Patents by Inventor Thierry Guy Xavier TESSON
Thierry Guy Xavier TESSON 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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Publication number: 20240052863Abstract: An assembly for a turbine engine includes at least a first part and a second part, and at least one bolt including a screw engaging with a nut. The screw extends through respective openings in the first part and in the second part. A bearing element of the bolt has an annular flange mounted between the screw or the nut and the first part. The flange has a bearing surface bearing that is tapered and forms an angle (?) with an additional bearing surface of the first part such that only an outer peripheral area of the flange bearing surface comes into contact with the additional bearing surface of the first part, in a non-tightened state of the bolt, the flange deformable such that when the nut is tightened on the screw, a larger area of the flange bearing surface bears on the additional bearing surface of the first part.Type: ApplicationFiled: November 11, 2021Publication date: February 15, 2024Inventors: Gaël BOUCHY, Thomas REVEL, Christophe Paul AUPETIT, Thierry Guy Xavier TESSON
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Publication number: 20240052759Abstract: An assembly for a turbomachine includes at least a first part and a second part, and at least one bolt including a screw engaging with a nut. The screw extends through respective openings in the first part and in the second part. The bolt includes a support member having an annular collar mounted between the screw or the nut, and the first part. The collar has a support surface abutting, at least partially, on a complementary support surface of the first part. The collar also includes a recessed annular groove extending at the inner periphery of the collar.Type: ApplicationFiled: November 25, 2021Publication date: February 15, 2024Inventors: Thierry Guy Xavier TESSON, Thomas REVEL, Christophe Paul AUPETIT, Denis Jean Armel BUSQUET
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Publication number: 20230399268Abstract: A method of consolidation includes placing a fibrous preform in the shaping recess of a shaping tool, and supplying the shaping tool with a gas phase to obtain a deposit in the fibrous preform, the shaping tool for the vapor phase chemical infiltration including first and second portions, having respectively first and second shaping zones surrounded by a first and second edge zones, the first and the second shaping zone defining a shaping recess to receive the fibrous preform. A gas injection port is present at least partially in the first or second edge zone and a gas outlet port is present at least partially in the first or second edge zone, the gas injection port and the gas outlet port placing the shaping recess in fluid communication with the outside of the shaping tool. Outer faces of the first and second portion are impermeable to gas.Type: ApplicationFiled: February 10, 2021Publication date: December 14, 2023Inventors: Stéphane Roger André GOUJARD, Adrien DELCAMP, Cédric DESCAMPS, Thierry Guy Xavier TESSON, Charles LELEU
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Publication number: 20230340926Abstract: The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone (100) comprising a radially outer annular wall (102) defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (102), the sound box comprising a radially inner annular wall (104), —a connecting member (106) intended to be axially inserted between the exhaust housing and the ejection cone (100), the connecting member (106) comprising an upstream annular flange (108) intended to be attached to the exhaust housing and a plurality of downstream securing tabs (110) connected to the inner annular wall (104), —an annular sealing shroud (112) comprising an upstream portion surrounding the securing tabs (110) of the connecting member (106) so as to cover the spaces circumferentially located between the securing tabs (110) and axially located between the upstream annular flange (108) of the connecting member (106) and the radially inner annType: ApplicationFiled: October 4, 2021Publication date: October 26, 2023Inventors: Thierry Guy Xavier TESSON, Christophe Jean François THOREL, Christophe Paul AUPETIT, Thierry Jacques Albert LE DOCTE, Philippe AVENEL
