Patents by Inventor Sébastien Digard Brou De Cuissart
Sébastien Digard Brou De Cuissart 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: 11788515Abstract: The present disclosure relates to cable guiding assemblies for wind turbine power cables. A cable guiding assembly comprises an outer part and a central part. Each part has a top surface, a bottom surface, a laterally inner surface and a laterally outer surface. The laterally inner surface has a plurality of recesses suitable for receiving power cables. An outer portion of the central part is configured to be attached to an inner portion of the outer part.Type: GrantFiled: March 9, 2022Date of Patent: October 17, 2023Assignee: General Electric Renovables Espana, S.L.Inventors: Joel Maignan, Sébastien Digard Brou De Cuissart, Alan Pfeiffer, Patrice Denis
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Publication number: 20230323860Abstract: The present disclosure relates to a wind turbine (10) comprising a wind turbine tower (15), a nacelle including a primary frame (110), wherein the primary frame is connected to the tower (15). The wind turbine further comprises a secondary structure (120) connected to the primary frame (110) and one or more flexible couplings (130) between the primary frame (110) and the secondary structure (120) configured to reduce transmission of deformations from the primary frame (110) to the secondary structure (120). The present disclosure also relates to secondary structures (120) configured to be connected to primary frames (110) and to methods (500) for refurbishing a secondary structure (120) of a wind turbine (10).Type: ApplicationFiled: April 10, 2023Publication date: October 12, 2023Inventors: Francisco Javier ECHARTE CASQUERO, Sébastien DIGARD BROU DE CUISSART, John T. OLESEN
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Publication number: 20220290657Abstract: The present disclosure relates to cable guiding assemblies for wind turbine power cables. A cable guiding assembly comprises an outer part and a central part. Each part has a top surface, a bottom surface, a laterally inner surface and a laterally outer surface. The laterally inner surface has a plurality of recesses suitable for receiving power cables. An outer portion of the central part is configured to be attached to an inner portion of the outer part.Type: ApplicationFiled: March 9, 2022Publication date: September 15, 2022Inventors: Joel MAIGNAN, Sébastien DIGARD BROU DE CUISSART, Alan PFEIFFER, Patrice DENIS
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Patent number: 10717128Abstract: A method for manufacturing a metal component using lost-wax casting is provided. The component is made of, for example, nickel alloy, with a columnar or monocrystalline structure with at least one cavity of elongate shape. The method includes creating a wax model of the component with a ceramic core corresponding to the cavity, creating a shell mold around the model, placing the mold in a furnace, with the base standing on the sole of the furnace, pouring molten alloy into the shell mold, solidifying the poured metal by gradual cooling from the sole in a direction of propagation.Type: GrantFiled: January 13, 2014Date of Patent: July 21, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Yvan Rappart, Christelle Berthelemy, Benoît Georges Jocelyn Marie, David Locatelli, Sébastien Digard Brou De Cuissart
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Patent number: 10689985Abstract: A turbine blade for a turbomachine such as a turboprop or a turbojet, the blade including a root, a vane carried by the root and extending in a spanwise direction, ending at a tip, the vane including a pressure-side wall and a suction-side wall spaced apart from each other, and at least one duct configured to collect cooling air at the root and to make same flow in the vane in order to cool same; holes and/or slots made in the walls of same in order to discharge the cooling air out of the vane; an upper inner cavity located at the tip of the vane in order to cool same; and wherein at least one of the ducts directly supplies the upper cavity with cooling air collected in the root.Type: GrantFiled: May 27, 2015Date of Patent: June 23, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Charlotte Marie Dujol, Patrice Eneau, Sebastien Digard Brou De Cuissart, Matthieu Jean-Luc Vollebregt
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Patent number: 10669863Abstract: A blade for a turbomachine bladed wheel having N blades. At one end, the blade presents a platform that is formed integrally with an airfoil of the blade. Over a portion of the axial extent of the blade, a section through the platform wall on a plane perpendicular to the axis (X) of the wheel is constituted mainly by two first straight line segments arranged respectively on the two sides of the airfoil. Each of these segments forms an angle of 90°-180°/N relative to the radial direction on either side of the airfoil.Type: GrantFiled: December 12, 2014Date of Patent: June 2, 2020Assignee: Safran Aircraft EnginesInventors: Sami Benichou, Christian Bariaud, Stéphanie Deflandre, Sébastien Digard Brou De Cuissart, Patrick Emilien Paul Emile Huchin
