Patents by Inventor Jean-Michel Patrick Maurice Franchet
Jean-Michel Patrick Maurice Franchet has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11702371Abstract: The invention concerns a method for coating a core (1) for producing a turbomachine part (2) by isostatic compacting, for example a leading-edge shield of a blade, the coating method comprising the steps of:—S1: covering the core (1) by means of a first solution comprising a first refractory component configured to oppose the diffusion of species, the first component comprising a metal oxide,—S2: covering the core (1) by means of a second solution comprising a second component designed to bind the first component in such a way as to form a homogeneous layer, the second component comprising a mineral binder;—S3: applying a heat treatment to the covered core (1) in such a way as to dry the solution and solidify the coating.Type: GrantFiled: December 20, 2019Date of Patent: July 18, 2023Assignee: SAFRANInventors: Jean-Michel Patrick Maurice Franchet, Gilles Charles Casimir Klein
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Publication number: 20230011910Abstract: A Nickel-based superalloy, whose composition includes, in percent by weight of the total composition: Chromium: 10.0-11.25; Cobalt: 11.2-13.7; Molybdenum: 3.1-3.8; Tungsten: 3.1-3.8; Aluminium: 2.9-3.5; Titanium: 4.6-5.6; Niobium: 1.9-2.3; Hafnium: 0.25-0.35; Zirconium: 0.040-0.060; Carbon: 0.010-0.030; Boron: 0.01-0.030; Nickel: remainder as well as unavoidable impurities; the composition being free of tantalum.Type: ApplicationFiled: December 9, 2020Publication date: January 12, 2023Inventors: Anne-Laure ROUFFIE, Jean-Michel Patrick Maurice FRANCHET, Didier LOCQ
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Publication number: 20230001480Abstract: A method for manufacturing a metal bladed wheel of a turbomachine reinforced by an insert made of metal matrix composite material, includes winding the ceramic fibers around a mandrel in order to form the insert, the ceramic fibers being surrounded by a material constituting the matrix; and spark plasma sintering the insert with a powder of metal constituting the bladed wheel to be manufactured.Type: ApplicationFiled: December 10, 2020Publication date: January 5, 2023Inventors: Pierre Jean SALLOT, Jean-Michel Patrick Maurice FRANCHET
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Publication number: 20220064073Abstract: The invention concerns a method for coating a core (1) for producing a turbomachine part (2) by isostatic compacting, for example a leading-edge shield of a blade, the coating method comprising the steps of:—S1: covering the core (1) by means of a first solution comprising a first refractory component configured to oppose the diffusion of species, the first component comprising a metal oxide,—S2: covering the core (1) by means of a second solution comprising a second component designed to bind the first component in such a way as to form a homogeneous layer, the second component comprising a mineral binder;—S3: applying a heat treatment to the covered core (1) in such a way as to dry the solution and solidify the coating.Type: ApplicationFiled: December 20, 2019Publication date: March 3, 2022Applicant: SAFRANInventors: Jean-Michel Patrick Maurice FRANCHET, Gilles Charles Casimir KLEIN
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Publication number: 20220064776Abstract: The invention relates to a method for manufacturing a core (1) for producing a leading edge of a fan blade. The method comprises the steps of: (a) providing an initial core (11) made of a nickel-base alloy, (b) thermal spraying of a layer (12) of a cobalt-base alloy, comprising chromium and at least one element of tungsten and/or molybdenum, on the initial core.Type: ApplicationFiled: December 20, 2019Publication date: March 3, 2022Applicant: SAFRANInventors: Denis FLECHE, Jean-Michel Patrick Maurice FRANCHET
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Patent number: 10837069Abstract: A device for generating a microstructure with a structure gradient in an axisymmetric mechanical part having a hollow center and initially possessing a uniform structure with fine grains, the device including a first heater system defining a first shell for receiving the mechanical part and suitable for heating the outer periphery of the mechanical part to a first temperature higher than the solvus temperature. The device further includes a second heater system defining a second shell arranged inside the first shell and suitable for heating the inner periphery of the mechanical part to a second temperature lower than the solvus temperature, with the space between the first shell and the second shell defining a housing suitable for receiving the axisymmetric mechanical part having a hollow center.Type: GrantFiled: November 4, 2016Date of Patent: November 17, 2020Assignee: SAFRANInventors: Jean-Michel Patrick Maurice Franchet, Gilles Charles Casimir Klein
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Patent number: 10576578Abstract: A field of rotary blades, and more particularly to a method of fabricating a leading edge shield for protecting such a blade. The method includes at least steps of performing initial plastic deformation on at least one sheet from a pressure side sheet and a suction side sheet, using additive fabrication to add a reinforcement with a fiber insert on at least one of the pressure and suction side sheets, closing the pressure and suction side sheets around a core after the initial plastic deformation and after adding the reinforcement, performing subsequent plastic deformation by pressing the pressure and suction side sheets against an outside surface of the core after the sheets have been closed around the core, and extracting the core.Type: GrantFiled: September 18, 2015Date of Patent: March 3, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Dominique Michel Serge Magnaudeix
