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).

  • Patent number: 10989066
    Abstract: 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: Grant
    Filed: June 25, 2019
    Date of Patent: April 27, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Michael Podgorski, Philippe Charles Alain Le Biez, Ludovic Edmond Camille Molliex, Serge Selezneff
  • Publication number: 20190309651
    Abstract: 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: Application
    Filed: June 25, 2019
    Publication date: October 10, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Michael PODGORSKI, Philippe Charles, Alain LE BIEZ, Ludovic Edmond, Camille Molliex, Serge SELEZNEFF
  • Patent number: 10427983
    Abstract: 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: Grant
    Filed: December 18, 2015
    Date of Patent: October 1, 2019
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN
    Inventors: Michael Podgorski, Catherine Billotte Cabre, Bruno Jacques Gérard Dambrine, Ludovic Edmond Camille Molliex, Edu Ruiz, Sylvain Turenne
  • Patent number: 10385725
    Abstract: 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: Grant
    Filed: August 5, 2013
    Date of Patent: August 20, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Michael Podgorski, Philippe Charles Alain Le Biez, Ludovic Edmond Camille Molliex, Serge Selezneff
  • Patent number: 10328604
    Abstract: 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: Grant
    Filed: December 18, 2015
    Date of Patent: June 25, 2019
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN
    Inventors: Michael Podgorski, Catherine Billotte Cabre, Bruno Jacques Gérard Dambrine, Ludovic Edmond Camille Molliex, Edu Ruiz, Sylvain Turenne
  • Patent number: 10240466
    Abstract: 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: Grant
    Filed: October 3, 2014
    Date of Patent: March 26, 2019
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN
    Inventors: Michael Podgorski, Bruno Jacques Gerard Dambrine, Son Le Hong, Dominique Marie Christian Coupe, Ludovic Edmond Camille Molliex, Jonathan Goering
  • Patent number: 10124547
    Abstract: 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: Grant
    Filed: September 26, 2013
    Date of Patent: November 13, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Julien Schneider, Ludovic Edmond Camille Molliex
  • Publication number: 20170341263
    Abstract: 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: Application
    Filed: December 18, 2015
    Publication date: November 30, 2017
    Inventors: Michael PODGORSKI, Catherine BILLOTTE CABRE, Bruno Jacques Gérard DAMBRINE, Ludovic Edmond Camille MOLLIEX, Edu RUIZ, Sylvain TURENNE
  • Publication number: 20170334791
    Abstract: 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: Application
    Filed: December 18, 2015
    Publication date: November 23, 2017
    Inventors: Michael PODGORSKI, Catherine BILLOTTE CABRE, Bruno Jacques Gérard DAMBRINE, Ludovic Edmond Camille MOLLIEX, Edu RUIZ, Sylvain TURENNE
  • Patent number: 9802869
    Abstract: 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: Grant
    Filed: December 6, 2013
    Date of Patent: October 31, 2017
    Assignee: SNECMA
    Inventors: Michael Podgorski, Bruno Jacques Gerard Dambrine, Ludovic Edmond Camille Molliex, Beryl Cassandre Anne Mereaux
  • Publication number: 20160348518
    Abstract: 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: Application
    Filed: October 22, 2014
    Publication date: December 1, 2016
    Applicants: SNECMA, SAFRAN
    Inventors: Michael PODGORSKI, Dominique Marie Christian COUPE, Bruno Jacques Gerard DAMBRINE, Son LE HONG, Ludovic Edmond Camille MOLLIEX
  • Publication number: 20160273372
    Abstract: 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: Application
    Filed: October 3, 2014
    Publication date: September 22, 2016
    Applicants: SNECMA, SAFRAN
    Inventors: Michael PODGORSKI, Bruno Jacques, Gerard DAMBRINE, Son LE HONG, Dominique Marie, Christian COUPE, Ludovic Edmond, Camille MOLLIEX, Jonathan GEORING
  • Publication number: 20150211382
    Abstract: 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: Application
    Filed: August 5, 2013
    Publication date: July 30, 2015
    Applicant: SNECMA
    Inventors: Michael Podgorski, Philippe Charles, Alain Le Biez, Ludovic Edmond, Camille Molliex, Serge Selezneff
  • Publication number: 20140161626
    Abstract: 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: Application
    Filed: December 6, 2013
    Publication date: June 12, 2014
    Applicant: SNECMA
    Inventors: Michael PODGORSKI, Bruno Jacques, Gerard Dambrine, Ludovic Edmond, Camille Molliex, Beryl Cassandre, Anne Mereaux
  • Patent number: 7334999
    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.
    Type: Grant
    Filed: June 28, 2006
    Date of Patent: February 26, 2008
    Assignee: Snecma
    Inventors: Caroline Aumont, Sandrine Chatel, Bruno Jacques Gerard Dambrine, Didier Rene Andre Escure, Jean-Francois Fromentin, Jean-yves Guedou, Ludovic Edmond Camille Molliex, Stephane Rousselin
  • Patent number: 6379480
    Abstract: 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: Grant
    Filed: June 15, 2000
    Date of Patent: April 30, 2002
    Assignee: Societe National d'Etude et de Construction de Moteurs d'Aviation “snecma”
    Inventors: Daniel Georges Girault, Gérard Philippe Gauthier, Ludovic Edmond Camille Molliex
  • Patent number: 6174570
    Abstract: 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: Grant
    Filed: September 22, 1999
    Date of Patent: January 16, 2001
    Assignee: 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
  • Patent number: 5733495
    Abstract: 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: Grant
    Filed: September 25, 1996
    Date of Patent: March 31, 1998
    Assignee: 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
  • Patent number: 5678164
    Abstract: 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: Grant
    Filed: August 24, 1995
    Date of Patent: October 14, 1997
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"
    Inventors: Jean-Claude Berthelemy, Ludovic Edmond Camille Molliex
  • Patent number: 5642851
    Abstract: 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: Grant
    Filed: March 20, 1996
    Date of Patent: July 1, 1997
    Assignee: 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