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Patent number: 10626728Abstract: A blade for a turbomachine bladed wheel, the blade comprising a root, an airfoil, and a tip. The root and the tip have respective platforms, each presenting a surface on a side toward the airfoil, which surfaces are referred to respectively as the root platform wall and the tip platform wall. Each of these platform walls is constituted by a pressure side portion and a suction side portion meeting at a crest curve.Type: GrantFiled: December 8, 2014Date of Patent: April 21, 2020Assignee: Safran Aircraft EnginesInventors: Sami Benichou, Christian Bariaud, Stéphanie Deflandre, Sébastien Digard Brou De Cuissart, Patrick Emilien Paul Emile Huchin
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Patent number: 10486230Abstract: A method of fabricating a two-component blade for a gas turbine engine, the method including in succession: obtaining a blade profile made of ceramic material having a hole passing right through the blade profile in its length direction so as to form a longitudinal channel opening out into a top cavity; positioning and maintaining the blade profile in a mold so as to form a bottom cavity communicating with the channel of the blade profile; casting molten metal into the blade profile so as to fill the top and bottom cavities and the channel interconnecting them; and cooling the metal so that the shrinkage of the metal cooled in the top and bottom cavities leads to the ceramic of the blade profile being subjected to compression prestress.Type: GrantFiled: June 29, 2015Date of Patent: November 26, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Francois Casteilla, Sebastien Digard Brou De Cuissart, Serge Alain Fargeas, Vincent Marc Herb, Chantal Sylvette Marie-Noël Langlois
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Patent number: 10363633Abstract: A method of fabricating at least one metal part for a turbine engine, the method including the steps of casting a metal alloy by centrifuging into a permanent metal mold for making a blank; obtaining a cast blank of elongate shape and of section that is circular or polygonal; and machining the blank to make the part.Type: GrantFiled: October 9, 2013Date of Patent: July 30, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Celine Jeanne Marcillaud, Sebastien Digard Brou De Cuissart, Marie Mineur-Panigeon, Anthony Texier
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Patent number: 10196907Abstract: A turbomachine rotor blade includes an outer part at its distal end. The outer part includes a platform defining an outside surface of a passage for gas passing through a turbomachine and presenting first and second opposite side edges; and upstream and downstream sealing wipers extending outwards from the platform, each wiper extending between two lateral faces situated respectively at the first and second side edges. The two lateral faces of the upstream or the downstream wiper are covered at least in part in an anti-wear material.Type: GrantFiled: January 16, 2013Date of Patent: February 5, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Slim Bensalah, Arnaud Negri, Sebastien Digard Brou De Cuissart, Guillaume Klein, Ba-Phuc Tang, David Mathieu, Sibylle Doremus
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Patent number: 9981308Abstract: A method of manufacturing a core for molding a blade of a turbomachine, including placing a flexible ceramic sheet in a cavity of a mold in such a way as to shape the ceramic sheet, introducing a ceramic paste into the cavity of the mold, the ceramic paste forming at least one frame in contact with the ceramic sheet, and co-sintering the ceramic sheet and the frame in such a way as to rigidly join together the ceramic sheet and the frame, the frame maintaining the shape of the ceramic sheet given by the mold during the preceding co-sintering phases.Type: GrantFiled: June 29, 2015Date of Patent: May 29, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sebastien Digard Brou De Cuissart, Charlotte Marie Dujol, Patrice Eneau, Philippe Metron, Matthieu Jean-Luc Vollebregt
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Patent number: 9969035Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mold in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron having first and second sides (30a, 30b) and third and fourth sides (30c, 30d), in which the third and fourth sides extend between the first and second sides, flaring apart from the first side towards the second side, first at a first angle and subsequently at a second larger angle, and said at least one part is machined in the blank.Type: GrantFiled: December 9, 2014Date of Patent: May 15, 2018Assignee: SNECMAInventors: Patrick Emilien Paul Emile Huchin, Karine Deschandol, Sébastien Digard Brou De Cuissart, Serge Fargeas, Marc Soisson, Anthony Texier, Valéry Piaton
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Patent number: 9962763Abstract: A casting method for obtaining a part that includes a tapering portion, and a turbine engine blade obtained by casting and including a tapering trailing edge, are provided. The method includes: providing an insert element having a tapering section; making a shell around the insert element; and casting a molten material into the shell including the insert element.Type: GrantFiled: June 10, 2013Date of Patent: May 8, 2018Assignee: SNECMAInventors: Sebastien Digard Brou De Cuissart, Josserand Bassery, Stephanie Deflandre
