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).

  • Patent number: 12281578
    Abstract: Turbine shroud assembly comprising sections (10) made from CMC and forming a shroud (1) and a support structure (3), each section having a base (12) with a radially internal face (12a) and a radially external face (12b), from which there extend in a projecting manner an upstream attachment lug (14) and a downstream attachment lug (16), the support structure comprising a collar (31), from which there radially extend in a projecting manner towards the shroud an upstream radial flange (32) and a downstream radial flange (36), by which the lugs of each section of the shroud are retained, the shroud (1) being retained by axial pins (119, 120) which cooperate, on the one hand, with the upstream radial flange, via first and second annular end plates (33, 34), and directly with the downstream radial flange and, on the other hand, with the upstream and downstream attachment lugs, respectively.
    Type: Grant
    Filed: March 22, 2021
    Date of Patent: April 22, 2025
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Jarrossay, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Aurélien Gaillard, Nicolas Paul Tableau
  • Patent number: 12203484
    Abstract: The invention relates to a fan blade (3) of a turbomachine (15) comprising a structure (4) made of composite material having, within the root (5) and/or the stilt (6) of the blade, a first layer (11) comprising the lower face (16) and having a first thickness (E1) of between 10% and 25% of the total thickness (E), a second layer (12) comprising the suction face (17) and having a second thickness (E2) of between 10% and 25% of the total thickness (E), and a central layer (13) extending between the first layer (11) and the second layer (12), the shortening of the warp strands (9) in the first and second layers (11, 12) being greater than the shortening of the warp strands (9) in the central layer (13).
    Type: Grant
    Filed: May 25, 2022
    Date of Patent: January 21, 2025
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Pascal Jean-Charles Gondre, Nicolas Paul Tableau, Julien Paul Schneider-Die-Gross
  • Patent number: 12158079
    Abstract: A turbine ring assembly extending about an axis, includes a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure held by a turbine casing, each ring sector including a base from which an upstream lug and a downstream lug spaced axially from each other extend radially outwardly, the ring support structure including a spacer having a clamp against which the downstream lug of the ring sectors is held, a first upstream flange against which the upstream lug of the ring sectors is held, and upstream of the first upstream flange, a second upstream flange for absorbing forces against which the first upstream flange is held.
    Type: Grant
    Filed: April 3, 2020
    Date of Patent: December 3, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Clément Jarrossay, Nicolas Paul Tableau
  • Publication number: 20240376902
    Abstract: The invention relates to a fan blade (3) of a turbomachine (15) comprising a structure (4) made of composite material having, within the root (5) and/or the stilt (6) of the blade, a first layer (11) comprising the lower face (16) and having a first thickness (E1) of between 10% and 25% of the total thickness (E), a second layer (12) comprising the suction face (17) and having a second thickness (E2) of between 10% and 25% of the total thickness (E), and a central layer (13) extending between the first layer (11) and the second layer (12), the shortening of the warp strands (9) in the first and second layers (11, 12) being greater than the shortening of the warp strands (9) in the central layer (13).
    Type: Application
    Filed: May 25, 2022
    Publication date: November 14, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Pascal Jean-Charles GONDRE, Nicolas Paul TABLEAU, Julien Paul SCHNEIDER-DIE-GROSS
  • Patent number: 12123320
    Abstract: A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.
    Type: Grant
    Filed: January 14, 2021
    Date of Patent: October 22, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Aurelien Gaillard, Sebastien Serge Francis Congratel, Clement Jarrossay, Pascal Cedric Tabarin, Nicolas Paul Tableau
  • Patent number: 12055060
    Abstract: A turbine ring assembly extending around a longitudinal axis and comprises: a plurality of ring angular sectors made of CMC material circumferentially arranged in such a way as to form a turbine ring, each sector comprising a base from which an upstream leg and a downstream leg extend radially, a ring support structure comprising: a spacer extending around the sectors and comprising a downstream flange in such a way that the downstream leg of each sector is held against the downstream flange, a upstream force-absorbing plate extending circumferentially around the longitudinal axis in such a way as to be in contact with the upstream leg of each sector and fixed to an upstream area of the spacer which extends in extension of the upstream leg.
