Patents by Inventor Antoine Claude Michel Etienne Danis

Antoine Claude Michel Etienne Danis 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).

  • Publication number: 20210108525
    Abstract: A turbine of a turbo engine includes a casing and a nozzle stage including an outer metal shroud secured to the casing, an inner metal shroud, and a plurality of ring sectors made of ceramic-matrix composite material each having an internal platform, an external platform and at least one blade extending between the external platform and the internal platform and secured thereto. The internal platform of each sector includes a first and a second tab protruding radially inwardly from respectively an upstream end and a downstream end of the internal platform, and the inner shroud includes a shoulder protruding radially outwardly and being in abutment upstream against the first tab, and a clamp downstream of the shoulder including two jaws extending radially outwardly and held under stress towards each other against the second tab.
    Type: Application
    Filed: April 15, 2019
    Publication date: April 15, 2021
    Inventors: Clément JARROSSAY, Sébastien Serge Francis CONGRATEL, Antoine Claude Michel Etienne DANIS, Clément Jean Pierre DUFFAU, Lucien Henri Jacques QUENNEHEN
  • Patent number: 10934872
    Abstract: A support case for a turbomachine ring sector includes an annular body around a longitudinal axis of the case, and a downstream edge for attachment of the ring sector. The downstream edge extends from the body radially towards the inside of the case. The downstream edge extends circumferentially along a junction region between the body and a fixed vanes stage. The junction region includes a central portion and two lateral portions located on each side of the central portion, along a circumferential direction of the case with respect to its longitudinal axis. The central portion projects radially outwards from the case with respect to the lateral portions.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: March 2, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Paul Tableau, Sebastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Maurice Guy Judet, Lucien Henri Jacques Quennehen
  • Publication number: 20200355088
    Abstract: A turbine ring assembly includes ring sectors forming a turbine ring and a ring support structure, each sector having, along a cutting plane defined by an axial direction and a radial direction of the ring, a portion forming an annular base with, in the radial direction, an inner face and an outer face from which a first and a second lug protrude, the structure including a shroud from which protrude a first and a second radial clamp from which the first and second lugs are held. The turbine ring includes an annular flange having a first portion bearing against the first lug, and a second portion removably fixed to the first radial clamp, the first portion including radial slits open on a free end of the annular flange and delimiting first-portion sectors.
    Type: Application
    Filed: December 24, 2018
    Publication date: November 12, 2020
    Inventors: Nicolas Paul TABLEAU, Sébastien Serge Francis CONGRATEL, Antoine Claude Michel Etienne DANIS, Clément Jean Pierre DUFFAU, Clément JARROSSAY
  • Publication number: 20190128132
    Abstract: A support case for a turbomachine ring sector includes an annular body around a longitudinal axis of the case, and a downstream edge for attachment of the ring sector. The downstream edge extends from the body radially towards the inside of the case. The downstream edge extends circumferentially along a junction region between the body and a fixed vanes stage. The junction region includes a central portion and two lateral portions located on each side of the central portion, along a circumferential direction of the case with respect to its longitudinal axis. The central portion projects radially outwards from the case with respect to the lateral portions.
    Type: Application
    Filed: October 22, 2018
    Publication date: May 2, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Paul TABLEAU, Sebastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Maurice Guy Judet, Lucien Henri Jacques Quennehen
  • Publication number: 20190063244
    Abstract: A sector of a sectorized annular nozzle of a turbine of a turbomachine comprises an outer platform having an outer wall connected to a coaxial inner wall via at least one straightening fixed blade. The outer platform includes hooking means that hook the outer platform to a turbine fixed casing. The outer platform includes an outer circular shell, axially offset with respect to the outer wall and integrally formed with the outer wall, and the outer shell is intended to surround an angular portion of a rotor wheel. The hooking means includes an upstream circular edge and a downstream circular edge extending axially, said upstream and downstream edges being respectively configured to attach to an upstream hook and a downstream hook of said turbine casing, and said upstream and downstream edges being oriented in the downstream direction.
    Type: Application
    Filed: August 23, 2018
    Publication date: February 28, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Clément Jarrossay, Nicolas Paul Tableau