Patents by Inventor Romain Jean-François Guerit

Romain Jean-François Guerit 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: 12049831
    Abstract: A method repairs welding of an aircraft turbine engine blade that has a lower surface and an upper surface connected by a leading edge and a trailing edge. The blade further includes a free end referred to as the tip. The method includes the repair welding of the tip and including the steps of: securing a first stop to the leading edge at the tip and a second stop to the trailing edge at the tip, depositing a repair weld bead on the tip, from the first stop to the second stop, and removing the first and second stops. The first and second stops are secured solely by squeezing same on the leading and trailing edges.
    Type: Grant
    Filed: October 1, 2020
    Date of Patent: July 30, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Pascal Jean-Marc Charpentier, Romain Jean-François Guerit
  • Publication number: 20220341325
    Abstract: A method repairs welding of an aircraft turbine engine blade that has a lower surface and an upper surface connected by a leading edge and a trailing edge The blade further includes a free end referred to as the tip. The method includes the repair welding of the tip and including the steps of: securing a first stop to the leading edge at the tip and a second stop to the trailing edge at the tip, depositing a repair weld bead on the tip, from the first stop to the second stop, and removing the first and second stops. The first and second stops are secured solely by squeezing same on the leading and trailing edges.
    Type: Application
    Filed: October 1, 2020
    Publication date: October 27, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Pascal Jean-Marc CHARPENTIER, Romain Jean-François GUERIT
  • Patent number: 11261743
    Abstract: A device for masking the inner periphery of a disc of a turbine engine generally includes a lower element, an upper element, and an elastic annular seal. The lower element, the upper element, and the elastic annular seal are coaxial, the elastic annular seal arranged longitudinally between the lower element and the upper element. The seal generally includes a lower annular part bearing radially and internally against the lower element, and an upper annular part bearing radially and internally against the upper element. The lower part and the upper part are connected to one another by an annular central part forming a return element. The elastic annular seal is configured to bear longitudinally, radially, and externally against each longitudinal end of said inner periphery of the disc to mask said inner periphery, and a clamping system capable of clamping the seal between the lower element and the upper element.
    Type: Grant
    Filed: April 11, 2019
    Date of Patent: March 1, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Léon Jean-Baptiste Besnard, Romain Jean-François Guerit, Laurent Miguel Sanchez
  • Publication number: 20190316476
    Abstract: A device for masking the inner periphery of a disc of a turbine engine generally includes a lower element, an upper element, and an elastic annular seal. The lower element, the upper element, and the elastic annular seal are coaxial, the elastic annular seal arranged longitudinally between the lower element and the upper element. The seal generally includes a lower annular part bearing radially and internally against the lower element, and an upper annular part bearing radially and internally against the upper element. The lower part and the upper part are connected to one another by an annular central part forming a return element. The elastic annular seal is configured to bear longitudinally, radially, and externally against each longitudinal end of said inner periphery of the disc to mask said inner periphery, and a clamping system capable of clamping the seal between the lower element and the upper element.
    Type: Application
    Filed: April 11, 2019
    Publication date: October 17, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Léon Jean-Baptiste Besnard, Romain Jean-François Guerit, Laurent Miguel Sanchez