Safran Aircraft Engines

Snecma

Centre National De La Recherche Scientifique

Université Paul Sabatier (toulouse Iii)

Aircelle Limited

Université De Nantes

Mbda France

Universite Paris Sud (ups)

Université Paris—sud

Jean-Baptiste Mottin

Guillaume Fribourg

Claude Estournes

Marc Jacky Vassault

Romain Epherre

Geoffroy Chevallier

Philippe Charles Alain Le Biez

Serge Georges Vladimir Selezneff

Christophe Colin

Jean-Francois Fromentin

Thierry Jean Emile Flesch

Beryl Cassandre Anne Mereaux

Thierry Baudin

Olivier Chantoiseau

Pascal Paillard

Jean-François Castagne

Sophie Martine Jobez

Laëtitia Kirschner

Thierry Flesch

Gérard Saussereau

Vanessa Mengeling

Bruno Le Razer

Jean-Paul Benard

Yves Le Meur

Alexandre Yann Michel Benoit

Yannick Marcel Beynet

Beryl Cassandre Mereaux

Gerard Saussereau

Laetitia Kirschner

Alexandre Yann Benoit

Jean-Francois Castagne

Thierry Jean Flesch

A device for fabricating a three-dimensional part by selectively melting a powder bed, the device including a first tank for containing a first powder and provided with a first powder dispenser valve, a second tank for containing a second different powder and provided with a second powder dispenser valve, a first and a second monitoring device for monitoring the quantity of first powder delivered by the first valve and the quantity of second powder delivered by the second valve, a mixer chamber in communication with the first and second valves and including a third powder dispenser valve, and a mixer for mixing the powder particles in the chamber, a support for receiving the powder delivered by the third valve and on which the parts is to be fabricated, a powder spreader for spreading powder on the support, and a heater member for locally melting the powder spread on the support.

Device and a method for fabricating a three-dimensional part by selectively melting a powder bed

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.

Method for the additive manufacturing of a part by selective melting or selective sintering of optimized-compactness powder beds using a high energy beam

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.

Method for hard-surfacing metal parts for aircraft turbofans, and local protection tool for implementing the method

A method of fabricating an abradable coating of varying density, and such an abradable coating of varying density. According to the invention, the method comprises the following steps: providing a substrate () having a first portion with its surface situated at a first level (A), and a second portion with its surface situated at a second level (B) different from the first level; depositing a precursor material on the first and second portions of the substrate (); compressing the precursor material between the substrate and a bearing surface; and sintering the precursor material as compressed in this way in order to obtain an abradable coating () having a first portion () on the first portion of the substrate, and possessing a first density, and a second portion () on the second portion of the substrate, and possessing a second density distinct from the first.

Abradable coating having variable densities

The invention relates to a method for manufacturing a turbine shroud () for a turbomachine, the method comprising manufacturing at least one turbine shroud sector (), positioning the turbine shroud sector () in a bottom mold so that an outer surface of the turbine shroud sector is in contact at least in part with the bottom mold, and depositing a powder layer on an inner surface () of the turbine shroud sector (). Thereafter, a top mold is positioned on the powder layer and an abradable layer () is made by subjecting the powder layer to a method of SPS sintering, the abradable layer () being for being disposed facing a turbine wheel.

Method for manufacturing a turbine shroud for a turbomachine

According to the invention, a blade is friction-welded to a rotor disk of a turbomachine, the disk comprising a projecting block having an outer surface to which the blade is to be welded. To this end: a surfacing process is carried out on at least a part of the periphery of the block, in the region of said outer surface; the outer surface of the block and the surfacing are machined in order to level same; and friction-welding is then carried out between the surfaced outer surface of the block and the blade.

Method for friction-welding a blade to a turbomachine vane, including a surfacing process

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.

Process for complete cladding of metal parts of aircraft turbojets, and complete protection tool for implementing the process

A method of friction welding an airfoil () onto a rotor disk of a turbine engine, the disk having at its outer periphery a projecting stub () onto which the airfoil is to be welded, the method comprising a step consisting in mounting chocks () 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 () between the chocks and the stub are expelled, at least in part, in seams of material () 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.

Method for friction welding a blade onto a turbine engine rotor disc; corresponding integral blade disc

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.

Method for welding and for hard surface deposition of metal parts made of aluminium by a MIG method with pulsed current and filler wire

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.

Method and device for drilling a workpiece with laser pulses

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.

Protection cover for a spray nozzle during a hardfacing process

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.

Sintering and laser fusion device, comprising a means for heating powder by induction

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.

Method for manufacturing an assembly including a plurality of blades mounted in a platform

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.

Growing community of inventors

Poitiers, France

Jean-Baptiste Mottin