    Type: Grant
    Filed: November 4, 2021
    Date of Patent: August 6, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Emile André Cazin, Pascal Cédric Tabarin, Sébastien Serge Francis Congratel, Nicolas Paul Tableau
  • Patent number: 12055459
    Abstract: Method for monitoring a turbomachine comprising a stator and a rotor, device, system, aircraft and computer program product. The method comprises a step of acquiring an input signal which represents a deformation of the stator or rotor of the turbomachine. The input signal has been acquired by a deformation gauge which is attached to the stator or rotor. The input signal comprises a first component which represents deformations of the stator or rotor which are caused by rotation of the rotor vanes in relation to the stator, and a second component which represents deformations which are caused by different elements of the rotor vanes. The method comprises a step of re-sampling the input signal in order to obtain a re-sampled input signal comprising a predefined whole number of samples per revolution of the turbomachine rotor.
    Type: Grant
    Filed: December 4, 2020
    Date of Patent: August 6, 2024
    Assignees: SAFRAN, SAFRAN AIRCRAFT ENGINES
    Inventors: Dany Abboud, Mohammed El Badaoui, Nicolas Paul Tableau
  • Patent number: 12031455
    Abstract: Turbine comprising a casing and a nozzle including a metal outer shroud integral with the casing, a metal inner shroud, and a plurality of nozzle sectors of CMC forming a ring extending between the metal outer shroud and the metal inner shroud, each sector including a mast, an inner platform, an outer platform and at least one airfoil having a hollow profile defining an inner recess, each of the inner and outer platforms having an opening communicating with said inner recess, and the mast passing through said openings and the inner recess and being attached to said casing and connected with said nozzle sector. The mast comprises at least one fastening projection having at least one portion extending from a radially outer end of the mast in a direction opposite to the center of the mast and in a plane orthogonal to the radial direction.
    Type: Grant
    Filed: June 1, 2020
    Date of Patent: July 9, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Aurélien Gaillard, Antoine Claude Michel Etienne Danis, Clément Jarrossay, Gilles Gérard Claude Lepretre, Nicolas Paul Tableau
  • Patent number: 11965433
    Abstract: A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.
    Type: Grant
    Filed: April 28, 2021
    Date of Patent: April 23, 2024
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Antoine Claude Michel Etienne Danis, Clément Jarrossay, Lucien Henri Jacques Quennehen, Nicolas Paul Tableau, Matthieu Arnaud Gimat
  • Patent number: 11879342
    Abstract: A turbine assembly (1) comprising: —a plurality of turbine ring sectors (20) made of ceramic-matrix composite material, —a ring support structure (3), comprising an annular shroud (6), and in addition —a plurality of angular spacer sectors (70) together forming an annular spacer (7), said annular spacer (7) being, on the one hand, fixed to the turbine ring (2) and, on the other hand, fixed to said annular shroud (6), characterized in that said turbine assembly (1) comprises at least one air diffuser (8), which is configured to diffuse cooling air onto the radially outer face (212) of at least one of said turbine ring sectors (20), and in that said at least one air diffuser (8) is mounted by being nested on one of said angular spacer sectors (70), in a nested position.
    Type: Grant
    Filed: March 19, 2021
    Date of Patent: January 23, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Aurélien Gaillard, Clément Emile André Cazin, Clément Jarrossay, Pascal Cédric Tabarin, Nicolas Paul Tableau
  • Publication number: 20240003267
    Abstract: A turbine ring assembly extending around a longitudinal axis and comprises: a plurality of ring angular sectors made of CMC material circumferentially arranged in such a way as to form a turbine ring, each sector comprising a base from which an upstream leg and a downstream leg extend radially, a ring support structure comprising: a spacer extending around the sectors and comprising a downstream flange in such a way that the downstream leg of each sector is held against the downstream flange, a upstream force-absorbing plate extending circumferentially around the longitudinal axis in such a way as to be in contact with the upstream leg of each sector and fixed to an upstream area of the spacer which extends in extension of the upstream leg.