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Publication number: 20190143396Abstract: A metal core for hot-shaping a metal part made out of titanium-based alloy. The metal core presents on an outside surface that is to come into contact with the metal part, a layer of material enriched in metallic carbonitride. The metal core includes an alloy based on nickel or on cobalt, and the nickel- or cobalt-based alloy includes chromium, molybdenum, and/or titanium. A method of fabricating and regenerating the metal core, and also a method of fabricating a metal part using the metal core, are disclosed.Type: ApplicationFiled: April 10, 2017Publication date: May 16, 2019Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN, Centre National De La Recherche ScientifiqueInventors: Gilles Charles Casimir KLEIN, Jean-Michel Patrick Maurice FRANCHET, Yann LEPETITCORPS, Jerome ROGER, Benoit SERGENT
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Publication number: 20180371563Abstract: A device for generating a microstructure with a structure gradient in an axisymmetric mechanical part having a hollow center and initially possessing a uniform structure with fine grains, the device including a first heater system defining a first shell for receiving the mechanical part and suitable for heating the outer periphery of the mechanical part to a first temperature higher than the solvus temperature. The device further includes a second heater system defining a second shell arranged inside the first shell and suitable for heating the inner periphery of the mechanical part to a second temperature lower than the solvus temperature, with the space between the first shell and the second shell defining a housing suitable for receiving the axisymmetric mechanical part having a hollow center.Type: ApplicationFiled: November 4, 2016Publication date: December 27, 2018Applicant: SAFRANInventors: Jean-Michel Patrick Maurice FRANCHET, Gilles Charles Casimir KLEIN
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Patent number: 10119180Abstract: A titanium-based intermetallic alloy includes, in atomic percent, 16% to 26% Al, 18% to 28% Nb, 0% to 3% of a metal M selected from Mo, W, Hf, and V, 0.1% to 2% of Si, 0% to 2% of Ta, 1% to 4% of Zr, with the condition Fe+Ni?400 ppm, the balance being Ti, the alloy also presenting an Al/Nb ratio in atomic percent lying in the range 1.05 to 1.15.Type: GrantFiled: December 14, 2015Date of Patent: November 6, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jean-Yves Guedou, Jean-Michel Patrick Maurice Franchet, Jean-Loup Bernard Victor Strudel, Laurent Germann, Dipankar Banerjee, Vikas Kumar, Tapash Nandy
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Patent number: 9963971Abstract: A method for producing a metal reinforcement for protecting a leading edge of a compressor blade of composite, including: creating a core that has a shape of an internal cavity of the reinforcement; creating an insert made of an alloy of a hardness greater than that of the reinforcement; shaping sheet metal by stamping with the creation, upstream of the core, a cavity between the metal sheets, which cavity is configured to accept the insert, positioning the sheets around the core with the insert placed in the cavity and securing the assembly together; creating a vacuum and closing the assembly by welding; consolidation by hot isostatic pressing; cutting the assembly to extract the core and separate the reinforcement; creating an external profile of the reinforcement by a final machining operation that reveals a material of the insert.Type: GrantFiled: April 11, 2013Date of Patent: May 8, 2018Assignee: SNECMAInventors: Jean-Michel Patrick Maurice Franchet, Gilles Charles Casimir Klein, Gilbert Michel Marin Leconte, Dominique Magnaudeix
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Patent number: 9874103Abstract: A method of making a metal reinforcing member that is to be mounted on a leading edge or a trailing edge of a composite blade of a turbine engine, the method including: shaping two metal sheets, positioning them on either side of a core including at least one recess that is to form a mold for a spacer for positioning the reinforcing member, assembling them together under a vacuum, conforming them against the core by hot isostatic compression, and cutting them to separate the reinforcing member and release the core.Type: GrantFiled: May 31, 2013Date of Patent: January 23, 2018Assignee: SNECMAInventors: Gilbert Michel Marin Leconte, Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Dominique Magnaudeix
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Publication number: 20170342524Abstract: A titanium-based intermetallic alloy includes, in atomic percent, 16% to 26% Al, 18% to 28% Nb, 0% to 3% of a metal M selected from Mo, W, Hf, and V, 0.1% to 2% of Si, 0% to 2% of Ta, 1% to 4% of Zr, with the condition Fe+Ni?400 ppm, the balance being Ti, the alloy also presenting an Al/Nb ratio in atomic percent lying in the range 1.05 to 1.15.Type: ApplicationFiled: December 14, 2015Publication date: November 30, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Jean-Yves GUEDOU, Jean-Michel Patrick Maurice FRANCHET, Jean-Loup Bernard Victor STRUDEL, Laurent GERMANN, Dipankar BANERJEE, Vikas KUMAR, Tapash NANDY