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Patent number: 11753947Abstract: Method for manufacturing a CMC, i.e. ceramic matrix composite material, part provided with at least one cutout, as well as to such a CMC part provided with at least one cutout, the method comprising the following steps: providing (E1) a fibrous reinforcement (10), forming (E2?) a cavity in a portion of the fibrous reinforcement (10), injecting (E3) a slip comprising at least a ceramic powder and a solvent, the slip being injected so as to impregnate the fibrous reinforcement (10?) and to fill the cavity of the fibrous reinforcement (10?), drying (E4) the obtained assembly, carrying out a densification (E6) by infiltration of a liquid densification material and solidification of said densification material, machining (E7) at least one cutout in the obtained blank (30) within the volume corresponding to the cavity of the fibrous reinforcement (10).Type: GrantFiled: September 13, 2018Date of Patent: September 12, 2023Assignee: SAFRAN CERAMICSInventors: Maxime François Roger Carlin, Nicolas Eberling-Fux, Eddy Goullianne, Thierry Guy Xavier Tesson
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Patent number: 11738521Abstract: A manufacturing process of a fibrous preform for a composite material includes creating a fibrous texture by three-dimensional or multilayer weaving between a plurality of weft layers and warp layers, the fibrous texture including an extra-thick portion having a sacrificial portion and a useful portion adjacent to the sacrificial portion in the warp direction, the sacrificial portion, placing the fibrous texture in a forming toolset, shaping the fibrous texture so as to obtain a fibrous preform having a sacrificial portion and an adjacent useful portion, removing the sacrificial portion from the fibrous preform. When weaving the fibrous blank, one or more expansion elements are inserted into the weft layers located at the core of the sacrificial portion of the fibrous texture. Each expansion element has a cross-section greater than the cross-section or count of the weft threads or strands present in the useful portion.Type: GrantFiled: July 1, 2020Date of Patent: August 29, 2023Assignee: SAFRAN CERAMICSInventors: Thierry Guy Xavier Tesson, Marie Lefebvre, David Mathieu Paul Marsal
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Patent number: 11591924Abstract: An assembly for a turbomachine turbine includes a housing (1) extending circumferentially about an axis X, sectors (2) intended to form a ring capable of delimiting a gas flow path, each sector (2) comprising a first side (17) and a second side (18) extending radially and circumferentially about the said axis X and spaced axially from each other, each side (17, 18) of the sector (2) including at least one radial bearing surface of an oblong hole capable of cooperating with support pins (13, 14) of the housing (1), at least one of the sides (17, 18) including means (23) for the circumferential positioning of the sector (2) with respect to the housing (1), wherein each radial bearing surface is cylindrical relative to axis X and is capable of bearing on a complementary cylindrical surface relative to axis X of a support pin.Type: GrantFiled: February 26, 2020Date of Patent: February 28, 2023Assignee: SAFRAN CERAMICSInventors: Christophe Paul Aupetit, Thierry Guy Xavier Tesson, Clément Marie Benoît Roussille, Cécile Marie Emilienne Chevalier
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Publication number: 20220274354Abstract: A manufacturing process of a fibrous preform for a composite material includes creating a fibrous texture by three-dimensional or multilayer weaving between a plurality of weft layers and warp layers, the fibrous texture including an extra-thick portion having a sacrificial portion and a useful portion adjacent to the sacrificial portion in the warp direction, the sacrificial portion, placing the fibrous texture in a forming toolset, shaping the fibrous texture so as to obtain a fibrous preform having a sacrificial portion and an adjacent useful portion, removing the sacrificial portion from the fibrous preform. When weaving the fibrous blank, one or more expansion elements are inserted into the weft layers located at the core of the sacrificial portion of the fibrous texture. Each expansion element has a cross-section greater than the cross-section or count of the weft threads or strands present in the useful portion.Type: ApplicationFiled: July 1, 2020Publication date: September 1, 2022Inventors: Thierry Guy Xavier TESSON, Marie LEFEBVRE, David Mathieu Paul MARSAL
