Patents by Inventor Odile Lavigne

Odile Lavigne 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: 11268170
    Abstract: A nickel-based superalloy comprises, in percentages by mass, 4.0 to 5.5% rhenium, 3.5 to 12.5% cobalt, 0.30 to 1.50% molybdenum, 3.5 to 5.5% chromium, 3.5 to 5.5% tungsten, 4.5 to 6.0% aluminum, 0.35 to 1.50% titanium, 8.0 to 10.5% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. A single-crystal blade comprises such an alloy and a turbomachine comprising such a blade.
    Type: Grant
    Filed: November 14, 2018
    Date of Patent: March 8, 2022
    Assignees: SAFRAN, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES
    Inventors: Jérémy Rame, Virginie Jaquet, Joël Delautre, Jean-Yves Guedou, Pierre Caron, Odile Lavigne, Didier Locq, Mikael Perrut
  • Patent number: 11220727
    Abstract: A nickel-based superalloy comprises in mass percent: 4.0% to 6.0% chromium; 0.4% to 0.8% molybdenum; 2.5% to 3.5% rhenium; 6.2% to 6.6% tungsten; 5.2% to 5.7% aluminum; 0.0 to 1.6% titanium; 6.0% to 9.9% tantalum; 0.0 to 0.7% hafnium; and 0.0 to 0.3% silicon; the balance being constituted by nickel and any impurities. A monocrystalline blade comprises such an alloy and a turbomachine including such a blade.
    Type: Grant
    Filed: October 24, 2017
    Date of Patent: January 11, 2022
    Assignees: Safran, Safran Aircraft Engines, Office National D'Etudes et de Recherches Aerospatiales, Safran Helicopter Engines
    Inventors: Jérémy Rame, Philippe Belaygue, Pierre Caron, Joël Delautre, Virginie Jaquet, Odile Lavigne
  • Publication number: 20210246533
    Abstract: A nickel-based superalloy comprises, in percentages by mass, 4.0 to 5.5% rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0% cobalt, 0.3 to 1.0% molybdenum, 3.0 to 5.0% chromium, 2.5 to 4.0% tungsten, 4.5 to 6.5% aluminum, 0.50 to 1.50% titanium, 8.0 to 9.0% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. A single-crystal blade comprises such an alloy and a turbomachine comprising such a blade.
    Type: Application
    Filed: November 14, 2018
    Publication date: August 12, 2021
    Applicants: SAFRAN, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES
    Inventors: Jérémy RAME, Virginie JAQUET, Joël DELAUTRE, Jean-Yves GUEDOU, Pierre CARON, Odile LAVIGNE, Didier LOCQ, Mikael PERRUT
  • Publication number: 20200299808
    Abstract: A nickel-based superalloy comprises, in percentages by mass, 4.0 to 5.5% rhenium, 3.5 to 12.5% cobalt, 0.30 to 1.50% molybdenum, 3.5 to 5.5% chromium, 3.5 to 5.5% tungsten, 4.5 to 6.0% aluminum, 0.35 to 1.50% titanium, 8.0 to 10.5% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. A single-crystal blade comprises such an alloy and a turbomachine comprising such a blade.
    Type: Application
    Filed: November 14, 2018
    Publication date: September 24, 2020
    Applicants: SAFRAN, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES
    Inventors: Jérémy RAME, Virginie JAQUET, Joël DELAUTRE, Jean-Yves GUEDOU, Pierre CARON, Odile LAVIGNE, Didier LOCQ, Mikael PERRUT
  • Publication number: 20190330714
    Abstract: A nickel-based superalloy comprises in mass percent: 4.0% to 6.0% chromium; 0.4% to 0.8% molybdenum; 2.5% to 3.5% rhenium; 6.2% to 6.6% tungsten; 5.2% to 5.7% aluminum; 0.0 to 1.6% titanium; 6.0% to 9.9% tantalum; 0.0 to 0.7% hafnium; and 0.0 to 0.3% silicon; the balance being constituted by nickel and any impurities. A monocrystalline blade comprises such an alloy and a turbomachine including such a blade.
    Type: Application
    Filed: October 24, 2017
    Publication date: October 31, 2019
    Applicants: Safran, Safran Aircraft Engines, Office National D'Etudes et de Recherches Aerospatiales, Safran Helicopter Engines
    Inventors: Jérémy RAME, Philippe BELAYGUE, Pierre CARON, Joël DELAUTRE, Virginie JAQUET, Odile LAVIGNE
  • Patent number: 10267151
    Abstract: The invention relates to a method for repairing a thermal barrier of a component comprising a substrate coated with such a thermal barrier, said substrate being made of a high-performance alloy, said thermal barrier being adhered to the alloy and having lower thermal conductivity than the alloy, the thermal barrier including at least one ceramic, one region of the thermal barrier being a region to be repaired, wherein said method includes the following steps: a) defining the region to be repaired, using a mask which protects the other regions of the thermal barrier; b) injecting a carrier gas loaded with droplets of ceramic precursor into a plasma discharge inside a plasma chamber of a plasma reactor containing the component to be repaired, while making the concentration of ceramic precursor in the carrier gas dependent on at least one parameter of the reactor selected from among: the pressure of the plasma chamber, the power of the plasma generator and the diameter of the precursor droplets, in order to cont
    Type: Grant
    Filed: December 1, 2014
    Date of Patent: April 23, 2019
    Assignee: Office National D'Etudes et de Recherches Aerospatiales
    Inventors: Marie-Pierre Bacos, Odile Lavigne, Catherine Rio, Marie-Helene Vidal-Setif, Frederic Rousseau, Daniel Morvan
  • Publication number: 20170044901
    Abstract: The invention relates to a method for repairing a thermal barrier of a component comprising a substrate coated with such a thermal barrier, said substrate being made of a high-performance alloy, said thermal barrier being adhered to the alloy and having lower thermal conductivity than the alloy, the thermal barrier including at least one ceramic, one region of the thermal barrier being a region to be repaired, wherein said method includes the following steps: a) defining the region to be repaired, using a mask which protects the other regions of the thermal barrier; b) injecting a carrier gas loaded with droplets of ceramic precursor into a plasma discharge inside a plasma chamber of a plasma reactor containing the component to be repaired, while making the concentration of ceramic precursor in the carrier gas dependent on at least one parameter of the reactor selected from among: the pressure of the plasma chamber, the power of the plasma generator and the diameter of the precursor droplets, in order to cont
    Type: Application
    Filed: December 1, 2014
    Publication date: February 16, 2017
    Inventors: Marie-Pierre Bacos, Odile Lavigne, Catherine Rio, Marie-Helene Vidal-Setif, Frederic Rousseau, Daniel Morvan
  • Patent number: 6333118
    Abstract: A low thermal conductivity heat barrier composition, particularly for a superalloy article, is disclosed comprising a zirconia base and a dysprosium oxide having the dual function of stabilizing the zirconia and reducing the thermal conductivity thereof. Optionally, the composition also comprises a metal oxide containing a quadrivalent metallic ion selected from the group consisting of hafnium dioxide, cerium dioxide, uranium dioxide, and mixtures thereof.
    Type: Grant
    Filed: September 11, 2000
    Date of Patent: December 25, 2001
    Assignee: SNECMA Moteurs
    Inventors: Serge Alperine, Véronique Arnault, Odile Lavigne, Rémy Mevrel