Patents by Inventor Patrick Jean Laurent Sultana
Patrick Jean Laurent Sultana 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: 20240102397Abstract: A turbine stator assembly including a guide vane assembly and a sealing ring bearing an abradable element of a dynamic sealing ring. The assembly includes pins secured to the sealing ring and cooperating with respective oblong openings formed in the guide vane assembly so as to allow a radial movement of the ring with respect to the guide vane assembly in order to compensate for differential thermal expansions. A seal is arranged so as to compensate for circumferential spaces between ring sectors forming the guide vane assembly.Type: ApplicationFiled: December 3, 2021Publication date: March 28, 2024Applicant: SAFRAN AIRCRAFT ENGINESInventors: Patrick Jean Laurent SULTANA, Marc-Antoine Anatole GOT, Laurent Cédric ZAMAI
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Patent number: 11788430Abstract: A counter-rotating turbine of an aircraft turbomachine, includes a casing including an endoscopy port configured for an endoscopy plug of a non-destructive testing device to pass into the casing. The endoscopy plug includes a mechanism for acquiring and transmitting images. The non-destructive testing device includes a mechanism for receiving and displaying images connected to the mechanism for acquiring and transmitting images by a wireless connection. First and second rotors are configured to rotate in opposite rotation directions, the second rotor having an endoscopy port in which the endoscopy plug is removably attached.Type: GrantFiled: March 16, 2020Date of Patent: October 17, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Patrick Jean Laurent Sultana, Renaud James Martet, Maxime Aurelien Rotenberg
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Patent number: 11555408Abstract: Counter-rotating turbine (C) of a turbomachine (10) extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum on which an inner movable blading (22) is fixed, an outer rotor configured to rotate about the axis of rotation (X) in a direction opposite to the inner rotor, and comprising an outer drum (50) on which an outer movable blading (20) is fixed, the outer movable blading (20) comprising at least one fixing rod (212) extending through an orifice (51) of the outer drum (50), the outer movable blading (20) being fixed to the outer drum (50) via a clamping means (100) fixed to the fixing rod (212) from an outer face of the outer drum (50), a set ring (80) being disposed around the fixing rod (50) in the orifice (51) of the outer drum (50).Type: GrantFiled: April 3, 2020Date of Patent: January 17, 2023Assignee: Safran Aircraft EnginesInventors: Patrick Jean Laurent Sultana, Clément Charles Jérémy Coiffier, Olivier Renon, Laurent Cédric Zamai
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Publication number: 20220389874Abstract: The invention relates to an assembly for a turbine engine, comprising a radially inner shaft (3) and a radially outer shaft (7), said shafts (7, 8) being coaxial and extending along an axis (X), means (11, 15) for coupling said inner and outer shafts (7, 8) in rotation, means (22) for axially holding the inner shaft (8) relative to the outer shaft (7), means for centring the inner shaft (8) relative to the outer shaft (7), characterised in that the centring means comprise a shim (14) for radial centring and for axial positioning, this shim being frustoconical and interposed between a frustoconical centring surface (13) of the inner shaft (8) and a corresponding frustoconical centring surface (10) of the outer shaft (7).Type: ApplicationFiled: September 21, 2020Publication date: December 8, 2022Inventors: Patrick Jean Laurent SULTANA, Stéphane Pierre Guillaume BLANCHARD, Antoine Hervé DOS SANTOS
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Patent number: 11486252Abstract: A rotor disc for a turbomachine, the disc extending circumferentially about an axis and including a plurality of cavities configured to receive blade roots, each cavity including a downstream radial wall configured to axially block the blade root in the cavity, each downstream radial wall including a channel of ventilation of the cavity, including an inlet orifice which opens into the cavity and an outlet orifice which opens onto a downstream surface of the disc. An assembly for a turbomachine including such a disc and an upstream retention ring and a turbomachine including such an assembly.Type: GrantFiled: August 26, 2019Date of Patent: November 1, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Patrick Jean Laurent Sultana, Arnaud Lasantha Genilier
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Patent number: 11454117Abstract: A rotor for a contrarotating turbine comprising a drum and a blading mounted inside, the drum comprising a hook delimiting a housing having an outer wall and an inner wall, the blading comprising a blade and an outer platform provided with spoiler placed inside the housing, wherein the rotor comprises a foil comprising an elastic inner wing and an outer wing, the outer wing being arranged radially between the spoiler and the outer wall, the inner wing having a first support with the inner wall and a second support with the spoiler, the inner wing being arranged in the housing so as to exert a force on the spoiler so as to press the spoiler against the outer wall via the outer wing.Type: GrantFiled: March 6, 2020Date of Patent: September 27, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Patrick Jean Laurent Sultana, Olivier Renon, Laurent Cédric Zamai, Clément Charles Jérémy Coiffier
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Publication number: 20220186633Abstract: A counter-rotating turbine of an aircraft turbomachine, includes a casing including an endoscopy port configured for an endoscopy plug of a non-destructive testing device to pass into the casing. The endoscopy plug includes a mechanism for acquiring and transmitting images. The non-destructive testing device includes a mechanism for receiving and displaying images connected to the mechanism for acquiring and transmitting images by a wireless connection. First and second rotors are configured to rotate in opposite rotation directions, the second rotor having an endoscopy port in which the endoscopy plug is removably attached.Type: ApplicationFiled: March 16, 2020Publication date: June 16, 2022Inventors: Patrick Jean Laurent SULTANA, Renaud James MARTET, Maxime Aurelien ROTENBERG
