Patents by Inventor Nicolas Paul TABLEAU

Nicolas Paul TABLEAU 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: 20210115806
    Abstract: A turbine ring assembly includes ring sectors forming a turbine ring and a ring support structure, each ring sector having, along a section 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 attachment tabs protrude, the structure including a central shroud from which a first and a second radial clamps protrude between which the attachment tabs of each ring sector are maintained. The turbine ring assembly includes a first and a second annular flanges removably fastened to the first radial clamp, the second annular flange including a bearing shroud protruding upstream in the axial direction and having a radial bearing in contact with the central shroud.
    Type: Application
    Filed: March 13, 2018
    Publication date: April 22, 2021
    Inventors: Nicolas Paul TABLEAU, Sébastien Serge Francis CONGRATEL, Clément Jean Pierre DUFFAU, Fabrice Marcel Noël GARIN, 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: 20210054757
    Abstract: A turbine ring assembly including ring sections forming a turbine ring and a ring support structure, each ring section having, along a section plane defined by an axial direction and a radial direction of the ring, a part forming an annular base with, in the radial direction, an inner face and an outer face, from which a first and a second fastening lug project, the structure including a central shroud, from which a first and a second radial clamp project, between which the fastening lugs of each ring section are maintained. It includes a first and a second annular flange detachably fixed to the first radial clamp, the second annular flange including a support shroud projecting upstream in the axial direction and having a radial support in contact with the central shroud.
    Type: Application
    Filed: March 13, 2018
    Publication date: February 25, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Paul TABLEAU, Sebastien Serge Francis CONGRATEL, Clement Jean Pierre DUFFAU, Fabrice Marcel Noel GARIN, 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
  • Patent number: 10738635
    Abstract: A turbine for a turbine engine is disclosed. The turbine includes a casing and a turbine nozzle stage made of a ceramic matrix composite material and including annular sectors forming a ring presenting an inner shroud and an outer shroud. Each annular sector has an inner platform forming part the inner shroud and an outer platform forming part of the outer shroud, and an airfoil extending between the outer platform and the inner platform and secured thereto. The airfoil presents a hollow profile defining an inside housing extending between the inner platform and the outer platform, and the inner and outer platforms each presenting an orifice communicating with the inside housing of the airfoil. Each annular sector includes a strut passing through the orifices in the platforms and through the inside housing of the airfoil. The strut is fastened to the casing and is connected with the annular sector.
    Type: Grant
    Filed: January 18, 2018
    Date of Patent: August 11, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sebastien Serge Francis Congratel, Nicolas Paul Tableau, Matthieu Arnaud Gimat, Clement Marie Benoit Roussille
  • Publication number: 20200131938
    Abstract: A turbine ring assembly including ring sectors forming a turbine ring and a ring support structure, each ring sector having, along a section 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 defining the inner face of the ring and an outer face from which a first and a second attachment tabs protrude, the structure including a central shroud from which a first and a second radial clamps protrude between which the first and second attachment tabs of each ring sector are maintained. It includes a first and a second annular flanges removably fastened to the first radial clamp of the central shroud and separated from each other by a contact abutment.
    Type: Application
    Filed: March 13, 2018
    Publication date: April 30, 2020
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Paul TABLEAU, Sebastien Serge Francis CONGRATEL, Clement Jean Pierre DUFFAU, Hubert Jean-Yves ILLAND, Lucien Henri Jacques QUENNEHEN
  • Patent number: 10619517
    Abstract: A turbine ring assembly includes ring sectors made of ceramic matrix composite forming a ring and a ring support structure. Each sector includes an annular base with, in a radial direction, an inside face and an outside face from which extend two attachment tabs held between two radial tabs of the structure. The assembly also includes, for each sector, at least two pins cooperating with one of the attachment tabs and the corresponding radial tab, and at least one pin cooperating with the other attachment tab and the corresponding radial tab. The first radial tab includes a first annular radial portion integral to the structure, and a removable second annular radial portion extending radially toward the center of the ring over a greater portion than said first radial annular portion, the portion extending beyond the first annular radial portion including orifices for receiving one of the pins.
