Patents by Inventor Jean-Francois CABRE
Jean-Francois CABRE 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: 11988387Abstract: Annular combustion chamber for an aircraft turbomachine, said chamber having two coaxial annular walls, an inner annular wall and an outer annular wall, respectively, which are connected upstream by an annular bottom wall of the chamber, wherein an injection device passes through an axis and comprises an air injection system and a frustoconical bowl which is flared downstream and has air passage openings, the chamber further having an annular deflector placed downstream of the bottom wall substantially parallel to the latter; and wherein the air injection system, the bottom wall, the deflector and the bowl are integrally formed.Type: GrantFiled: July 2, 2021Date of Patent: May 21, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Haris Musaefendic, Romain Nicolas Lunel, Jean-François Cabre
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Patent number: 11873783Abstract: A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.Type: GrantFiled: April 11, 2023Date of Patent: January 16, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Brice Marie Yves Emile Le Pannerer, Jean-François Cabre, Nicolas Camille Claude Curlier, Lucas Arthur Pflieger
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Publication number: 20230265814Abstract: A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.Type: ApplicationFiled: April 11, 2023Publication date: August 24, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Brice Marie Yves Emile LE PANNERER, Jean-François CABRE, Nicolas Camille Claude CURLIER, Lucas Arthur PFLIEGER
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Publication number: 20230250962Abstract: Annular combustion chamber for an aircraft turbomachine, said chamber having two coaxial annular walls, an inner annular wall and an outer annular wall, respectively, which are connected upstream by an annular bottom wall of the chamber, wherein an injection device passes through an axis and comprises an air injection system and a frustoconical bowl which is flared downstream and has air passage openings, the chamber further having an annular deflector placed downstream of the bottom wall substantially parallel to the latter; and wherein the air injection system, the bottom wall, the deflector and the bowl are integrally formed.Type: ApplicationFiled: July 2, 2021Publication date: August 10, 2023Inventors: Haris Musaefendic, Romain Nicolas Lunel, Jean-François Cabre
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Patent number: 11686274Abstract: A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.Type: GrantFiled: May 28, 2020Date of Patent: June 27, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Brice Marie Yves Emile Le Pannerer, Jean-François Cabre, Nicolas Camille Claude Curlier, Lucas Arthur Pflieger
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Publication number: 20220275941Abstract: A combustion chamber for an aircraft turbomachine includes an annular chamber end wall structure, an annular row of main injection systems mounted in the chamber end wall structure and configured to deliver a sheet of fuel, including a central recirculation region and a corner recirculation region around the central recirculation region, and secondary injection systems each configured to inject an additional flow of air and fuel directly into a corresponding corner recirculation region.Type: ApplicationFiled: July 27, 2020Publication date: September 1, 2022Inventors: Julien Marc Matthieu LEPAROUX, Jean-François CABRE, Haris MUSAEFENDIC, Romain Nicolas LUNEL
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Publication number: 20220252023Abstract: A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.Type: ApplicationFiled: May 28, 2020Publication date: August 11, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Brice Marie Yves Emile LE PANNERER, Jean-François CABRE, Nicolas Camille Claude CURLIER, Lucas Arthur PFLIEGER
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Patent number: 10139110Abstract: A turbomachine combustion chamber, comprises a fuel injector nozzle and an injection system. The injection system comprises a sliding traverse, means for maintaining the sliding traverse and a supporting sole for the sliding traverse. The injection system comprises means for recalling the sliding traverse configured to stress the supporting sole against axial displacements of the sliding traverse relatively to the means for maintaining. The outer connection surface of the injector nozzle and/or at least one portion of the internal centring surface of the sliding traverse narrow in the downstream direction, in such a way as to retain the injector nozzle relatively to the sliding traverse axially in the downstream direction.Type: GrantFiled: September 8, 2016Date of Patent: November 27, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Brice Marie Yves Emile Le Pannerer, Jean-François Cabre, Galadriel Dancie