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Publication number: 20220235498Abstract: The invention relates to a three-dimensionally woven multilayer fibrous structure (20) having the same number of warp yarns woven at any level along the warp direction, the fibrous structure (20) comprising, in the warp direction, a first part (22) and a second part (24), the first part (22) having a thickness measured in a direction perpendicular to the warp and weft directions, greater than the second part (24), characterised in that the spacing between two weft planes along the warp direction is greater in the second part than in the first part (22), and in that the number of weft yarns is lower in the second part (24) than in the first part (22).Type: ApplicationFiled: June 3, 2020Publication date: July 28, 2022Inventors: Thierry Guy Xavier TESSON, Eric PHILIPPE, Marie LEFEBVRE, Aline PLANCKEEL
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Publication number: 20220154591Abstract: The invention concerns an assembly for a turbomachine turbine, comprising a housing (1) extending circumferentially about an axis X, sectors (2) intended to form a ring capable of delimiting a gas flow path, each sector (2) comprising a first side (17) and a second side (18) extending radially and circumferentially about the said axis X and spaced axially from each other, each side (17, 18) of the sector (2) comprising at least one radial bearing surface capable of cooperating with radial bearing means (13, 14) of the housing (1), at least one of the sides (17, 18) comprising means (23) for the circumferential positioning of the sector (2) with respect to the housing (1), characterised in that each radial bearing surface is cylindrical of axis X and is capable of bearing on a complementary cylindrical surface of axis X, integral with the housing (1).Type: ApplicationFiled: February 26, 2020Publication date: May 19, 2022Inventors: Christophe Paul AUPETIT, Thierry Guy Xavier TESSON, Clément Marie Benoit ROUSSILLE, Cécile MarieEmilienne CHEVALIER
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Patent number: 11332411Abstract: A method for producing a consolidated fiber preform intended for the manufacture of a part made of composite material, includes shaping a fiber texture in a heated metal mold, the texture being pre-impregnated with a transient or fugitive material, or shaping a fiber texture in a metal mold and injecting a transient or fugitive material into the fiber texture held in shape in the metal mold, cooling the mold, removing the set fiber preform from the mold, coating the fiber preform with a slurry containing a powder of ceramic or carbon particles, heat-treating the coated fiber preform so as to form a porous shell around the fiber preform by consolidation of the slurry and so as to remove the transient or fugitive material present in the fiber preform, consolidating the fiber preform by gas-phase chemical infiltration.Type: GrantFiled: March 5, 2018Date of Patent: May 17, 2022Assignees: SAFRAN, SAFRAN CERAMICSInventors: Thierry Guy Xavier Tesson, Maxime François Roger Carlin, Simon Thibaud, Rémy Dupont, Ramzi Bohli
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Patent number: 11015484Abstract: An assembly comprising ring sectors made of a first material, the sectors being placed circumferentially end to end and suspended from an outer casing, and radial positioning means comprising at least one annular tongue made of a different material, for fastening the ring sectors to the outer casing, by an annular support. The radial positioning means further comprise an eccentric spreader engaged on one side with said at least one annular tongue and, on the other side, with the sectorized annular element, and acting to enable the distance between the annular tongue and the sectorized annular element to be adjusted radially.Type: GrantFiled: June 26, 2018Date of Patent: May 25, 2021Assignee: Safran Aircraft EnginesInventors: Gilles Gérard Claude Lepretre, Thierry Guy Xavier Tesson, Hubert Jean-Yves Illand, Lucien Henri Jacques Quennehen, Matthieu Arnaud Gimat
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Publication number: 20200370170Abstract: A method for producing a consolidated fiber preform intended for the manufacture of a part made of composite material, includes shaping a fiber texture in a heated metal mold, the texture being pre-impregnated with a transient or fugitive material, or shaping a fiber texture in a metal mold and injecting a transient or fugitive material into the fiber texture held in shape in the metal mold, cooling the mold, removing the set fiber preform from the mold, coating the fiber preform with a slurry containing a powder of ceramic or carbon particles, heat-treating the coated fiber preform so as to form a porous shell around the fiber preform by consolidation of the slurry and so as to remove the transient or fugitive material present in the fiber preform, consolidating the fiber preform by gas-phase chemical infiltration.Type: ApplicationFiled: March 5, 2018Publication date: November 26, 2020Inventors: Thierry Guy Xavier TESSON, Maxime François Roger CARLIN, Simon THIBAUD, Rémy DUPONT, Ramzi BOHLI