    Type: Grant
    Filed: August 18, 2017
    Date of Patent: April 14, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Nicolas Paul Tableau
  • Patent number: 10605120
    Abstract: A turbine ring assembly comprises a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure including first and second annular flanges. In section, each ring sector presents a K-shape having an annular base-forming portion with an inside face defining the inside face of the turbine ring and an outside face with first and second S-shaped tabs projecting therefrom. The inside faces of the first and second tabs of each ring sector rest on holder elements secured to the first and second annular flanges, while the outside faces of the first and second tabs are in contact with clamping elements secured to the ring support structure.
    Type: Grant
    Filed: September 26, 2017
    Date of Patent: March 31, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sebastien Serge Francis Congratel, Clement Jean Pierre Duffau, Nicolas Paul Tableau
  • Patent number: 10598045
    Abstract: A turbine ring assembly includes ring sectors forming a turbine ring and a ring support structure, each ring sector having, in a section plane defined by an axial direction and a radial direction of the turbine ring, a portion forming an annular base with, in the radial direction, an inside face defining the inside face of the turbine ring and an outside face from which a first and a second attachment tab protrude, the ring support structure having a central annulus from which a first and a second radial tab protrude, between which the first and second attachment tabs of each ring sector are held. The first radial tab comprises a one-piece annular flange that is fastened in a removable manner to the central annulus of the ring support structure.
    Type: Grant
    Filed: August 18, 2017
    Date of Patent: March 24, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Nicolas Paul Tableau, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Lucien Henri Jacques Quennehen
  • Publication number: 20200040748
    Abstract: The invention relates to an assembly comprising a turbomachine casing (7) and a nozzle made of ceramic matrix composite material having a blade (21), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part (31) of the nozzle to the casing (7), said connecting part (31) extending substantially radially outwards, the blade (21) and said connecting part (31) being formed in one piece, said assembly being characterized in that the connecting part (31) is fastened to a first radial wall (51) integral with the casing (7) by fastening means (53).
    Type: Application
    Filed: July 31, 2019
    Publication date: February 6, 2020
    Inventors: Matthieu Arnaud GIMAT, Lucien Henri Jacques QUENNEHEN, Gilles Gérard Claude LEPRETRE, Nicolas Paul TABLEAU
  • Publication number: 20190383166
    Abstract: A turbine ring assembly including a ring support structure and a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring, each sector presenting in a first section plane defined by an axial direction and a radial direction of the ring a portion forming an annular base having, in the radial direction, an inner face and an outer face from which there extend two attachment tabs defining between them a circumferentially-open annular cavity, the structure including two radial tabs between which the attachment tabs are held, and at least one injection orifice for injecting a stream of cooling air into the annular cavity. In a second section plane containing the axial direction and a direction orthogonal to the first section plane, the orifice forms a first feed angle relative to the direction orthogonal to the first section plane, the first feed angle lying in the range ?80° to +80°.
    Type: Application
    Filed: January 5, 2018
    Publication date: December 19, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Clement Jean Pierre DUFFAU, Sebastien Serge Francis CONGRATEL, Lucien Henri Jacques QUENNEHEN, Nicolas Paul TABLEAU
  • Patent number: 10502082
    Abstract: A turbine ring assembly includes both a plurality of CMC ring sectors forming a turbine ring and a ring support structure, each ring sector having a portion forming an annular base that presents an outside face in the radial direction of the turbine ring, with first and second attachment tabs projecting therefrom in the radial direction, each attachment tab presenting an end that is free, each ring sector having third and fourth attachment tabs, each extending in the axial direction of the turbine ring between the free end of the first attachment tab and the free end of the second attachment tab. Each ring sector is fastened to the ring support structure by a bolt having a bolt head bearing against the ring support structure and a thread co-operating with tapping formed in a plate, the plate co-operating with the third and fourth attachment tabs.
