Patents by Inventor Ludovic Edmond Camille Molliex
Ludovic Edmond Camille Molliex 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: 10989066Abstract: The present invention relates to an abradable coating for a turbine engine part, characterized by the fact that said coating includes a layer made of an abradable material, the surface asperities of which are filled with thermally bonded ceramic grains, forming a smooth, free surface having a low roughness.Type: GrantFiled: June 25, 2019Date of Patent: April 27, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Michael Podgorski, Philippe Charles Alain Le Biez, Ludovic Edmond Camille Molliex, Serge Selezneff
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Publication number: 20190309651Abstract: The present invention relates to an abradable coating for a turbine engine part, characterized by the fact that said coating includes a layer made of an abradable material, the surface asperities of which are filled with thermally bonded ceramic grains, forming a smooth, free surface having a low roughnessType: ApplicationFiled: June 25, 2019Publication date: October 10, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Michael PODGORSKI, Philippe Charles, Alain LE BIEZ, Ludovic Edmond, Camille Molliex, Serge SELEZNEFF
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Patent number: 10427983Abstract: A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; impregnating the fiber texture for a first time with a first slip containing first refractory particles; eliminating the liquid phase from the first slip so as to leave within the texture only the first refractory particles; impregnating the fiber texture for a second time with a second slip containing second refractory particles; eliminating the liquid phase from the second slip so as to leave within the texture only the second refractory particles and obtain a fiber preform filled with the first and second refractory particles; and sintering the first and second refractory particles present in the fiber preform in order to form a refractory matrix in the preform.Type: GrantFiled: December 18, 2015Date of Patent: October 1, 2019Assignees: SAFRAN AIRCRAFT ENGINES, SAFRANInventors: Michael Podgorski, Catherine Billotte Cabre, Bruno Jacques Gérard Dambrine, Ludovic Edmond Camille Molliex, Edu Ruiz, Sylvain Turenne
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Patent number: 10385725Abstract: The present invention relates to an abradable coating for a turbine engine part, characterized by the fact that said coating includes a layer made of an abradable material, the surface asperities of which are filled with thermally bonded ceramic grains, forming a smooth, free surface having a low roughness.Type: GrantFiled: August 5, 2013Date of Patent: August 20, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Michael Podgorski, Philippe Charles Alain Le Biez, Ludovic Edmond Camille Molliex, Serge Selezneff
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Patent number: 10328604Abstract: A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; placing the texture in a mold having an impregnation chamber including in its bottom portion a part made of porous material, the impregnation chamber being closed in its top portion by a deformable impermeable diaphragm separating the impregnation chamber from a compacting chamber; injecting a slip containing a powder of refractory particles into the impregnation chamber; injecting a compression fluid into the compacting chamber, to force the slip to pass through the texture; draining the liquid of the slip via the porous material part, while retaining the powder of refractory particles inside the texture so as to obtain a fiber preform filled with refractory particles; drying the fiber preform; unmolding the preform; and sintering the refractory particles present in the preform in order to form a refractory matrix in the preform.Type: GrantFiled: December 18, 2015Date of Patent: June 25, 2019Assignees: SAFRAN AIRCRAFT ENGINES, SAFRANInventors: Michael Podgorski, Catherine Billotte Cabre, Bruno Jacques Gérard Dambrine, Ludovic Edmond Camille Molliex, Edu Ruiz, Sylvain Turenne
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Patent number: 10240466Abstract: A fiber preform for a hollow turbine engine vane, the preform including a main fiber structure obtained by three-dimensional weaving and including at least one main part, wherein the main part extends from a first link strip, includes a first main longitudinal portion forming a pressure side wall of an airfoil, an U-turn bend portion forming a leading edge or a trailing edge of the airfoil, a second main longitudinal portion facing the first main longitudinal portion and forming a suction side wall of the airfoil, and terminating at a second link strip. The first and second link strips are secured to each other and form a link portion of the main fiber structure. The main longitudinal portions are spaced apart so as to form a gap between the main longitudinal portions forming a hollow in the airfoil.Type: GrantFiled: October 3, 2014Date of Patent: March 26, 2019Assignees: SAFRAN AIRCRAFT ENGINES, SAFRANInventors: Michael Podgorski, Bruno Jacques Gerard Dambrine, Son Le Hong, Dominique Marie Christian Coupe, Ludovic Edmond Camille Molliex, Jonathan Goering
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Patent number: 10124547Abstract: A method of identifying and/or tracking deformation of a mechanical part made of composite material for a turbine engine, in which the part includes a preform of fiber material and a resin, is provided. The method includes incorporating metal particles in the preform or the resin during fabrication of the part, and subjecting the mechanical part to two X-ray inspections on two different occasions so as to identify the part and/or so as to deduce deformation of its internal structure.Type: GrantFiled: September 26, 2013Date of Patent: November 13, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Julien Schneider, Ludovic Edmond Camille Molliex