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Publication number: 20220162951Abstract: Counter-rotating turbine (C) of a turbomachine (10) extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum on which an inner movable blading (22) is fixed, an outer rotor configured to rotate about the axis of rotation (X) in a direction opposite to the inner rotor, and comprising an outer drum (50) on which an outer movable blading (20) is fixed, the outer movable blading (20) comprising at least one fixing rod (212) extending through an orifice (51) of the outer drum (50), the outer movable blading (20) being fixed to the outer drum (50) via a clamping means (100) fixed to the fixing rod (212) from an outer face of the outer drum (50), a set ring (80) being disposed around the fixing rod (50) in the orifice (51) of the outer drum (50).Type: ApplicationFiled: April 3, 2020Publication date: May 26, 2022Applicant: Safran Aircraft EnginesInventors: Patrick Jean Laurent SULTANA, Clément Charles Jérémy COIFFIER, Olivier RENON, Laurent Cédric ZAMAI
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Publication number: 20210355830Abstract: A rotor disc for a turbomachine, the disc extending circumferentially about an axis and including a plurality of cavities configured to receive blade roots, each cavity including a downstream radial wall configured to axially block the blade root in the cavity, each downstream radial wall including a channel of ventilation of the cavity, including an inlet orifice which opens into the cavity and an outlet orifice which opens onto a downstream surface of the disc. An assembly for a turbomachine including such a disc and an upstream retention ring and a turbomachine including such an assembly.Type: ApplicationFiled: August 26, 2019Publication date: November 18, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Patrick Jean Laurent SULTANA, Arnaud Lasantha GENILIER
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Patent number: 11156129Abstract: A casing of a turbine of a turbine engine includes an internal shroud, an external shroud extending around the internal shroud, and hollow arms connecting the external shroud to the internal shroud and each intended to receive a tubular auxiliary element, each hollow arm defining an inner housing connecting a first passage orifice passing through the internal shroud in the radial direction to a second passage orifice passing through the external shroud in the radial direction, and including an inner wall facing the inner housing. Each arm includes at least one protrusion on the inner wall of the arm protruding from the inner wall towards the inner housing and defining a constriction of the inner housing in a section plane orthogonal to the direction in which the arm extends.Type: GrantFiled: February 24, 2020Date of Patent: October 26, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Patrick Jean Laurent Sultana, Gaël Frédéric Claude Cyrille Evain, Olivier Arnaud Fabien Lambert
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Patent number: 11136894Abstract: The invention relates to a turbomachine assembly comprising: —a casing comprising: —an internal hub (10), —an external ferrule (20) extending around and at a distance from the internal hub (10), —a hollow arm (30), provided with a longitudinal cavity (40) and connecting the internal hub (10) and the external ferrule (20), —a tube (50) configured to extend in the interior of the longitudinal cavity (40) of the hollow arm (30) of the casing and comprising a central support (60) comprising two elastic blades (61) and configured to exert a pressure on the wall (42) of the longitudinal cavity (40) when the tube (50) is extended in the interior of the longitudinal cavity (40); characterized in that the material(s) of the elastic blades (61) is (are) such that said elastic blades (61) have a stress curve between the minimum and maximum stress curves of table A.Type: GrantFiled: March 23, 2018Date of Patent: October 5, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Patrick Jean Laurent Sultana, Sebastien Jean Laurent Prestel, Olivier Renon
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Publication number: 20210108526Abstract: The invention relates to a turbomachine assembly comprising: —a casing comprising: —an internal hub (10), —an external ferrule (20) extending around and at a distance from the internal hub (10), —a hollow arm (30), provided with a longitudinal cavity (40) and connecting the internal hub (10) and the external ferrule (20), —a tube (50) configured to extend in the interior of the longitudinal cavity (40) of the hollow arm (30) of the casing and comprising a central support (60) comprising two elastic blades (61) and configured to exert a pressure on the wall (42) of the longitudinal cavity (40) when the tube (50) is extended in the interior of the longitudinal cavity (40); characterized in that the material(s) of the elastic blades (61) is (are) such that said elastic blades (61) have a stress curve between the minimum and maximum stress curves of table A.Type: ApplicationFiled: March 23, 2018Publication date: April 15, 2021Inventors: Patrick Jean Laurent SULTANA, Sebastien Jean Laurent PRESTEL, Olivier RENON
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Publication number: 20200291822Abstract: A casing of a turbine of a turbine engine includes an internal shroud, an external shroud extending around the internal shroud, and hollow arms connecting the external shroud to the internal shroud and each intended to receive a tubular auxiliary element, each hollow arm defining an inner housing connecting a first passage orifice passing through the internal shroud in the radial direction to a second passage orifice passing through the external shroud in the radial direction, and including an inner wall facing the inner housing. Each arm includes at least one protrusion on the inner wall of the arm protruding from the inner wall towards the inner housing and defining a constriction of the inner housing in a section plane orthogonal to the direction in which the arm extends.Type: ApplicationFiled: February 24, 2020Publication date: September 17, 2020Inventors: Patrick Jean Laurent SULTANA, Gaël Frédéric Claude Cyrille EVAIN, Olivier Arnaud Fabien LAMBERT
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Publication number: 20200284150Abstract: A rotor for a contrarotating turbine comprising a drum and a blading mounted inside, the drum comprising a hook delimiting a housing having an outer wall and an inner wall, the blading comprising a blade and an outer platform provided with spoiler placed inside the housing, wherein the rotor comprises a foil comprising an elastic inner wing and an outer wing, the outer wing being arranged radially between the spoiler and the outer wall, the inner wing having a first support with the inner wall and a second support with the spoiler, the inner wing being arranged in the housing so as to exert a force on the spoiler so as to press the spoiler against the outer wall via the outer wing.Type: ApplicationFiled: March 6, 2020Publication date: September 10, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Patrick Jean Laurent Sultana, Olivier Renon, Laurent Cédric Zamai, Clément Charles Jérémy Coiffier