Patents by Inventor Sylvain Paquin
Sylvain Paquin 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: 20240018872Abstract: The invention relates to a method for manufacturing a vane (11) of a turbine engine comprising a pressure-face wall (14) and a suction-face wall (15) spaced apart from one another, this vane (11) comprising a tip (S) with: a bottom wall (18) extending from the pressure-face wall (14) to the suction-face wall (15), each of which comprises a free edge (19, 21) extending beyond this bottom wall (18) to delimit, together with this bottom wall (18), a squealer shape (B); a partition wall (22) extending from the pressure-face wall (14) to the suction-face wall (15) and spaced apart from the bottom wall (18) to delimit, together with this bottom wall (18), a cavity (C) under the squealer tip; the method including: a moulding step to form at least the pressure-face wall (14), the suction-face wall (15) and the partition wall (22); —a step of forming the bottom wall (18) using an additive manufacturing method by adding metal material.Type: ApplicationFiled: December 8, 2021Publication date: January 18, 2024Applicant: SAFRANInventors: Leandre OSTINO, Romain Pierre CARIOU, Filippo PAGNONI, Sylvain PAQUIN, Adrien Bernard Vincent ROLLINGER
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Patent number: 11299990Abstract: The invention relates to a turbomachine turbine vane comprising a root having a blade (12) comprising a leading edge (16) and a trailing edge (17) and a lower surface wall (14) and an upper surface wall (13), as well as: a manifold for cooling (18) the leading edge (16); a supply line (19) for collecting air from the root and supplying the manifold (18); a side cavity (23) extending along the upper surface wall (13) and supplied with air from the root, to form a heat shield facing the supply line (19); and a circuit forming a trombone comprising a middle portion (24) extending along the supply line (19) and extending laterally to the upper surface wall (13), the middle portion (24) being supplied by the supply line at the tip of the blade (12).Type: GrantFiled: March 9, 2017Date of Patent: April 12, 2022Assignee: SAFRANInventors: Sylvain Paquin, Adrien Bernard Vincent Rollinger
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Patent number: 11248468Abstract: Aviation turbine blade (10) extending in the radial direction from a blade root (14) as far as an upper partition wall (26), said blade (10) comprising a plurality of inner cavities (C1-C10) defining at least one cooling circuit, each of said inner cavities (C1-C10) being defined by walls among inner walls (40, 42), a lower surface wall (22), an upper surface wall (24), the blade root (14) and the upper partition wall (26), said blade (10) being characterized in that it comprises at least one reinforcing beam (50, 60) disposed inside one of the inner cavities (C3, C8), and connecting the blade root (14) to the upper partition wall (26), said reinforcing beam (50, 60) is not connected to the inner walls (40, 42), the lower surface wall (22) and the upper surface wall (24).Type: GrantFiled: April 10, 2018Date of Patent: February 15, 2022Assignee: SAFRANInventors: Sylvain Paquin, Romain Pierre Cariou, Thomas Michel Flamme, Adrien Bernard Vincent Rollinger
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Patent number: 11236617Abstract: Blade for a turbine, comprising a blade root and an airfoil (13) extending radially outwards from the blade root (12), the airfoil (13) comprising a first internal cooling circuit including an intrados cavity (33, 36) extending radially along the intrados wall (16) and a first inner wall (47, 45) arranged between the intrados wall (16) and the extrados wall (18), an extrados cavity (34, 37) extending radially along the extrados wall (18) and a second inner wall (47, 43) arranged between the intrados wall (16) and the extrados wall (18). The first cooling circuit includes one inner through cavity (35, 38) defined between two through walls (59, 57, 55, 53) each extending between the intrados wall (16) and the extrados wall (18). The intrados cavity (33, 36), the extrados cavity (34, 37) and the inner through cavity (35, 38) are fluidly connected in series.Type: GrantFiled: April 10, 2018Date of Patent: February 1, 2022Assignee: SAFRANInventors: Thomas Michel Flamme, Romain Pierre Cariou, Sylvain Paquin, Adrien Bernard Vincent Rollinger
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Patent number: 11073025Abstract: An aviation turbine blade (10) includes at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower surface cavity (C2) being adjacent to the lower surface wall (22), each of the first and second through-cavities (C1, C4) extending from the lower surface wall (22) as far as the upper surface wall (24), the second through-cavity (C4) including a first inner wall (P1) extending from the upper surface wall (24) as far as the first through-cavity (C1), and a second inner wall (P2) extending from the lower surface wall (22) as far as the first through-cavity (C1). The first (P1) and second (P2) inner walls are not connected.Type: GrantFiled: April 10, 2018Date of Patent: July 27, 2021Assignee: SAFRANInventors: Sylvain Paquin, Romain Pierre Cariou, Thomas Michel Flamme, Adrien Bernard Vincent Rollinger