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Patent number: 9869187Abstract: The internal cooling of moving blades of turbines in aircraft turbomachines is limited in effectiveness because of inhomogeneities of this cooling on each of the pressure-side and suction-side walls. To address this problem, there is proposed a blade including a circuit for cooling the airfoil part thereof, in which circuit the cavities interconnected in series are such that the stream of air flows radially toward the outside along the pressure-side wall in pressure-side cavities, and radially toward the inside along the suction-side wall in a suction-side cavity that is separated from the pressure-side cavities by an internal wall of the airfoil part. In this way, the force of the Coriolis effect deflects the stream of air toward each of the pressure-side and suction-side walls thereby limiting the inhomogeneity.Type: GrantFiled: April 23, 2015Date of Patent: January 16, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Charlotte Marie Dujol, Patrice Eneau, Sebastien Digard Brou De Cuissart, Matthieu Jean-Luc Vollebregt
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Patent number: 9844843Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mold in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.Type: GrantFiled: December 9, 2014Date of Patent: December 19, 2017Assignee: SNECMAInventors: Patrick Emilien Paul Emile Huchin, Karine Deschandol, Sébastien Digard Brou De Cuissart, Serge Fargeas, Marc Soisson, Anthony Texier, Valéry Piaton
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Patent number: 9796058Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.Type: GrantFiled: December 12, 2014Date of Patent: October 24, 2017Assignee: SNECMAInventors: Patrick Emilien Paul Emile Huchin, Karine Deschandol, Sébastien Digard Brou De Cuissart, Serge Fargeas, Marc Soisson, Anthony Texier, Valéry Piaton
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Patent number: 9764381Abstract: The invention relates to a rotary mold for centrifugal casting of an alloy. The mold comprises liners (135a) housed in hollow exoskeletons (137a). The exoskeletons retain the liners against the centrifugal force, during the casting, while the mold is spinning.Type: GrantFiled: January 29, 2015Date of Patent: September 19, 2017Assignee: Safran Aircraft EnginesInventors: Sébastien Digard Brou De Cuissart, Valéry Piaton, Marc Soisson
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Publication number: 20170183969Abstract: A turbine blade for a turbomachine such as a turboprop or a turbojet, the blade including a root, a vane carried by the root and extending in a spanwise direction, ending at a tip, the vane including a pressure-side wall and a suction-side wall spaced apart from each other, and at least one duct configured to collect cooling air at the root and to make same flow in the vane in order to cool same; holes and/or slots made in the walls of same in order to discharge the cooling air out of the vane; an upper inner cavity located at the tip of the vane in order to cool same; and wherein at least one of the ducts directly supplies the upper cavity with cooling air collected in the root.Type: ApplicationFiled: May 27, 2015Publication date: June 29, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Charlotte Marie DUJOL, Patrice ENEAU, Sebastien DIGARD BROU DE CUISSART, Matthieu Jean-Luc VOLLEBREGT
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Publication number: 20170151604Abstract: A method of manufacturing a core for molding a blade of a turbomachine, including placing a flexible ceramic sheet in a cavity of a mold in such a way as to shape the ceramic sheet, introducing a ceramic paste into the cavity of the mold, the ceramic paste forming at least one frame in contact with the ceramic sheet, and co-sintering the ceramic sheet and the frame in such a way as to rigidly join together the ceramic sheet and the frame, the frame maintaining the shape of the ceramic sheet given by the mold during the preceding co-sintering phases.Type: ApplicationFiled: June 29, 2015Publication date: June 1, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Sebastien DIGARD BROU DE CUISSART, Charlotte DUJOL, Patrice ENEAU, Philippe METRON, Matthieu Jean-Luc VOLLEBREGT
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Publication number: 20170136534Abstract: A method of fabricating a two-component blade for a gas turbine engine, the method including in succession: obtaining a blade profile made of ceramic material having a hole passing right through the blade profile in its length direction so as to form a longitudinal channel opening out into a top cavity; positioning and maintaining the blade profile in a mold so as to form a bottom cavity communicating with the channel of the blade profile; casting molten metal into the blade profile so as to fill the top and bottom cavities and the channel interconnecting them; and cooling the metal so that the shrinkage of the metal cooled in the top and bottom cavities leads to the ceramic of the blade profile being subjected to compression prestress.Type: ApplicationFiled: June 29, 2015Publication date: May 18, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Francois CASTEILLA, Sebastien DIGARD BROU DE CUISSART, Serge FARGEAS, Vincent HERB