Abstract: A method for hard surface deposition on aluminum metal parts of a turbine engine using MIG welding equipment which includes a pulsed current generator and pulsed filler metal wire feed, wherein the deposition is achieved using a filler metal wire whose composition is of the same nature as the composition of the aluminum alloy of the part to undergo hard surface deposition, with the pulsed metal wire feed and speed of deposition on the metal part of the turbine engine being adapted to carry out deposition without hot fissuring.

Abstract: A method of drilling a part, or a turbine engine part, by a pulse laser generator including a cavity in which there is mounted a solid bar for generating laser pulses, the method including determining values of a plurality of operating parameters of the laser generator for forming orifices of predetermined diameter in the part, and taking account, among the parameters, of a setpoint value for the temperature of the laser cavity, which value is determined as a function of characteristics of the orifices to be drilled.

Abstract: A protection cover suitable for being placed between a spray nozzle and a metal part during a process of resurfacing the metal part, the protection cover including a side wall extending along a reference axis, the side wall including an inner surface and an outer surface, the side wall having a lower end and an upper end, the side wall being perforated by at least one lateral gas inlet port, the lower end of the side wall being perforated by a notch into which a portion of the metal part can be inserted, the upper end of the side wall being provided with an opening into which a portion of the spray nozzle can be inserted. The inner surface of the side wall includes at least one frustoconical portion.

Abstract: A device for producing or building up a metal part by sintering and laser fusion, the device including a laser beam generator, a mechanism for deflecting the beam to scan a surface of the part to be produced, a sintering pan including a metal powder used to cover the surface of the part and to be melted by the laser beam to thicken the part, and at least one mechanism for heating powder contained in an area of the sintering pan by induction.

Abstract: A protection cover suitable for being placed between a spray nozzle and a metal part during a process of resurfacing the metal part, the protection cover including a side wall extending along a reference axis, the side wall including an inner surface and an outer surface, the side wall having a lower end and an upper end, the side wall being perforated by at least one lateral gas inlet port, the lower end of the side wall being perforated by a notch into which a portion of the metal part can be inserted, the upper end of the side wall being provided with an opening into which a portion of the spray nozzle can be inserted. The inner surface of the side wall includes at least one frustoconical portion.

Abstract: A method for fabricating a part by selective melting or sintering of powder beds by high energy beam, the method including a) providing a material in the form of powder particles; b) depositing a first powder layer on a support; c) scanning a region of the first layer with the beam to heat the powder locally to a temperature higher than the powder sintering temperature, such that the powder particles as melted or sintered form a first single-piece element; d) depositing a second powder layer on the first powder layer; e) scanning a region of the second layer with the beam to heat the powder to a temperature higher than the powder sintering temperature, so that the particles of powder as sintered or melted form a second single-piece element; and f) repeating d) and e) for each new powder layer laid over a preceding layer until the part is formed.

Abstract: A method of friction welding an airfoil (32) onto a rotor disk of a turbine engine, the disk having at its outer periphery a projecting stub (18) onto which the airfoil is to be welded, the method comprising a step consisting in mounting chocks (24) on leading and trailing edges of the stub, the method being characterized in that, before friction welding, the chocks are secured to the stub by welding, and in that during the friction welding operation, the beads of welding (28) between the chocks and the stub are expelled, at least in part, in seams of material (34) that form around the connection zone between the airfoil and the stub and that are subsequently to be removed or eliminated, e.g. by machining.

Abstract: A method of manufacturing an assembly, including a plurality of blades mounted in a platform preparing a mixture of metal powder and thermoplastic binder, includes manufacturing the blades separately from the platform, and finishing the blades after the manufacturing. The method also includes injecting the mixture into a mold to obtain a platform blank, removing the binder from the platform blank prior to assembling the finished blades with the blank, inserting one end of the finished blades into a housing formed in the platform blank in order to assemble the assembly, and sintering the assembly comprising the platform blank and the finished blades to unify the assembly.

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 of drilling a part, or a turbine engine part, by a pulse laser generator including a cavity in which there is mounted a solid bar for generating laser pulses, the method including determining values of a plurality of operating parameters of the laser generator for forming orifices of predetermined diameter in the part, and taking account, among the parameters, of a setpoint value for the temperature of the laser cavity, which value is determined as a function of characteristics of the orifices to be drilled.