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Publication number: 20170341263Abstract: A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; placing the texture in a mold having an impregnation chamber including in its bottom portion a part made of porous material, the impregnation chamber being closed in its top portion by a deformable impermeable diaphragm separating the impregnation chamber from a compacting chamber; injecting a slip containing a powder of refractory particles into the impregnation chamber; injecting a compression fluid into the compacting chamber, to force the slip to pass through the texture; draining the liquid of the slip via the porous material part, while retaining the powder of refractory particles inside the texture so as to obtain a fiber preform filled with refractory particles; drying the fiber preform; unmolding the preform; and sintering the refractory particles present in the preform in order to form a refractory matrix in the preform.Type: ApplicationFiled: December 18, 2015Publication date: November 30, 2017Inventors: Michael PODGORSKI, Catherine BILLOTTE CABRE, Bruno Jacques Gérard DAMBRINE, Ludovic Edmond Camille MOLLIEX, Edu RUIZ, Sylvain TURENNE
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Publication number: 20170334791Abstract: A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; impregnating the fiber texture for a first time with a first slip containing first refractory particles; eliminating the liquid phase from the first slip so as to leave within the texture only the first refractory particles; impregnating the fiber texture for a second time with a second slip containing second refractory particles; eliminating the liquid phase from the second slip so as to leave within the texture only the second refractory particles and obtain a fiber preform filled with the first and second refractory particles; and sintering the first and second refractory particles present in the fiber preform in order to form a refractory matrix in the preform.Type: ApplicationFiled: December 18, 2015Publication date: November 23, 2017Inventors: Michael PODGORSKI, Catherine BILLOTTE CABRE, Bruno Jacques Gérard DAMBRINE, Ludovic Edmond Camille MOLLIEX, Edu RUIZ, Sylvain TURENNE
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Patent number: 9802869Abstract: An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade.Type: GrantFiled: December 6, 2013Date of Patent: October 31, 2017Assignee: SNECMAInventors: Michael Podgorski, Bruno Jacques Gerard Dambrine, Ludovic Edmond Camille Molliex, Beryl Cassandre Anne Mereaux
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Publication number: 20160348518Abstract: A fiber preform for a hollow turbine engine vane, and a method of fabricating such a hollow vane are provided. The preform includes a first fiber structure including a main longitudinal portion for forming a pressure side wall of an airfoil; a second fiber structure including a main longitudinal portion for forming a suction side wall of the airfoil; each of the first and second fiber structures includes a first interlinking zone extending along the front edge of its main longitudinal portion, which first zones are integral with each other and form a first interlinking portion, and a second interlinking zone extending along the rear edge of its main longitudinal portion, the second zones being integral with each other and forming a second interlinking portion. The main longitudinal portions of the first and second fiber structures are dissociated so as to leave a gap between the main longitudinal portions forming an airfoil hollow.Type: ApplicationFiled: October 22, 2014Publication date: December 1, 2016Applicants: SNECMA, SAFRANInventors: Michael PODGORSKI, Dominique Marie Christian COUPE, Bruno Jacques Gerard DAMBRINE, Son LE HONG, Ludovic Edmond Camille MOLLIEX
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Publication number: 20160273372Abstract: A fiber preform for a hollow turbine engine vane, the preform including a main fiber structure obtained by three-dimensional weaving and including at least one main part, wherein the main part extends from a first link strip, includes a first main longitudinal portion forming a pressure side wall of an airfoil, an U-turn bend portion forming a leading edge or a trailing edge of the airfoil, a second main longitudinal portion facing the first main longitudinal portion and forming a suction side wall of the airfoil, and terminating at a second link strip. The first and second link strips are secured to each other and form a link portion of the main fiber structure. The main longitudinal portions are spaced apart so as to form a gap between the main longitudinal portions forming a hollow in the airfoil.Type: ApplicationFiled: October 3, 2014Publication date: September 22, 2016Applicants: SNECMA, SAFRANInventors: Michael PODGORSKI, Bruno Jacques, Gerard DAMBRINE, Son LE HONG, Dominique Marie, Christian COUPE, Ludovic Edmond, Camille MOLLIEX, Jonathan GEORING
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Publication number: 20150211382Abstract: The present invention relates to an abradable coating for a turbine engine part, characterized by the fact that said coating includes a layer made of an abradable material, the surface asperities of which are filled with thermally bonded ceramic grains, forming a smooth, free surface having a low roughnessType: ApplicationFiled: August 5, 2013Publication date: July 30, 2015Applicant: SNECMAInventors: Michael Podgorski, Philippe Charles, Alain Le Biez, Ludovic Edmond, Camille Molliex, Serge Selezneff