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Patent number: 10961856Abstract: A ceramic core used for fabricating a hollow turbine blade for a turbine engine by using the lost-wax casting technique and shaped to constitute the cavities of the blade as a single element, includes, in order to feed the insides of these cavities jointly with cooling air, core portions that are to form first and second lateral cavities and that are connected to a core portion that is to form at least one central cavity, firstly in the core root via at least two ceramic junctions, and secondly at various heights up the core via a plurality of other ceramic junctions of positioning that defines the thickness of the internal partitions of the blade, while also ensuring additional cooling air for predetermined critical zones of the first and second lateral cavities.Type: GrantFiled: March 22, 2016Date of Patent: March 30, 2021Assignees: SAFRAN AIRCRAFT ENGINES, SAFRANInventors: Sylvain Paquin, Charlotte Marie Dujol, Patrice Eneau, Hugues Denis Joubert, Adrien Bernard Vincent Rollinger
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Patent number: 10844733Abstract: An aviation turbine blade extending in the radial direction and presenting a pressure side and a suction side, including a plurality of pressure side cavities extending radially at the pressure side of the blade, a plurality of suction side cavities extending radially at the suction side of the blade, and at least one central cavity located in the central portion of the blade and surrounded by pressure side cavities and by suction side cavities, the blade further including a plurality of cooling circuits, in which at least a first cooling circuit comprises: a first cavity and a second cavity, the first and second cavities communicating with each other at a radially inner end and at a radially outer end of the blade.Type: GrantFiled: September 28, 2017Date of Patent: November 24, 2020Assignee: SAFRANInventors: Adrien Bernard Vincent Rollinger, Romain Pierre Cariou, Thomas Michel Flamme, Sylvain Paquin
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Publication number: 20200157948Abstract: An aviation turbine blade (10) includes at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower surface cavity (C2) being adjacent to the lower surface wall (22), each of said first and second through-cavities (C1, C4) extending from the lower surface wall (22) as far as the upper surface wall (24), the second through-cavity (C4) including a first inner wall (P1) extending from the upper surface wall (24) as far as the first through-cavity (C1), and a second inner wall (P2) extending from the lower surface wall (22) as far as the first through-cavity (C1). The first (P1) and second (P2) inner walls are not connected.Type: ApplicationFiled: April 10, 2018Publication date: May 21, 2020Applicant: SAFRANInventors: Sylvain PAQUIN, Romain Pierre CARIOU, Thomas Michel FLAMME, Adrien Bernard Vincent ROLLINGER
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Publication number: 20200149405Abstract: Blade for a turbine, comprising a blade root and an airfoil (13) extending radially outwards from the blade root (12), the airfoil (13) comprising a first internal cooling circuit including an intrados cavity (33, 36) extending radially along the intrados wall (16) and a first inner wall (47, 45) arranged between the intrados wall (16) and the extrados wall (18), an extrados cavity (34, 37) extending radially along the extrados wall (18) and a second inner wall (47, 43) arranged between the intrados wall (16) and the extrados wall (18). The first cooling circuit includes one inner through cavity (35, 38) defined between two through walls (59, 57, 55, 53) each extending between the intrados wall (16) and the extrados wall (18). The intrados cavity (33, 36), the extrados cavity (34, 37) and the inner through cavity (35, 38) are fluidly connected in series.Type: ApplicationFiled: April 10, 2018Publication date: May 14, 2020Applicant: SAFRANInventors: Thomas Michel FLAMME, Romain Pierre CARIOU, Sylvain PAQUIN, Adrien Bernard Vincent ROLLINGER
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Publication number: 20200040741Abstract: Aviation turbine blade (10) extending in the radial direction from a blade root (14) as far as an upper partition wall (26), said blade (10) comprising a plurality of inner cavities (C1-C10) defining at least one cooling circuit, each of said inner cavities (C1-C10) being defined by walls among inner walls (40, 42), a lower surface wall (22), an upper surface wall (24), the blade root (14) and the upper partition wall (26), said blade (10) being characterized in that it comprises at least one reinforcing beam (50, 60) disposed inside one of the inner cavities (C3, C8), and connecting the blade root (14) to the upper partition wall (26), said reinforcing beam (50, 60) is not connected to the inner walls (40, 42), the lower surface wall (22) and the upper surface wall (24).Type: ApplicationFiled: April 10, 2018Publication date: February 6, 2020Applicant: SAFRANInventors: Sylvain PAQUIN, Romain Pierre CARIOU, Thomas Michel FLAMME, Adrien Bernard Vincent ROLLINGER