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Publication number: 20170274470Abstract: A field of rotary blades, and more particularly to a method of fabricating a leading edge shield for protecting such a blade. The method includes at least steps of performing initial plastic deformation on at least one sheet from a pressure side sheet and a suction side sheet, using additive fabrication to add a reinforcement with a fiber insert on at least one of the pressure and suction side sheets, closing the pressure and suction side sheets around a core after the initial plastic deformation and after adding the reinforcement, performing subsequent plastic deformation by pressing the pressure and suction side sheets against an outside surface of the core after the sheets have been closed around the core, and extracting the core.Type: ApplicationFiled: September 18, 2015Publication date: September 28, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Gilles Charles Casimir KLEIN, Jean-Michel Patrick Maurice FRANCHET, Dominique Michel Serge MAGNAUDEIX
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Patent number: 9708701Abstract: A device for metal coating of fibers, for example ceramic fibers, by a liquid process, the device including a crucible containing a liquid metal bath through which a fiber is drawn to be coated with the metal, and a cooling system positioned downstream from the metal bath to solidify the metal sheath created around the fiber by capillarity. The cooling system includes at least one nozzle for ejecting a compressed gas towards the coated fiber, and the system is sized such as to solidify the metal on the periphery of the coated fiber over a length of no more than 200 mm.Type: GrantFiled: February 16, 2011Date of Patent: July 18, 2017Assignee: SNECMAInventors: Jean-Michel Patrick Maurice Franchet, Gilles Charles Casimir Klein, Gerald Sanchez
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Patent number: 9598966Abstract: In structural reinforcement for a composite blade of a turbine engine, the reinforcement being for adhesively bonding to a leading edge of the blade and presenting over its full height a section that is substantially V-shaped, having a base that is extended by two lateral flanks, there is provided an assembly of a plurality of fiber bundles that is mounted in at least one housing in the base, which assembly defines fiber content that varies along the full height of the housing.Type: GrantFiled: April 25, 2013Date of Patent: March 21, 2017Assignee: SNECMAInventors: Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Dominique Magnaudeix, Gilbert Michel Marin Leconte
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Patent number: 9482102Abstract: A method of reinforcing a mechanical part, for example a turbine engine part, the part being made by assembling together two portions, the method including: inserting reinforcing mechanisms of elongate shape at least in part in at least one recess formed in one of the portions and opening out into a junction surface between the portions; and assembling the two portions together.Type: GrantFiled: May 23, 2012Date of Patent: November 1, 2016Assignee: SNECMAInventors: Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Gilbert Michel Marin Leconte, Dominique Magnaudeix
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Patent number: 9328614Abstract: A metal reinforcing piece for mounting on a leading edge or trailing edge of a composite blade for a turbine engine is made by shaping two metal sheets, positioning them on either side of a core, assembling the two sheets together around the core under a vacuum, shaping them on the core by hot isostatic compression, and cutting them to separate the reinforcing piece and release the core. A predetermined roughness is given to at least a portion of the surface of the core and is transferred to a corresponding portion of an inside surface of the reinforcing piece by the hot isostatic compression.Type: GrantFiled: January 10, 2012Date of Patent: May 3, 2016Assignee: SNECMAInventors: Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Gilbert Michel Marin Leconte, Dominique Magnaudeix
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Patent number: 9314834Abstract: A device for shaping a metal sheet by die stamping, the device including first and second trunnions configured to be fastened respectively to two opposite ends of a sheet, the sheet being configured to be shaped by die stamping, wherein the first and second trunnions define respective first and second bearing surfaces configured respectively to guide turning of the trunnions, the first bearing surface defining a peripheral groove around a pivot axis of the first trunnion while the second bearing surface is smooth along a pivot axis of the second trunnion.Type: GrantFiled: August 9, 2012Date of Patent: April 19, 2016Assignee: SNECMAInventors: Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Gilbert Michel Marin Leconte, Dominique Magnaudeix
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Patent number: 9127337Abstract: A method of manufacturing a mechanical component, and winding device to implementing the method. The component includes at least one insert of metal matrix composite, within which matrix ceramic fibers extend, the composite insert obtained from a plurality of coated filaments each including a ceramic fiber coated with a metal sheath. The method manufactures an insert preform by winding a bonded lap or bundle of coated filaments about a cylindrical component. At least some of the winding is performed in at least one rectilinear direction. The method further inserts the insert preform in a first container; performs hot isostatic compaction of the first container; and machines the first container to form a rectilinear insert.Type: GrantFiled: July 10, 2008Date of Patent: September 8, 2015Assignees: SNECMA, MESSIER-BUGATTI-DOWTYInventors: Patrick Dunleavy, Jean-Michel Patrick Maurice Franchet, Gilles Charles Casimir Klein, Richard Masson