Patents by Inventor Sebastien Serge Francis CONGRATEL

Sebastien Serge Francis CONGRATEL 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: 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
  • Patent number: 10858958
    Abstract: A turbine ring assembly includes a plurality of ring sectors of ceramic matrix composite material forming a turbine ring and a ring support structure secured to a turbine casing and having two annular flanges, each ring sector having two tabs held between the two annular flanges. The ring support structure includes an annular retention band mounted on the turbine casing, the annular retention band including an annular web forming one of the flanges. The two annular flanges exert stress on the tabs of the ring sectors. One of the flanges is elastically deformable in the axial direction of the turbine ring. The band has a first series of teeth distributed circumferentially on the band and the turbine casing has a second series of teeth distributed circumferentially on the casing, and the teeth of the first series and the teeth of the second series together provide circumferential jaw coupling.
    Type: Grant
    Filed: May 18, 2016
    Date of Patent: December 8, 2020
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Lucien Henri Jacques Quennehen, Sebastien Serge Francis Congratel
  • Publication number: 20200370438
    Abstract: A turbomachine vane includes a blading made of composite material with fibrous reinforcement densified by a matrix and an integrated metal leading edge, the blading extending in a longitudinal direction, the leading edge being formed by a metal foil overmolded onto the blading, the foil having a lower wing and an upper wing which extend respectively on the lower and upper faces of the blading while matching an aerodynamic profile of the vane. One of the lower wing and the upper wing has a positioning portion extending in the longitudinal direction, the portion having a flat inner face and an increasing thickness away from the leading edge, and being housed in a correspondingly shaped groove in the blading.
    Type: Application
    Filed: May 20, 2020
    Publication date: November 26, 2020
    Inventors: Sébastien Serge Francis CONGRATEL, Célia IGLESIAS CANO, Antoine Hubert Marie Jean MASSON
  • 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: 10787924
    Abstract: A turbine ring assembly including both a plurality of ring sectors together forming a turbine ring and also a ring support structure including an upstream annular flange and a downstream annular flange, each ring sector having a first horizontal sealing tongue, an upstream vertical sealing tongue, and a first downstream vertical sealing tongue. Each ring sector also includes a second horizontal sealing tongue over the first horizontal sealing tongue in the radial direction of the ring. A first angled sealing element is housed both in a vertical groove present in the upstream tab and in a second horizontal groove, and a second angled sealing element is received both in a first horizontal groove and in a first vertical groove present in the downstream tab.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: September 29, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Sebastien Serge Francis Congratel, Clement Jean Pierre Duffau, Matthieu Simon
  • Patent number: 10767491
    Abstract: A turbine blade including a root bearing an aerofoil extending in a direction of span and ending in a tip, this aerofoil including a leading edge and a trailing edge which are connected by a pressure face wall and a suction face wall, the trailing edge including on the pressure face side cooling slots. The trailing edge includes one or more first slots close to the root, which are supplied via a lower cavity; one or more last slots near the tip which are supplied via an upper cavity; intermediate slots situated between the first slots and the last slots supplied with air via a downstream line set; and wherein the lower cavities and upper cavities and the downstream line set are supplied distinctly at the level of the root.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: September 8, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrice Eneau, Sebastien Serge Francis Congratel, Charlotte Marie Dujol, Philippe Picot
  • 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
  • Patent number: 10690007
    Abstract: A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and also a ring support structure having two annular flanges, each ring sector having two tabs held respectively between the two annular flanges of the ring support structure. The two annular flanges of the ring support structure exert stress on the tabs of the ring sectors. One of the flanges of the ring support structure is elastically deformable in the axial direction of the turbine ring. The turbine ring assembly further includes a plurality of pegs engaged both in the annular flanges of the ring support structure and in the tabs of the ring sectors facing the annular flanges.
    Type: Grant
    Filed: May 12, 2016
    Date of Patent: June 23, 2020
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Lucien Henri Jacques Quennehen, Sebastien Serge Francis Congratel
  • 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: 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
  • Publication number: 20190376394
    Abstract: A turbine blade of a turbine engine such as a turbojet engine, comprising: a root supporting a blade and extending in a wingspan direction, ending in a vertex, the blade comprising a leading edge and a trailing edge, with a pressure side wall and a suction side wall separated from one another and connecting the leading edge (17) to the trailing edge, the blade also comprising: cooling ducts in which air collected at the blade root circulates; first and second inner side recesses running along the pressure side wall in order to form a heat shield spaced apart from one another along the pressure side wall; and at least one duct extending from the pressure side wall to the suction side wall between the first and second side recesses.
    Type: Application
    Filed: October 18, 2017
    Publication date: December 12, 2019
    Inventors: Charlotte Marie DUJOL, Sébastien Serge Francis CONGRATEL, Patrice ENEAU, Léandre OSTINO, Michel SLUSARZ
  • 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
  • Publication number: 20190292918
    Abstract: A turbine vane of a turbine engine such as a turboprop or a turbojet, the vane comprising a root supporting a blade, the vane including at least one air-circulation duct for cooling the air during operation, the duct including, at the vane root, an inlet portion for collecting the cooling air, the inlet portion extending away from a lower surface of the vane root opposite the blade. At least one inlet portion is provided with a helical element for rotating the cooling air in order to improve the cooling efficiency thereof.
    Type: Application
    Filed: May 31, 2017
    Publication date: September 26, 2019
    Inventors: Erwan Daniel BOTREL, Sébastien Serge Francis CONGRATEL, Simon PARINET
  • 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