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Publication number: 20190211693Abstract: An aviation turbine blade extending in the radial direction and presenting a pressure side and a suction side, including a plurality of pressure side cavities extending radially at the pressure side of the blade, a plurality of suction side cavities extending radially at the suction side of the blade, and at least one central cavity located in the central portion of the blade and surrounded by pressure side cavities and by suction side cavities, the blade further including a plurality of cooling circuits, in which at least a first cooling circuit comprises: a first cavity and a second cavity, the first and second cavities communicating with each other at a radially inner end and at a radially outer end of the blade.Type: ApplicationFiled: September 28, 2017Publication date: July 11, 2019Applicant: SAFRANInventors: Adrien Bernard Vincent ROLLINGER, Romain Pierre CARIOU, Thomas Michel FLAMME, Sylvain PAQUIN
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Publication number: 20190093485Abstract: The invention relates to a turbomachine turbine vane comprising a root having a blade (12) comprising a leading edge (16) and a trailing edge (17) and a lower surface wall (14) and an upper surface wall (13), as well as: a manifold for cooling (18) the leading edge (16); a supply line (19) for collecting air from the root and supplying the manifold (18); a side cavity (23) extending along the upper surface wall (13) and supplied with air from the root, to form a heat shield facing the supply line (19); and a circuit forming a trombone comprising a middle portion (24) extending along the supply line (19) and extending laterally to the upper surface wall (13), the middle portion (24) being supplied by the supply line at the tip of the blade (12).Type: ApplicationFiled: March 9, 2017Publication date: March 28, 2019Inventors: Sylvain PAQUIN, Adrien Bernard Vincent ROLLINGER
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Publication number: 20180073373Abstract: A ceramic core used for fabricating a hollow turbine blade for a turbine engine by using the lost-wax casting technique and shaped to constitute the cavities of the blade as a single element, includes, in order to feed the insides of these cavities jointly with cooling air, core portions that are to form first and second lateral cavities and that are connected to a core portion that is to form at least one central cavity, firstly in the core root via at least two ceramic junctions, and secondly at various heights up the core via a plurality of other ceramic junctions of positioning that defines the thickness of the internal partitions of the blade, while also ensuring additional cooling air for predetermined critical zones of the first and second lateral cavities.Type: ApplicationFiled: March 22, 2016Publication date: March 15, 2018Applicants: SAFRAN, SAFRAN AIRCRAFT ENGINESInventors: Sylvain PAQUIN, Charlotte Marie DUJOL, Patrice ENEAU, Hugues Denis JOUBERT, Adrien Bernard Vincent ROLLINGER
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Patent number: 7513739Abstract: A moving blade for a turbomachine, the central portion of the blade including a pressure-side cooling circuit and a suction-side cooling circuit. The pressure-side circuit comprises at least first and second pressure-side cavities extending from the pressure side of the blade to a central wall, a central cavity extending from the pressure side to the suction side of the blade, and outlet orifices opening out from the central cavity and into the pressure-side face of the blade. The suction-side circuit comprises at least first and second suction-side cavities extending radially from the suction side of the blade to the central wall, a central cavity extending across the blade from the pressure side to the suction side, and outlet orifices opening out from the central cavity and into the pressure-side face of the blade.Type: GrantFiled: June 15, 2006Date of Patent: April 7, 2009Assignee: SnecmaInventors: Jacques Auguste Amedee Boury, Patrice Eneau, Sylvain Paquin
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Publication number: 20070116570Abstract: A moving blade for a turbomachine, the central portion of the blade including a pressure-side cooling circuit and a suction-side cooling circuit. The pressure-side circuit comprises at least first and second pressure-side cavities extending from the pressure side of the blade to a central wall, a central cavity extending from the pressure side to the suction side of the blade, and outlet orifices opening out from the central cavity and into the pressure-side face of the blade. The suction-side circuit comprises at least first and second suction-side cavities extending radially from the suction side of the blade to the central wall, a central cavity extending across the blade from the pressure side to the suction side, and outlet orifices opening out from the central cavity and into the pressure-side face of the blade.Type: ApplicationFiled: June 15, 2006Publication date: May 24, 2007Applicant: SNECMAInventors: Jacques Boury, Patrice Eneau, Sylvain Paquin