at least one attachment yarn and according to the TFP process, characterized in that the method comprises one or several steps for depositing a thermoplastic-resin layer on the support or on a layer of reinforcement fibers.

Abstract: A composite material turbomachine vane comprising a blade is provided, wherein the vane comprises a first resin reinforced with long fibers and a second resin reinforced with short fibers, the first and second resins being chemically compatible or identical, the long fibers serving to stiffen the vane and the short fibers dispersed in the second resin serving to fill in the parts of the vane that are not reinforced by the long fibers and giving the vane its substantially final shape.

Abstract: The present application relates to an annular cover for a lubrication chamber of a rotary bearing of a turbomachine. The cover includes a wall that is generally circular and flared with an orifice that is designed to receive a transmission shaft opposite an assembly surface for the cover, and at least one duct communicating with the inside of the wall and extending along the wall as far as the assembly surface. The duct is formed in the thickness of the body of the wall which is made from the same material, and which includes a composite material with a thermoplastic matrix and carbon fibres. The present application also relates to a turbomachine including a compressor linked to a turbine via a transmission shaft, an intermediate fan casing, and a bearing joining the transmission shaft to the intermediate casing. The casing is placed in a lubrication chamber delimited by an annular chamber cover, a chamber casing carrying the bearing and the cover.

Abstract: The present invention relates to a turbomachine rectifier comprising a plurality of stator vanes (5) connecting an inner collar (4) to an outer collar (3), each of said vanes (5) comprising a blade (11) and a blade-head platform (10), comprising an intermediate piece (6) arranged between the inner collar (4) and the outer collar (3) and fastened to the outer collar (3), said intermediate piece (6) comprising openings (14) for the passage of the vane blades (11) and said vane platforms (10) resting, on one side, on the outer collar (3) and, on the other side, on the intermediate piece (6).

Abstract: The present application relates to a compressor stator of an axial turbomachine having an inner shell formed of a plurality of annular segments arranged end to end, a layer of abradable material applied on the inner face of the shell, and an annular array of blades connected to the shell. The stator has at least one strip located in the layer of abradable material and extending from either side of the junctions between two adjacent annular segments. The inner tips of the blades have hooks mating mechanically with the strip.