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Publication number: 20140161626Abstract: An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade.Type: ApplicationFiled: December 6, 2013Publication date: June 12, 2014Applicant: SNECMAInventors: Michael PODGORSKI, Bruno Jacques, Gerard Dambrine, Ludovic Edmond, Camille Molliex, Beryl Cassandre, Anne Mereaux
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Patent number: 7334999Abstract: 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.Type: GrantFiled: June 28, 2006Date of Patent: February 26, 2008Assignee: SnecmaInventors: Caroline Aumont, Sandrine Chatel, Bruno Jacques Gerard Dambrine, Didier Rene Andre Escure, Jean-Francois Fromentin, Jean-yves Guedou, Ludovic Edmond Camille Molliex, Stephane Rousselin
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Patent number: 6379480Abstract: The invention concerns a method for producing parts made of thin, light and rigid metal alloy essentially having the following steps: producing a core having the part shape; producing cavities in the core; producing shells made of metal alloy combined with reinforcing fibers with high modulus of elasticity; densifying the shells; and diffusion welding of the shells on the core by compression at temperature and pressure conditions for isothermal forging of the metal alloy used.Type: GrantFiled: June 15, 2000Date of Patent: April 30, 2002Assignee: Societe National d'Etude et de Construction de Moteurs d'Aviation “snecma”Inventors: Daniel Georges Girault, Gérard Philippe Gauthier, Ludovic Edmond Camille Molliex
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Patent number: 6174570Abstract: The invention concerns a method for metal coating of fibres (15) by liquid process, said method being particularly but not exclusively designed for coating in thick and even layers (22) with metals and metal alloys having high melting point and reactivity. Said method is characterised in that it consists in moving along the stretched fibre (15) in the liquid metal maintained in levitation in a well (1), said fibre (15) passing through orifices (6, 7) provided in the well (1) wall (3), said orifices (6, 7) being arranged on either side of the liquid metal at places where the liquid metal (10) is not in contact with said wall (3).Type: GrantFiled: September 22, 1999Date of Patent: January 16, 2001Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “SNECMA”Inventors: Bruno Jacques G{acute over (e)}rard Dambrine, Marcel Garnier, Jean Hamburger, Yves Christian Louis Alain Honnorat, Ludovic Edmond Camille Molliex, Jos{acute over (e)} Feigenblum, G{acute over (e)}rard Weiss
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Patent number: 5733495Abstract: A blank consisting of a spirally wound fiber for use in the manufacture of a fiber reinforced article of composite material is made by winding the fiber onto a helical track on the surface of a frusto-conical spindle, covering the wound fiber with a thermoplastic binder which sets to form a frusto-conical shell encasing the fiber, removing the shell from the spindle and placing the shell with its base on a plate, and heating the shell starting from its base so as to soften it and cause it to progressively collapse onto the plate to form a disc comprising a spirally wound fiber. If necessary the collapse of the shell may be assisted by pressing on the shell in a direction towards the plate.Type: GrantFiled: September 25, 1996Date of Patent: March 31, 1998Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"Inventors: Jean-Claude Robert Berthelemy, Gerard Philippe Gauthier, Ludovic Edmond Camille Molliex, Alain Robert Yves Perroux
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Patent number: 5678164Abstract: A process for constructing a circular metallic article which includes a hub and a plurality of vanes mounted on the periphery of the hub wherein the vanes are placed in position around the hub, formers are arranged between the blade portions of the vanes, a dimensionally stable belt having a low thermal expansion coefficient is placed circumferentially around the vanes and the formers, and the assembly is subjected to an isostatic compression at the isothermal forging temperature and pressure of the materials of the hub and the vanes such that the vanes are diffusion welded to the hub and the blade portions of the vanes are compressed to shape.Type: GrantFiled: August 24, 1995Date of Patent: October 14, 1997Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"Inventors: Jean-Claude Berthelemy, Ludovic Edmond Camille Molliex
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Patent number: 5642851Abstract: An apparatus for producing a circular metal article reinforced by fibres in selected parts of its cross-section is described in which a metal blank of the article is formed and provided with at least one annular groove opening in the axial direction, preforms of reinforcing fibre and filler metal are placed in the groove which is then closed by a metal plug, and the assembly is isothermally forged to produce the article in a single forging step which serves to compress the preforms, weld the assembly together, and shape the article. Such articles may be used for machining high performance rotors for turbojet engines.Type: GrantFiled: March 20, 1996Date of Patent: July 1, 1997Assignee: Societe Nationale D'Etude et de Construction de Moteurs D'Aviation "Snecma"Inventors: Jean-Claude Berthelemy, Gilles Jean-Michel Bessenay, Gerard Philippe Gauthier, Daniel Georges Girault, Ludovic Edmond Camille Molliex