    Type: Application
    Filed: November 4, 2021
    Publication date: January 4, 2024
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Emile André CAZIN, Pascal Cédric TABARIN, Sébastien Serge Francis CONGRATEL, Nicolas Paul TABLEAU
  • Patent number: 11814990
    Abstract: A turbine comprises a casing, an outer metal shroud, an inner metal shroud and an annular distributor having a plurality of CMC ring sectors, each sector comprising a mast, an inner platform, an outer platform and at least one blade having a hollow profile that defines an inner housing, the inner and outer platforms each having an opening communicating with said inner housing, and the mast passing through said openings and the inner housing and being secured to said casing and connected to said annular sector. Each blade comprises at least one first radial shoulder projecting axially towards the inside of the blade, and each mast comprises at least one second shoulder projecting axially towards the outside of the mast configured to radially cooperate with a first shoulder and radially press the blade against the mast.
    Type: Grant
    Filed: October 28, 2020
    Date of Patent: November 14, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Paul Tableau, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Matthieu Arnaud Gimat, Gilles Gérard Claude Lepretre
  • Patent number: 11795838
    Abstract: A device for cooling a turbine shroud comprising at least one annular flange configured to be attached to an annular radial collar of a shroud support structure being arranged upstream, with respect to a circulation direction of an air flow, of the turbine shroud, and comprising at least one cooling air circulation channel, a diffuser configured to be attached to said annular radial collar downstream of the annular flange and comprising at least one intake channel in fluid communication with the circulation channel of the annular flange, and comprising an injection cavity comprising a plurality of injection holes and being configured to inject on a radially external face of the shroud, via the injection holes, the cooling air originating in the intake channel, and a particle filter arranged on an inlet section of the circulation channel of the annular flange, the particle filter comprising a plurality of openings.
    Type: Grant
    Filed: June 25, 2020
    Date of Patent: October 24, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Jarrossay, Antoine Claude Michel Etienne Danis, Lucien Henri Jacques Quennehen, Nicolas Paul Tableau, Sébastien Serge Francis Congratel
  • Publication number: 20230212952
    Abstract: A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.
    Type: Application
    Filed: April 28, 2021
    Publication date: July 6, 2023
    Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Antoine Claude Michel Etienne DANIS, Clément JARROSSAY, Lucien Henri Jacques QUENNEHEN, Nicolas Paul TABLEAU, Matthieu Arnaud GIMAT
  • Publication number: 20230142040
    Abstract: A turbine assembly (1) comprising: —a plurality of turbine ring sectors (20) made of ceramic-matrix composite material, —a ring support structure (3), comprising an annular shroud (6), and in addition ?a plurality of angular spacer sectors (70) together forming an annular spacer (7), said annular spacer (7) being, on the one hand, fixed to the turbine ring (2) and, on the other hand, fixed to said annular shroud (6), characterized in that said turbine assembly (1) comprises at least one air diffuser (8), which is configured to diffuse cooling air onto the radially outer face (212) of at least one of said turbine ring sectors (20), and in that said at least one air diffuser (8) is mounted by being nested on one of said angular spacer sectors (70), in a nested position.
