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).

  • 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: 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
  • Patent number: 11746668
    Abstract: The invention relates to a turbine assembly comprising: a plurality of ring sectors forming a ring; a support structure comprising a shroud from which there project radial flanges which serve to hold latching tabs of each ring sector; a stator positioned downstream of said ring and comprising a blade provided with a radially outer platform and extending axially opposite said ring; an annular space being defined between the ring, the support structure and the platform, this annular space having passing through it a leakage air current, the assembly comprising a hollow ring which occupies said annular space and which is shaped so as to collect, channel and expel said leakage air current, more specifically to channel and expel it into the radially inner region of said annular space.
    Type: Grant
    Filed: March 22, 2021
    Date of Patent: September 5, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Jarrossay, Clément Emile André Cazin, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Aurélien Gaillard
  • 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: 20230118738
    Abstract: The invention relates to a turbine assembly comprising: a plurality of ring sectors forming a ring; a support structure comprising a shroud from which there project radial flanges which serve to hold latching tabs of each ring sector; a stator positioned downstream of said ring and comprising a blade provided with a radially outer platform and extending axially opposite said ring; an annular space being defined between the ring, the support structure and the platform, this annular space having passing through it a leakage air current, the assembly comprising a hollow ring which occupies said annular space and which is shaped so as to collect, channel and expel said leakage air current, more specifically to channel and expel it into the radially inner region of said annular space.
    Type: Application
    Filed: March 22, 2021
    Publication date: April 20, 2023
    Applicant: Safran Aircraft Engines
    Inventors: Clément JARROSSAY, Clément Emile André CAZIN, Sébastien Serge Francis CONGRATEL, Antoine Claude Michel Etienne DANIS, Aurélien GAILLARD
  • 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
  • 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
  • Patent number: 11506085
    Abstract: A turbine shroud sector made of ceramic matrix composite, of longitudinal axis X and which includes a base with a radially internal face, a radially external face from which there extend upstream and downstream tabs for attachment to a shroud support structure. The base includes a first slot and a second slot, which is arranged radially on the outside of the first slot. The slots are formed in the lateral face. A first and a second sealing strip rest against a radially internal wall of the first and second slots. The first strip has the overall shape of an omega and the shroud sector exhibits a first clearance which is defined radially between a central part of the first strip and the radially internal wall of the first slot, and a second clearance which is defined radially between this central part and a radially external wall of the first slot.
    Type: Grant
    Filed: October 21, 2019
    Date of Patent: November 22, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clement Jarrossay, Sebastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Clement Jean Pierre Duffau, Nicolas Paul Tableau, Lucien Henri Jacques Quennehen
  • Publication number: 20220364475
    Abstract: Turbine (1) comprising a casing, an outer metal shroud (9), an inner metal shroud (5) and an annular distributor (2) having a plurality of CMC ring sectors (20), each sector comprising a mast (6), an inner platform (24), an outer platform (26) and at least one blade (28) having a hollow profile that defines an inner housing (280), the inner and outer platforms each having an opening (245, 265) communicating with said inner housing, and the mast (6) 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 (72) projecting axially towards the inside of the blade, and each mast comprises at least one second shoulder (71) projecting axially towards the outside of the mast (6) configured to radially cooperate with a first shoulder (72) and radially press the blade (28) against the mast (6).
    Type: Application
    Filed: October 28, 2020
    Publication date: November 17, 2022
    Applicant: 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: 11480064
    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: Grant
    Filed: April 15, 2019
    Date of Patent: October 25, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Jarrossay, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Lucien Henri Jacques Quennehen
  • Publication number: 20220316357
    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: Application
    Filed: June 25, 2020
    Publication date: October 6, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément JARROSSAY, Antoine Claude Michel Etienne DANIS, Lucien Henri Jacques QUENNEHEN, Nicolas Paul TABLEAU, Sébastien Serge Francis CONGRATEL
  • Patent number: 11441434
    Abstract: A turbine ring assembly including ring sectors forming a turbine ring and a ring support structure, each sector having, in a section plane defined by an axial direction and a radial direction of the ring, a first and a second attachment tabs extending in the radial direction, and the structure including a central shell ring from which extend as projections a first and a second radial flanges between which are retained the first and second attachment tabs of each sector. Each sector includes rectilinear seatings mounted on the faces of the first and second attachment tabs in contact, respectively, with the second annular flange and the annular ring-flange and including, along a tangent to the circumferential direction, a variable thickness in the axial direction with a minimum thickness at the first and second ends of the sector and a maximum thickness in a median portion of the rectilinear seating.
    Type: Grant
    Filed: December 10, 2019
    Date of Patent: September 13, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Claude Michel Etienne Danis, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Lucien Henri Jacques Quennehen, Nicolas Paul Tableau
  • Publication number: 20220228498
    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: Application
    Filed: June 1, 2020
    Publication date: July 21, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Aurélien GAILLARD, Antoine Claude Michel Etienne DANIS, Clément JARROSSAY, Gilles Gérard Claude LEPRETRE, Nicolas Paul TABLEAU
  • Patent number: 11391170
    Abstract: A turbine of a turbo engine including a casing and a turbine nozzle stage, the turbine 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 forming a crown extending between the outer metal shroud and the inner metal shroud and having an internal shroud and an external shroud, each ring sector having an internal platform forming a portion of the internal shroud, an external platform forming a portion of the external shroud, and at least one blade extending between the external platform and the internal platform and secured thereto. Each sector is fixed to the outer metal shroud using at least one assembly including a screw and a nut, the screw passing through the outer platform of the sector and the outer metal shroud.
    Type: Grant
    Filed: April 17, 2019
    Date of Patent: July 19, 2022
    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: 20220195894
    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: Application
    Filed: April 3, 2020
    Publication date: June 23, 2022
    Inventors: Lucien Henri Jacques QUENNEHEN, Antoine Claude Michel Etienne DANIS, Clément Jean Pierre DUFFAU, Clément JARROSSAY, Nicolas Paul TABLEAU
  • Publication number: 20220098994
    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: Application
    Filed: January 8, 2020
    Publication date: March 31, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Lucien Henri Jacques QUENNEHEN, Antoine Claude Michel Etienne DANIS, Hubert Jean-Yves ILLAND, Clément JARROSSAY, Nicolas Paul TABLEAU
  • Patent number: 11286813
    Abstract: A turbine ring assembly includes ring segments forming a turbine ring and a ring support structure, each segment having a part forming an annular base with, in the radial direction, an inner face and an outer face from which project a first and a second hooking tab, the structure including a shroud from which project a first and a second radial flange between which are retained the first and second tabs, a first annular flange made of one part and a second annular flange disposed upstream of the ring. The first flange includes an annular shoulder and the second flange includes an annular recess forming an axial stop cooperating with the shoulder.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: March 29, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Clément Jarrossay, Nicolas Paul Tableau, Lucien Henri Jacques Quennehen