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Publication number: 20200255344Abstract: Method for manufacturing a CMC, i.e. ceramic matrix composite material, part provided with at least one cutout, as well as to such a CMC part provided with at least one cutout, the method comprising the following steps: providing (E1) a fibrous reinforcement (10), forming (E2?) a cavity in a portion of the fibrous reinforcement (10), injecting (E3) a slip comprising at least a ceramic powder and a solvent, the slip being injected so as to impregnate the fibrous reinforcement (10?) and to fill the cavity of the fibrous reinforcement (10?), drying (E4) the obtained assembly, carrying out a densification (E6) by infiltration of a liquid densification material and solidification of said densification material, machining (E7) at least one cutout in the obtained blank (30) within the volume corresponding to the cavity of the fibrous reinforcement (10).Type: ApplicationFiled: September 13, 2018Publication date: August 13, 2020Applicant: Safran CeramicsInventors: Maxime François Roger CARLIN, Nicolas EBERLING-FUX, Eddy GOULLIANNE, Thierry Guy Xavier TESSON
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Patent number: 10590803Abstract: A turbine ring assembly includes ring sectors made as a single piece of ceramic matrix composite material and being for mounting on a metal ring support structure, the ring support structure having two tabs extending radially towards a gas flow passage, each ring sector having a first portion forming an annular base with a radially inside face defining the inside face of the turbine ring and an outside face from which there extend two tab-forming portions, the ring sectors having a section that is substantially ? shaped. The tabs of each ring sector fit axially over the tabs of the ring support structure with contact between the tabs of the ring support structure and the tabs of each ring sector when cold. The tabs of each ring sector are held to the ring support structure by pegs passing through holes formed in the tabs of each ring sector.Type: GrantFiled: March 15, 2016Date of Patent: March 17, 2020Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICSInventors: Lucien Henri Jacques Quennehen, Gaël Frédéric Claude Cyrille Evain, David Mathieu Paul Marsal, Thierry Guy Xavier Tesson
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Publication number: 20180371948Abstract: An assembly comprising ring sectors made of a first material, the sectors being placed circumferentially end to end and suspended from an outer casing, and radial positioning means comprising at least one annular tongue made of a different material, for fastening the ring sectors to the outer casing, by an annular support. The radial positioning means further comprise an eccentric spreader engaged on one side with said at least one annular tongue and, on the other side, with the sectorized annular element, and acting to enable the distance between the annular tongue and the sectorized annular element to be adjusted radially.Type: ApplicationFiled: June 26, 2018Publication date: December 27, 2018Applicant: Safran Aircraft EnginesInventors: Gilles Gérard Claude Lepretre, Thierry Guy Xavier Tesson, Hubert Jean-Yves IIIand, Lucien Henri Jacques Quennehen, Matthieu Arnaud Gimat
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Publication number: 20180073398Abstract: A turbine ring assembly includes ring sectors made as a single piece of ceramic matrix composite material and being for mounting on a metal ring support structure, the ring support structure having two tabs extending radially towards a gas flow passage, each ring sector having a first portion forming an annular base with a radially inside face defining the inside face of the turbine ring and an outside face from which there extend two tab-forming portions, the ring sectors having a section that is substantially r shaped. The tabs of each ring sector fit axially over the tabs of the ring support structure with contact between the tabs of the ring support structure and the tabs of each ring sector when cold. The tabs of each ring sector are held to the ring support structure by pegs passing through holes formed in the tabs of each ring sector.Type: ApplicationFiled: March 15, 2016Publication date: March 15, 2018Inventors: Lucien Henri Jacques QUENNEHEN, Gaël Frédéric Claude Cyrille EVAIN, David Mathieu Paul MARSAL, Thierry Guy Xavier TESSON