Patents by Inventor Laurent Cédric ZAMAI
Laurent Cédric ZAMAI 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: 11814967Abstract: A turbine for a turbomachine has a first rotor and a second rotor configured to pivot about an axis in two opposite directions of rotation. The first rotor includes a radially outer drum from which blades extend radially inwards. The turbine has cooling means attached relative to the outer drum. The cooling means include a support plate with at least one first orifice and a calibration plate that is attached to the support plate and located radially inside the support plate. The calibration plate has at least one second calibration orifice facing the outer drum to allow the passage of cooling air radially from the outside to the inside through the first and second orifices.Type: GrantFiled: June 11, 2020Date of Patent: November 14, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Ulysse Jacques Bernard Danteny, Laurent Cédric Zamai
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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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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: 20220243605Abstract: A turbine for a turbomachine has a first rotor and a second rotor configured to pivot about an axis in two opposite directions of rotation. The first rotor includes a radially outer drum from which blades extend radially inwards. The turbine has cooling means attached relative to the outer drum. The cooling means include a support plate with at least one first orifice and a calibration plate that is attached to the support plate and located radially inside the support plate. The calibration plate has at least one second calibration orifice facing the outer drum to allow the passage of cooling air radially from the outside to the inside through the first and second orifices.Type: ApplicationFiled: June 11, 2020Publication date: August 4, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Ulysse Jacques Bernard DANTENY, Laurent Cédric ZAMAI
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Publication number: 20220178331Abstract: A turbine includes a first rotor and a second rotor that can rotate in opposite directions and are interleaved. The turbine further includes a ring to which abradable material is secured, the ring, unsegmented, extending between the first impellers of the first rotor and the second rotor, over a sector of between 350 and 360°, and, axially between an upstream end and a downstream end of the ring, the ring is held with the second rotor.Type: ApplicationFiled: March 6, 2020Publication date: June 9, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Patrick SULTANA, Olivier RENON, Laurent Cédric ZAMAI, Clément Charles Jérémy COIFFIER
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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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Patent number: 11162366Abstract: A rotor disc for a turbomachine, the disc extending circumferentially around an axis and including a plurality of cells configured to receive blade roots and each cell including an upstream radial wall configured to axially block the blade root in the cell, each cell being connected to an upstream surface of the disc by a ventilation channel of the cell, the ventilation channel including an inlet orifice which opens onto the upstream surface of the disc and an outlet orifice which opens into the cell. An assembly of such a disc, of a plurality of blades and of a downstream retaining ring and a turbomachine including such an assembly.Type: GrantFiled: February 7, 2020Date of Patent: November 2, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Laurent Cédric Zamai, Benoit Guilhem Bruno Jeannin, Loïc Fabien François Villard
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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
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Publication number: 20200263548Abstract: A rotor disc for a turbomachine, the disc extending circumferentially around an axis and including a plurality of cells configured to receive blade roots and each cell including an upstream radial wall configured to axially block the blade root in the cell, each cell being connected to an upstream surface of the disc by a ventilation channel of the cell, the ventilation channel including an inlet orifice which opens onto the upstream surface of the disc and an outlet orifice which opens into the cell. An assembly of such a disc, of a plurality of blades and of a downstream retaining ring and a turbomachine including such an assembly.Type: ApplicationFiled: February 7, 2020Publication date: August 20, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Laurent Cédric ZAMAI, Benoit Guilhem Bruno JEANNIN, Loïc Fabien François VILLARD
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Patent number: 10221772Abstract: A shock absorber assembly for a non-streamlined blower includes an extension collar having a first interface suitable for being rigidly attached on a first module of the blower; a connector support housing including a third interface suitable for being rigidly attached on a second module of the blower; and a fourth interface allowing a mechanical connection to be made between the housing and a second interface of the collar; a plurality of elastic devices arranged between the collar and the housing; a flange element rigidly attached on the third interface of the housing comprising a stop bearing on the collar in such a way as to define a space between the collar and the flange element; the elastic means are arranged so that a residual clearance exists between the flange element and the housing.Type: GrantFiled: September 20, 2016Date of Patent: March 5, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Laurent Cedric Zamai, Matthieu Etienne Joachim Palis