Abstract: A method for fabricating a part by melting powder with the help of a high energy beam uses a device that includes a building support for receiving at least one powder layer; a high energy beam generator suitable for raising particles of the powder to a temperature higher than their melting temperature TF, and for forming a liquid pool including at least the particles of the melted powder, and an auxiliary heater device that is suitable for heating the material situated in a zone adjacent to the pool to a temperature that is lower than the melting temperature TF, the zone including at least one region selected from an upstream region situated upstream from the pool and a downstream region situated downstream from the pool.

Abstract: The invention relates to a method of producing a guide vane, the method comprising a step of fabricating at least a portion of a metal body of the guide vane by additive fabrication, with at least one outside surface thereof presenting a plurality of cavities; and a step of filling said cavities with a material of lower density than the metal body in order to form at least one substantially smooth airfoil surface.

Abstract: A method for creating a metal reinforcement for a leading or trailing edge of a turbine engine blade including a reinforcement foot and head, the method including: creating a plurality of V-shaped tapered elements that form different parts of the metal reinforcement so that the metal reinforcement is divided into a plurality of parts distributed between the foot and the head; positioning the parts on equipment that is shaped like the leading or trailing edge of the turbine engine blade; and rigidly connecting the different parts so as to form the complete profile of the one-piece metal reinforcement the by recombining the different parts.

Abstract: The invention relates to a method of producing a guide vane, the method comprising a step of fabricating at least a portion of a metal body of the guide vane by additive fabrication, with at least one outside surface thereof presenting a plurality of cavities; and a step of filling said cavities with a material of lower density than the metal body in order to form at least one substantially smooth airfoil surface.

Abstract: An assembly between a metal piece and a ceramic material piece made of SiC and/or C based ceramic material. The assembly includes a stack structure including the following elements assembled together in pairs in this order, by brazing: the metal piece; a first intermediate piece; a second intermediate piece; and the ceramic material piece. The second intermediate piece is made of another ceramic material, that is chemically less reactive relative to metals than are SiC or C, and that presents a coefficient of expansion smaller than that of the material constituting the metal piece. The first intermediate piece is made of metal and can deform to compensate for expansion difference between the metal piece and the second intermediate piece. The assembly can be used in a turbomachine.

Abstract: An assembly including a stack structure made up of the following elements assembled together by brazing: the titanium-based metal piece; a first intermediate piece suitable for deforming to accommodate differential expansion between the metal piece and a piece made of ceramic material based on silicon carbide and/or carbon; a second intermediate piece that is rigid, having a coefficient of expansion close to that of said ceramic material piece and made of aluminum nitride (AlN) or of tungsten (W); and the ceramic material piece is disclosed.

Abstract: An assembly including a metal piece, a piece made of ceramic material, and at least one intermediate connection element assembled to each of the pieces by brazing. The intermediate connection element includes a deformable sheet presenting at least two flat zones brazed to respective ones of the pieces, the two flat zones being interconnected by a deformable zone presenting at least two free undulations oriented in alternation towards the metal piece and towards the piece made of ceramic material.

Abstract: A process for manufacturing a component with an insert made of a composite is disclosed. The composite includes a metal matrix, within which ceramic fibers extend. The insert is made of a composite which is obtained from a plurality of coated filaments, each filament includes a ceramic fiber coated with a metal sheath. The process includes winding a bundle or bonded sheet of coated filaments around a body of revolution perpendicular to the axis of rotation of said body. The insert is then subjected to a hot isostatic pressing step in a container. The process is applied to the manufacture of aeronautical turbomachine components.

Abstract: The invention relates to a method for metallic coating of fibers by liquid technique, in which a fiber, coated with a material forming a diffusion barrier with the metal, is drawn through a liquid metal bath to be coated therewith. The method is characterized in that prior to the passage of the fiber into the bath, the fiber is coated with a compound wettable by the metal. The coating of the fiber by the metal is facilitated by the presence of the compound, forming an interface wettable by the metal.

Abstract: The assembly comprises a stack structure made up of the following elements assembled together in pairs by brazing: the titanium-based metal piece (10); a first intermediate piece (11) suitable for deforming to accommodate differential expansion between the metal piece (10) and a piece (20) made of ceramic material based on silicon carbide and/or carbon; a second intermediate piece (12) that is rigid, having a coefficient of expansion close to that of said ceramic material piece (20) and made of aluminum nitride (AlN) or of tungsten (W); and the ceramic material piece (20).

Abstract: An assembly including a metal piece, a piece made of ceramic material, and at least one intermediate connection element assembled to each of the pieces by brazing. The intermediate connection element includes a deformable sheet presenting at least two flat zones brazed to respective ones of the pieces, the two flat zones being interconnected by a deformable zone presenting at least two free undulations oriented in alternation towards the metal piece and towards the piece made of ceramic material.

Abstract: An assembly between a metal piece and a ceramic material piece made of SiC and/or C based ceramic material. The assembly includes a stack structure including the following elements assembled together in pairs in this order, by brazing: the metal piece; a first intermediate piece; a second intermediate piece; and the ceramic material piece. The second intermediate piece is made of another ceramic material, that is chemically less reactive relative to metals than are SiC or C, and that presents a coefficient of expansion smaller than that of the material constituting the metal piece. The first intermediate piece is made of metal and can deform to compensate for expansion difference between the metal piece and the second intermediate piece. The assembly can be used in a turbomachine.

Abstract: A turbomachine rotor including at least one disk having a ring constituted, for example, by a winding of metal-coated silicon carbide or alumina yarn. According to the invention, the composite ring is received in a closed annular cavity, e.g. defining by machining a groove in an enlarged portion of the disk and closing the groove by means of an annular plate after the ring has been put into place.

Abstract: The invention relates to a method for metallic coating of fibres by liquid technique, in which a fibre, coated with a material forming a diffusion barrier with the metal, is drawn through a liquid metal bath to be coated therewith. The method is characterized in that prior to the passage of the fibre into the bath, the fibre is coated with a compound wettable by the metal. The coating of the fibre by the metal is facilitated by the presence of the compound, forming an interface wettable by the metal.

Abstract: A turbomachine rotor including at least one disk having a ring constituted, for example, by a winding of metal-coated silicon carbide or alumina yarn. According to the invention, the composite ring is received in a closed annular cavity, e.g. defining by machining a groove in an enlarged portion of the disk and closing the groove by means of an annular plate after the ring has been put into place.

Abstract: Process for manufacturing a component with an insert made of a composite comprising a metal matrix, within which ceramic fibers extend, the insert made of a composite being obtained from a plurality of coated filaments, each comprising a ceramic fiber coated with a metal sheath, characterized in that it comprises the manufacture of an insert with a step of winding a bundle or bonded sheet of coated filaments around a body of revolution perpendicular to the axis of rotation of said body. The insert is then subjected to a hot isostatic pressing step in a container. The process is applied to the manufacture of aeronautical turbomachine components.