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).
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Patent number: 12031455Abstract: 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: GrantFiled: June 1, 2020Date of Patent: July 9, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Aurélien Gaillard, Antoine Claude Michel Etienne Danis, Clément Jarrossay, Gilles Gérard Claude Lepretre, Nicolas Paul Tableau
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Patent number: 11965433Abstract: 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: GrantFiled: April 28, 2021Date of Patent: April 23, 2024Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICSInventors: Antoine Claude Michel Etienne Danis, Clément Jarrossay, Lucien Henri Jacques Quennehen, Nicolas Paul Tableau, Matthieu Arnaud Gimat
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Patent number: 11814990Abstract: 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: GrantFiled: October 28, 2020Date of Patent: November 14, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Paul Tableau, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Matthieu Arnaud Gimat, Gilles Gérard Claude Lepretre
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Patent number: 11795838Abstract: 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: GrantFiled: June 25, 2020Date of Patent: October 24, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Jarrossay, Antoine Claude Michel Etienne Danis, Lucien Henri Jacques Quennehen, Nicolas Paul Tableau, Sébastien Serge Francis Congratel
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Patent number: 11746668Abstract: 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: GrantFiled: March 22, 2021Date of Patent: September 5, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Jarrossay, Clément Emile André Cazin, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Aurélien Gaillard
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Publication number: 20230212952Abstract: 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: ApplicationFiled: April 28, 2021Publication date: July 6, 2023Applicants: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICSInventors: Antoine Claude Michel Etienne DANIS, Clément JARROSSAY, Lucien Henri Jacques QUENNEHEN, Nicolas Paul TABLEAU, Matthieu Arnaud GIMAT
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Publication number: 20230118738Abstract: 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: ApplicationFiled: March 22, 2021Publication date: April 20, 2023Applicant: Safran Aircraft EnginesInventors: Clément JARROSSAY, Clément Emile André CAZIN, Sébastien Serge Francis CONGRATEL, Antoine Claude Michel Etienne DANIS, Aurélien GAILLARD
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Publication number: 20230116425Abstract: 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: ApplicationFiled: March 22, 2021Publication date: April 13, 2023Applicant: Safran Aircraft EnginesInventors: Clément JARROSSAY, Sébastien Serge Francis CONGRATEL, Antoine Claude Michel Etienne DANIS, Aurélien GAILLARD, Nicolas Paul TABLEAU
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Patent number: 11585241Abstract: 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: GrantFiled: September 24, 2019Date of Patent: February 21, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Claude Michel Etienne Danis, Clément Jarrossay, Lucien Henri Jacques Quennehen, Nicolas Paul Tableau, Hubert Jean-Yves Illand
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Patent number: 11542827Abstract: 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: GrantFiled: January 8, 2020Date of Patent: January 3, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Lucien Henri Jacques Quennehen, Antoine Claude Michel Etienne Danis, Hubert Jean-Yves Illand, Clément Jarrossay, Nicolas Paul Tableau
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Patent number: 11506085Abstract: 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: GrantFiled: October 21, 2019Date of Patent: November 22, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clement Jarrossay, Sebastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Clement Jean Pierre Duffau, Nicolas Paul Tableau, Lucien Henri Jacques Quennehen
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Publication number: 20220364475Abstract: 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: ApplicationFiled: October 28, 2020Publication date: November 17, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Paul TABLEAU, Sébastien Serge Francis CONGRATEL, Antoine Claude Michel Etienne DANIS, Matthieu Arnaud GIMAT, Gilles Gérard Claude LEPRETRE
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Patent number: 11480064Abstract: 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: GrantFiled: April 15, 2019Date of Patent: October 25, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Jarrossay, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Lucien Henri Jacques Quennehen
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Publication number: 20220316357Abstract: 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: ApplicationFiled: June 25, 2020Publication date: October 6, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clément JARROSSAY, Antoine Claude Michel Etienne DANIS, Lucien Henri Jacques QUENNEHEN, Nicolas Paul TABLEAU, Sébastien Serge Francis CONGRATEL
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Patent number: 11441434Abstract: 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: GrantFiled: December 10, 2019Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Claude Michel Etienne Danis, Sébastien Serge Francis Congratel, Clément Jean Pierre Duffau, Lucien Henri Jacques Quennehen, Nicolas Paul Tableau
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Publication number: 20220228498Abstract: 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: ApplicationFiled: June 1, 2020Publication date: July 21, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Aurélien GAILLARD, Antoine Claude Michel Etienne DANIS, Clément JARROSSAY, Gilles Gérard Claude LEPRETRE, Nicolas Paul TABLEAU
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Patent number: 11391170Abstract: 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: GrantFiled: April 17, 2019Date of Patent: July 19, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Lucien Henri Jacques Quennehen, Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Clément Jarrossay, Nicolas Paul Tableau
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Publication number: 20220195894Abstract: 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: ApplicationFiled: April 3, 2020Publication date: June 23, 2022Inventors: Lucien Henri Jacques QUENNEHEN, Antoine Claude Michel Etienne DANIS, Clément Jean Pierre DUFFAU, Clément JARROSSAY, Nicolas Paul TABLEAU
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Publication number: 20220098994Abstract: 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: ApplicationFiled: January 8, 2020Publication date: March 31, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Lucien Henri Jacques QUENNEHEN, Antoine Claude Michel Etienne DANIS, Hubert Jean-Yves ILLAND, Clément JARROSSAY, Nicolas Paul TABLEAU
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Patent number: 11286813Abstract: 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: GrantFiled: December 18, 2019Date of Patent: March 29, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Clément Jarrossay, Nicolas Paul Tableau, Lucien Henri Jacques Quennehen