Abstract: A process for cladding a metal part of an aircraft turbojet, including a plurality of metal portions, using a nozzle for emitting a laser beam, the process including positioning the metal part to be cladded on a turntable; positioning a cover on the turntable; positioning the nozzle in an aperture present in the cover; introducing an inert gas under the cover; and cladding a first portion of the metal part by carrying out operations of: spraying metal powders; emitting the laser beam; and moving the nozzle relative to the first metal portion.

Abstract: A method for hard-surfacing metal parts for an aircraft turbofan, the method involving the use of a nozzle outputting a laser beam or an electron beam, which is to heat a sprayed powder for hard-surfacing the metal part, the method including positioning the metal part to be hard-surfaced in an enclosure, the top portion of which has an opening; positioning a mobile cover covering the opening of the top portion, the mobile cover having an opening; positioning the nozzle at the opening of the mobile cover; feeding an inert gas into the enclosure; spraying metal powders and emitting the laser or electron beam for hard-surfacing the metal part; moving the nozzle relative to the enclosure along a path for hard-surfacing the metal part, the movement of the nozzle causing the movement of the mobile cover on the top surface of the enclosure.

Abstract: A method for hard surface deposition on aluminium metal parts of a turbine engine using MIG welding equipment which includes a pulsed current generator and pulsed filler metal wire feed, wherein the deposition is achieved using a filler metal wire whose composition is of the same nature as the composition of the aluminium alloy of the part to undergo hard surface deposition, with the pulsed metal wire feed and speed of deposition on the metal part of the turbine engine being adapted to carry out deposition without hot fissuring.

Abstract: A method of fabricating a metal part by selectively melting a powder, the method including: building up layer by layer on a plate and simultaneously with the part, at least one holder and support element for the part, the element being spaced apart and distinct from the part and being separated therefrom by a gap filled with non-melted powder; after the part has been made completely, removing at least some of the powder remaining in the gap between the part and the element, for example by suction, blowing, or vibration; and separating the part from the plate.

Abstract: A method for manufacturing at least a portion of a metal part of a turbine engine having a width. The portion of the metal part is manufactured by metal disposition using a MIG welding apparatus including a pulsed current generator and a pulsed deposition-wire flow, and used for varying the current and flow, the manufacture being carried out in the form of metal beads in several consecutive layers.

Abstract: A device for producing or building up a metal part by sintering and laser fusion, the device including a laser beam generator, a mechanism for deflecting the beam to scan a surface of the part to be produced, a sintering pan including a metal powder used to cover the surface of the part and to be melted by the laser beam to thicken the part, and at least one mechanism for heating powder contained in an area of the sintering pan by induction.

Abstract: A method of fabricating a metal part by selectively melting a powder, the method including: building up layer by layer on a plate and simultaneously with the part, at least one holder and support element for the part, the element being spaced apart and distinct from the part and being separated therefrom by a gap filled with non-melted powder; after the part has been made completely, removing at least some of the powder remaining in the gap between the part and the element, for example by suction, blowing, or vibration; and separating the part from the plate.

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: The present invention relates to a method of brazing two materials (1, 2) together using a filler metal (3), which comprises the following steps: the filler metal is placed between the two contacting materials in a brazing zone where they are intended to be joined; on at least one of the two materials, which is mounted so as to move, a stress force is exerted along each of the directions of expansion provided for the two materials; the assembly in the brazing zone is brought to what is called a brazing temperature, which is both above the melting point of the filler metal and below the melting point of each of the two materials; during the temperature rise, the forces exerted on the materials to be assembled are gradually reduced as said materials expand, so that there is substantially no longer a force exerted on the materials when the brazing temperature is reached; and, once the filler metal has melted and wetted each material to be assembled, the assembly is cooled so as to solidify the filler metal, whic

Abstract: A method of manufacturing an assembly, including a plurality of blades mounted in a platform preparing a mixture of metal powder and thermoplastic binder, includes manufacturing the blades separately from the platform, and finishing the blades after the manufacturing. The method also includes injecting the mixture into a mold to obtain a platform blank, removing the binder from the platform blank prior to assembling the finished blades with the blank, inserting one end of the finished blades into a housing formed in the platform blank in order to assemble the assembly, and sintering the assembly comprising the platform blank and the finished blades to unify the assembly.