Patents by Inventor Nicolas Camille Claude CURLIER

Nicolas Camille Claude CURLIER 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: 11873783
    Abstract: A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.
    Type: Grant
    Filed: April 11, 2023
    Date of Patent: January 16, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Brice Marie Yves Emile Le Pannerer, Jean-François Cabre, Nicolas Camille Claude Curlier, Lucas Arthur Pflieger
  • Publication number: 20230265814
    Abstract: A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.
    Type: Application
    Filed: April 11, 2023
    Publication date: August 24, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Brice Marie Yves Emile LE PANNERER, Jean-François CABRE, Nicolas Camille Claude CURLIER, Lucas Arthur PFLIEGER
  • Patent number: 11686274
    Abstract: A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.
    Type: Grant
    Filed: May 28, 2020
    Date of Patent: June 27, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Brice Marie Yves Emile Le Pannerer, Jean-François Cabre, Nicolas Camille Claude Curlier, Lucas Arthur Pflieger
  • Publication number: 20220252023
    Abstract: A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.
    Type: Application
    Filed: May 28, 2020
    Publication date: August 11, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Brice Marie Yves Emile LE PANNERER, Jean-François CABRE, Nicolas Camille Claude CURLIER, Lucas Arthur PFLIEGER