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Patent number: 9765970Abstract: A combustion chamber module for an aircraft turbomachine, including an annular combustion chamber in which each of primary and dilution ports of an outer annular wall, which is located at least partly in a wake of a fuel injector, has a discharge coefficient higher than that of its homologous port of an inner annular wall. A method for designing such a module includes determining wakes generated by fuel injectors, and then geometrically defining air inlet ports of coaxial walls of the combustion chamber such that an air flow rate actually entering through ports of the outer wall is substantially equal to an air flow rate entering through ports of the inner wall.Type: GrantFiled: October 24, 2012Date of Patent: September 19, 2017Assignee: Safran Aircraft EnginesInventors: Sebastien Alain Christophe Bourgois, Jean-Francois Cabre
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Publication number: 20170067638Abstract: A turbomachine combustion chamber, comprises a fuel injector nozzle and an injection system. The injection system comprises a sliding traverse, means for maintaining the sliding traverse and a supporting sole for the sliding traverse. The injection system comprises means for recalling the sliding traverse configured to stress the supporting sole against axial displacements of the sliding traverse relatively to the means for maintaining. The outer connection surface of the injector nozzle and/or at least one portion of the internal centring surface of the sliding traverse narrow in the downstream direction, in such a way as to retain the injector nozzle relatively to the sliding traverse axially in the downstream direction.Type: ApplicationFiled: September 8, 2016Publication date: March 9, 2017Inventors: Brice Marie Yves Emile LE PANNERER, Jean-François CABRE, Galadriel DANCIE
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Patent number: 9413141Abstract: A spark plug for combustion chamber of a gas turbine engine including: an external body forming ground electrode, intended to be received mainly in a bypass of the combustion chamber; an internal central electrode; and an interposed insulator with clearance between the external body and the internal electrode, is provided. The spark plug terminates in a nose forming portion to be received in the flame tube of the chamber of the combustion chamber, and a semi-conductor element being interposed between the central electrode and the ground electrode at the level of said nose forming portion. The external body includes at least one cooling air inlet which communicates inside the spark plug with at least one outlet arranged at the level of the nose forming portion.Type: GrantFiled: April 12, 2013Date of Patent: August 9, 2016Assignee: SNECMAInventors: Francois Leglaye, Jean-Francois Cabre, David Gino Stifanic
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Publication number: 20150285500Abstract: A combustion chamber module for an aircraft turbomachine, including an annular combustion chamber in which each of primary and dilution ports of an outer annular wall, which is located at least partly in a wake of a fuel injector, has a discharge coefficient higher than that of its homologous port of an inner annular wall. A method for designing such a module includes determining wakes generated by fuel injectors, and then geometrically defining air inlet ports of coaxial walls of the combustion chamber such that an air flow rate actually entering through ports of the outer wall is substantially equal to an air flow rate entering through ports of the inner wall.Type: ApplicationFiled: October 24, 2012Publication date: October 8, 2015Applicant: SNECMAInventors: Sebastien Alain, Christophe Bourgois, Jean-Francois Cabre
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Publication number: 20130327013Abstract: The invention relates to a spark plug for combustion chamber of a gas turbine engine comprising: an external body (1) forming ground electrode, intended to be received mainly in a bypass of the combustion chamber, an internal central electrode (2), an interposed insulator (3) with clearance between the external body (1) and the internal electrode (2), said spark plug terminating in a nose forming portion (5) intended for its part to be received in the flame tube of the chamber of the combustion chamber, a semi-conductor element being interposed between the central electrode and the ground electrode at the level of said nose forming portion, wherein the external body (1) comprises at least one cooling air inlet (6) which communicates inside the spark plug with at least one outlet (8, 9, 10) arranged at the level of the nose forming portion.Type: ApplicationFiled: April 12, 2013Publication date: December 12, 2013Applicant: SNECMAInventors: Francois LEGLAYE, Jean-Francois CABRE, David Gino STIFANIC