    Type: Application
    Filed: March 19, 2021
    Publication date: May 11, 2023
    Applicant: Safran Aircraft Engines
    Inventors: Aurélien GAILLARD, Clément Emile André CAZIN, Clément JARROSSAY, Pascal Cédric TABARIN, Nicolas Paul TABLEAU
  • Publication number: 20230116425
    Abstract: Turbine shroud assembly comprising sections (10) made from CMC and forming a shroud (1) and a support structure (3), each section having a base (12) with a radially internal face (12a) and a radially external face (12b), from which there extend in a projecting manner an upstream attachment lug (14) and a downstream attachment lug (16), the support structure comprising a collar (31), from which there radially extend in a projecting manner towards the shroud an upstream radial flange (32) and a downstream radial flange (36), by which the lugs of each section of the shroud are retained, the shroud (1) being retained by axial pins (119, 120) which cooperate, on the one hand, with the upstream radial flange, via first and second annular end plates (33, 34), and directly with the downstream radial flange and, on the other hand, with the upstream and downstream attachment lugs, respectively.
    Type: Application
    Filed: March 22, 2021
    Publication date: April 13, 2023
    Applicant: Safran Aircraft Engines
    Inventors: Clément JARROSSAY, Sébastien Serge Francis CONGRATEL, Antoine Claude Michel Etienne DANIS, Aurélien GAILLARD, Nicolas Paul TABLEAU
  • Patent number: 11585241
    Abstract: An assembly for a turbomachine turbine includes at least one ring sector made of CMC material and a support casing including an upstream flange and a downstream flange between which each ring sector is disposed, each ring sector including a base that has a radially external face from which radially extend two lugs, the lugs of each ring sector being retained between the two flanges of the support casing by axial pins each engaged in one of the flanges of the ring support casing and in the lug of the ring sector facing said flange, the assembly further including, for each ring sector, at least one radial retaining pin screwed into the support casing and coming to radially bear against a lug of the at least one ring sector to retain it in position, and anti-rotation system for rotationally locking the radial retaining pin.
    Type: Grant
    Filed: September 24, 2019
    Date of Patent: February 21, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Claude Michel Etienne Danis, Clément Jarrossay, Lucien Henri Jacques Quennehen, Nicolas Paul Tableau, Hubert Jean-Yves Illand
  • Publication number: 20230051167
    Abstract: A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.
    Type: Application
    Filed: January 14, 2021
    Publication date: February 16, 2023
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Aurelien GAILLARD, Sebastien Serge Francis CONGRATEL, Clement JARROSSAY, Pascal Cedric TABARIN, Nicolas Paul TABLEAU
  • Publication number: 20230016039
    Abstract: Method for monitoring a turbomachine comprising a stator and a rotor, device, system, aircraft and computer program product. The method comprises a step of acquiring an input signal which represents a deformation of the stator or rotor of the turbomachine. The input signal has been acquired by a deformation gauge which is attached to the stator or rotor. The input signal comprises a first component which represents deformations of the stator or rotor which are caused by rotation of the rotor vanes in relation to the stator, and a second component which represents deformations which are caused by different elements of the rotor vanes. The method comprises a step of re-sampling the input signal in order to obtain a re-sampled input signal comprising a predefined whole number of samples per revolution of the turbomachine rotor.
    Type: Application
    Filed: December 4, 2020
    Publication date: January 19, 2023
    Applicants: SAFRAN, SAFRAN AIRCRAFT ENGINES
    Inventors: Dany ABBOUD, Mohammed EL BADAOUI, Nicolas Paul TABLEAU
  • Patent number: 11542827
    Abstract: A method for assembling/disassembling a turbine ring assembly including a turbine ring of ceramic matrix composite material and a ring support structure of metal equipped with a central shroud and with at least one single-piece annular plate positioned upstream of the ring with respect to the direction of an air flow passing through the assembly, the plate having in the radial direction a first free end and a second end opposite to the first end, the second end being removably attached to the first radial flange and shrink-fit to the central shroud, is disclosed. The method for assembling/disassembling includes, before the assembling/disassembling of the plate, a step of deformation of the central shroud and/or of the at least one annular plate.
    Type: Grant
    Filed: January 8, 2020
    Date of Patent: January 3, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques Quennehen, Antoine Claude Michel Etienne Danis, Hubert Jean-Yves Illand, Clément Jarrossay, Nicolas Paul Tableau