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).

  • 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
  • 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
  • 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: 20190040758
    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: Application
    Filed: October 4, 2016
    Publication date: February 7, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques QUENNEHEN, Sebastien Serge Francis CONGRATEL, Clement Jean Pierre DUFFAU, Matthieu SIMON
  • Patent number: 10125615
    Abstract: A turbine wheel for a turbine engine comprising a disc carrying blades. Each blade comprises an upstream radial wall and a downstream radial wall which extend inwards from the platform of the blade. Inter-blade cavities each accommodate one inter-blade sealing and vibration damping member. According to the invention, each inter-blade sealing and vibration damping member comprises at least a first transverse partition wall axially arranged at a distance from a downstream (or upstream, respectively) portion of the member and axially opposite two upstream (or downstream, respectively) so as to obstruct a flow of incoming air into the cavity between two adjacent upstream radial walls or two adjacent downstream radial walls.
    Type: Grant
    Filed: November 3, 2015
    Date of Patent: November 13, 2018
    Assignee: SNECMA
    Inventors: Sébastien Serge Francis Congratel, Franck Boisnault, Patrice Jean-Marc Rosset
  • Publication number: 20180306035
    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: Application
    Filed: October 4, 2016
    Publication date: October 25, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrice ENEAU, Sebastien Serge Francis CONGRATEL, Charlotte Marie DUJOL, Philippe PICOT
  • 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: 20180156069
    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: Application
    Filed: May 12, 2016
    Publication date: June 7, 2018
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Lucien Henri Jacques QUENNEHEN, Sebastien Serge Francis CONGRATEL
  • Publication number: 20180142572
    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: Application
    Filed: May 18, 2016
    Publication date: May 24, 2018
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Lucien Henri Jacques QUENNEHEN, Sebastien Serge Francis CONGRATEL
  • Patent number: 9951625
    Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades each having a platform, carrying an impeller connected by a stilt to a root. Each blade comprises an upstream radial wall and a downstream radial wall extending inwards from the platform of the blade. The roots of the blades are engaged into slots on the periphery of the disk, so that the radial walls of the blades and the platforms of the blades are circumferentially arranged end-to-end, and define inter-blade cavities radially inside the platforms, each accommodating an inter-blade sealing and vibration damping member. At least one member comprises an elastically deformable element configured so as to be elastically prestressed against the walls of a cavity in the member mounting position.
    Type: Grant
    Filed: November 3, 2015
    Date of Patent: April 24, 2018
    Assignee: SNECMA
    Inventors: Sébastien Serge Francis Congratel, Maurice Guy Judet
  • 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
  • Publication number: 20180087399
    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: September 27, 2017
    Publication date: March 29, 2018
    Inventors: Lucien Henri Jacques QUENNEHEN, Sébastien Serge Francis CONGRATEL, Clément Jean Pierre DUFFAU, Nicolas Paul TABLEAU
  • Publication number: 20180087401
    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: 20180051581
    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: Application
    Filed: August 18, 2017
    Publication date: February 22, 2018
    Inventors: Lucien Henri Jacques QUENNEHEN, Sébastien Serge Francis CONGRATEL, Clément Jean Pierre DUFFAU, Nicolas Paul TABLEAU
  • Publication number: 20180051591
    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: Application
    Filed: August 18, 2017
    Publication date: February 22, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques QUENNEHEN, Sébastien Serge Francis CONGRATEL, Clément Jean Pierre DUFFAU, Nicolas Paul TABLEAU
  • Publication number: 20180051590
    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: Application
    Filed: August 18, 2017
    Publication date: February 22, 2018
    Applicant: Safran Aircraft Engines
    Inventors: Nicolas Paul TABLEAU, Sébastien Serge Francis CONGRATEL, Clément Jean Pierre DUFFAU, Lucien Henri Jacques QUENNEHEN
  • Patent number: 9833834
    Abstract: A blade preform includes a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream and downstream webs connect the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root. The blade root extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs and the side edges of each web are extended by walls that converge at the flanks of the blade root.
    Type: Grant
    Filed: June 4, 2014
    Date of Patent: December 5, 2017
    Assignee: SNECMA
    Inventors: Sébastien Serge Francis Congratel, Raphaël Jean Philippe Dupeyre, Guillaume Klein, David Mathieu, Ba-Phuc Tang
  • Publication number: 20160129497
    Abstract: The invention relates to a blade preform (46) including a strut connecting a plat-form (16) to a blade root portion (14) extending longitudinally in an upstream-downstream direction, an upstream web (26) and a downstream (28) web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream (26) and downstream (28) webs connect the upstream and downstream ends of the plat-form (16) to the upstream and downstream ends of the blade root (14). According to the invention, the blade root (14) extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs (26, 28) and the side edges (40) of each web (26, 28) are extended by walls that converge (44) at the flanks of the blade root.
    Type: Application
    Filed: June 4, 2014
    Publication date: May 12, 2016
    Applicant: Snecma
    Inventors: Sébastien Serge Francis Congratel, Raphaël Jean Philippe Dupeyre, Guillaume Klein, David Mathieu, Ba-Phuc Tang