    Type: Grant
    Filed: August 18, 2017
    Date of Patent: December 10, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Nicolas Paul Tableau
  • Patent number: 10428688
    Abstract: A turbine ring assembly includes a plurality of ring segments and a ring support structure, the ring assembly further including, for each ring segment, a cooling distribution element fixed to the ring support structure and positioned in a first cavity delimited between the turbine ring and the ring support structure.
    Type: Grant
    Filed: September 27, 2017
    Date of Patent: October 1, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Nicolas Paul Tableau
  • Patent number: 10415426
    Abstract: A turbine ring assembly includes a plurality of ring segments and a ring support structure, the ring assembly further including, for each ring segment, a cooling distribution element fixed to the ring support structure and positioned in a first cavity delimited between the turbine ring and the ring support structure.
    Type: Grant
    Filed: November 20, 2017
    Date of Patent: September 17, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Nicolas Paul Tableau
  • Patent number: 10415427
    Abstract: A turbine ring assembly includes a plurality of ring segments and a ring support structure, the ring assembly further including, for each ring segment, a cooling distribution element fixed to the ring support structure and positioned in a first cavity delimited between the turbine ring and the ring support structure.
    Type: Grant
    Filed: November 20, 2017
    Date of Patent: September 17, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Nicolas Paul Tableau
  • 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
  • Publication number: 20180202302
    Abstract: A turbine (1) for a turbine engine, the turbine comprising a casing (4) and a turbine nozzle stage (2), the nozzle stage (2) of the turbine (1) being made of a ceramic matrix composite material and comprising a plurality of annular sectors (20) forming a ring presenting an inner shroud (240) and an outer shroud (260), each annular sector (20) having both an inner platform (24) forming a portion of the inner shroud (240) and an outer platform (26) forming a portion of the outer shroud (260), and at least one airfoil (28) extending between the outer platform (26) and the inner platform (24) and secured thereto, said airfoil (28) presenting a hollow profile defining an inside housing (280) extending between the inner platform (24) and the outer platform (26), and each of the inner and outer platforms (26, 28) presenting an orifice (245, 265) communicating with said inside housing (280) of the airfoil (28).
    Type: Application
    Filed: January 18, 2018
    Publication date: July 19, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques QUENNEHEN, Sebastien Serge Francis CONGRATEL, Nicolas Paul TABLEAU, Matthieu Arnaud GIMAT, Clement Marie Benoit ROUSSILLE
  • Publication number: 20180087400
    Abstract: A turbine ring assembly includes a plurality of ring segments and a ring support structure, the ring assembly further including, for each ring segment, a cooling distribution element fixed to the ring support structure and positioned in a first cavity delimited between the turbine ring and the ring support structure.
    Type: Application
    Filed: November 20, 2017
    Publication date: March 29, 2018
    Inventors: Lucien Henri Jacques QUENNEHEN, Sébastien Serge Francis CONGRATEL, Clément Jean Pierre DUFFAU, Nicolas Paul TABLEAU
  • Publication number: 20180087405
    Abstract: A turbine ring assembly comprises a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure including first and second annular flanges. In section, each ring sector presents a K-shape having an annular base-forming portion with an inside face defining the inside face of the turbine ring and an outside face with first and second S-shaped tabs projecting therefrom. The inside faces of the first and second tabs of each ring sector rest on holder elements secured to the first and second annular flanges, while the outside faces of the first and second tabs are in contact with clamping elements secured to the ring support structure.
    Type: Application
    Filed: September 26, 2017
    Publication date: March 29, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques QUENNEHEN, Sebastien Serge Francis CONGRATEL, Clement Jean Pierre DUFFAU, Nicolas Paul TABLEAU