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).
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Patent number: 11725261Abstract: The invention relates to a nickel-based superalloy comprising, 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. The invention also relates to a single-crystal blade (20A, 20B) comprising such an alloy and a turbomachine (10) comprising such a blade (20A, 20B).Type: GrantFiled: April 6, 2022Date of Patent: August 15, 2023Assignees: SAFRAN, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Jérémy Rame, Virginie Jaquet, Joël Delautre, Jean-Yves Guedou, Pierre Caron, Odile Lavigne, Didier Locq, Mikael Perrut
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Publication number: 20220364208Abstract: The invention relates to a nickel-based superalloy comprising, 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. The invention also relates to a single-crystal blade (20A, 20B) comprising such an alloy and a turbomachine (10) comprising such a blade (20A, 20B).Type: ApplicationFiled: April 6, 2022Publication date: November 17, 2022Applicants: SAFRAN, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Jérémy RAME, Virginie JAQUET, Joël DELAUTRE, Jean-Yves GUEDOU, Pierre CARON, Odile LAVIGNE, Didier LOCQ, Mikael PERRUT
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Patent number: 11396685Abstract: 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: GrantFiled: November 14, 2018Date of Patent: July 26, 2022Assignees: SAFRAN, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Jérémy Rame, Virginie Jaquet, Joël Delautre, Jean-Yves Guedou, Pierre Caron, Odile Lavigne, Didier Locq, Mikael Perrut
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Patent number: 11268170Abstract: 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: GrantFiled: November 14, 2018Date of Patent: March 8, 2022Assignees: SAFRAN, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Jérémy Rame, Virginie Jaquet, Joël Delautre, Jean-Yves Guedou, Pierre Caron, Odile Lavigne, Didier Locq, Mikael Perrut
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Patent number: 11220727Abstract: 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: GrantFiled: October 24, 2017Date of Patent: January 11, 2022Assignees: Safran, Safran Aircraft Engines, Office National D'Etudes et de Recherches Aerospatiales, Safran Helicopter EnginesInventors: Jérémy Rame, Philippe Belaygue, Pierre Caron, Joël Delautre, Virginie Jaquet, Odile Lavigne
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Publication number: 20210246533Abstract: 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: ApplicationFiled: November 14, 2018Publication date: August 12, 2021Applicants: SAFRAN, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Jérémy RAME, Virginie JAQUET, Joël DELAUTRE, Jean-Yves GUEDOU, Pierre CARON, Odile LAVIGNE, Didier LOCQ, Mikael PERRUT
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Publication number: 20200299808Abstract: 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: ApplicationFiled: November 14, 2018Publication date: September 24, 2020Applicants: SAFRAN, OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALESInventors: Jérémy RAME, Virginie JAQUET, Joël DELAUTRE, Jean-Yves GUEDOU, Pierre CARON, Odile LAVIGNE, Didier LOCQ, Mikael PERRUT
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Publication number: 20190330714Abstract: 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: ApplicationFiled: October 24, 2017Publication date: October 31, 2019Applicants: Safran, Safran Aircraft Engines, Office National D'Etudes et de Recherches Aerospatiales, Safran Helicopter EnginesInventors: Jérémy RAME, Philippe BELAYGUE, Pierre CARON, Joël DELAUTRE, Virginie JAQUET, Odile LAVIGNE
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Patent number: 10267151Abstract: 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 contType: GrantFiled: December 1, 2014Date of Patent: April 23, 2019Assignee: Office National D'Etudes et de Recherches AerospatialesInventors: Marie-Pierre Bacos, Odile Lavigne, Catherine Rio, Marie-Helene Vidal-Setif, Frederic Rousseau, Daniel Morvan
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Publication number: 20170044901Abstract: 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 contType: ApplicationFiled: December 1, 2014Publication date: February 16, 2017Inventors: Marie-Pierre Bacos, Odile Lavigne, Catherine Rio, Marie-Helene Vidal-Setif, Frederic Rousseau, Daniel Morvan
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Patent number: 6333118Abstract: 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: GrantFiled: September 11, 2000Date of Patent: December 25, 2001Assignee: SNECMA MoteursInventors: Serge Alperine, Véronique Arnault, Odile Lavigne, Rémy Mevrel