Patents by Inventor Sebastien Alain Christophe Bourgois
Sebastien Alain Christophe Bourgois 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: 11840994Abstract: The fuel injection conduits in a multipoint device surrounding a so-called pilot central injection device include tubes of circumferential orientation. By separating the injection conduits from each other, it is possible to attribute to them different head losses which compensate the differences in length that the fuel has to travel: a uniform flow of fuel may be hoped for, for each of the injection holes. The tubes are individual but joined to form a crown that is unitary or composed of two almost symmetrical unitary portions, which lends itself well to manufacture by addition of material.Type: GrantFiled: July 22, 2019Date of Patent: December 12, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Alain Christophe Bourgois, Romain Nicolas Lunel, Haris Musaefendic
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Patent number: 11739936Abstract: An injection system for a turbomachine combustion chamber includes a swirler and a mixing bowl. The mixing bowl includes a converging frustoconical portion and a diverging frustoconical portion. The diverging frustoconical portion is connected to the converging frustoconical portion, forming a continuous aerodynamic profile with the converging frustoconical portion. The diverging frustoconical portion is passed through by vortex holes which each includes a circumferential component around a longitudinal axis of the injection system and an axial component along the longitudinal axis of the injection system.Type: GrantFiled: December 18, 2019Date of Patent: August 29, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Alain Christophe Bourgois, Romain Nicolas Lunel, Haris Musaefendic
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Publication number: 20220082259Abstract: An injection system for a turbomachine combustion chamber includes a swirler and a mixing bowl. The mixing bowl includes a converging frustoconical portion and a diverging frustoconical portion. The diverging frustoconical portion is connected to the converging frustoconical portion, forming a continuous aerodynamic profile with the converging frustoconical portion. The diverging frustoconical portion is passed through by vortex holes which each includes a circumferential component around a longitudinal axis of the injection system and an axial component along the longitudinal axis of the injection system.Type: ApplicationFiled: December 18, 2019Publication date: March 17, 2022Inventors: Sébastien Alain Christophe BOURGOIS, Romain Nicolas LUNEL, Haris MUSAEFENDIC
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Patent number: 11268699Abstract: An injection system for a turbine engine annular combustion chamber includes a support configured to support and to center a fuel injector head. The support includes a frustoconical surface connected at its downstream end of smallest diameter to an upstream end of a cylindrical surface. The system further includes a bowl configured to mix air and fuel arranged downstream of the support and at least one axial swirl inducer extending at least in part around the support. Each swirl inducer includes vanes delimiting between them substantially axial channels for the passage of an air flow. The channels open at their upstream ends on said frustoconical surface.Type: GrantFiled: April 10, 2019Date of Patent: March 8, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Alain Christophe Bourgois, Romain Nicolas Lunel, Haris Musaefendic
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Publication number: 20210262665Abstract: An injection system for a turbine engine annular combustion chamber includes a support configured to support and to center a fuel injector head. The support includes a frustoconical surface connected at its downstream end of smallest diameter to an upstream end of a cylindrical surface. The system further includes a bowl configured to mix air and fuel arranged downstream of the support and at least one axial swirl inducer extending at least in part around the support. Each swirl inducer includes vanes delimiting between them substantially axial channels for the passage of an air flow. The channels open at their upstream ends on said frustoconical surface.Type: ApplicationFiled: April 10, 2019Publication date: August 26, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Alain Christophe Bourgois, Romain Nicolas Lunel, Haris Musaefendic
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Publication number: 20200032749Abstract: The fuel injection conduits in a multipoint device surrounding a so-called pilot central injection device include tubes of circumferential orientation. By separating the injection conduits from each other, it is possible to attribute to them different head losses which compensate the differences in length that the fuel has to travel: a uniform flow of fuel may be hoped for, for each of the injection holes. The tubes are individual but joined to form a crown that is unitary or composed of two almost symmetrical unitary portions, which lends itself well to manufacture by addition of material.Type: ApplicationFiled: July 22, 2019Publication date: January 30, 2020Inventors: Sébastien Alain Christophe BOURGOIS, Romain Nicolas LUNEL, Haris MUSAEFENDIC
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Patent number: 10443850Abstract: A combustion chamber for a turbomachine that includes a chamber end wall and a plurality of air and fuel injection systems distributed circumferentially about an axis of the combustion chamber. The combustion chamber includes, associated with each injection system, a guide device for guiding an airflow including at least one wall mounted on the injection system and projecting in the upstream direction, one wall acting as an obstacle to a circumferential flow of air around the axis. The one wall of the guide device for guiding the airflow has a shape substantially defining a quarter of a spheroid the interior volume of which forms a guide scoop for guiding the airflow feeding the combustion chamber.Type: GrantFiled: April 21, 2016Date of Patent: October 15, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sebastien Alain Christophe Bourgois, Romain Nicolas Lunel, Clement Bernard, Frederic Dos Santos, Sebastien Loval
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Patent number: 10109985Abstract: An igniter plug for an aircraft turbomachine includes an external electrode, an internal electrode, as well as a semiconducting body arranged between the external electrode and the internal electrode and set back from these electrodes so as to define an electrical arc forming cavity, the bottom of which is formed by an axial end surface of the semiconducting body. The free end of the external electrode is equipped with at least one scoop for discharging possible fuel residues present in the cavity.Type: GrantFiled: January 30, 2015Date of Patent: October 23, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Joel Yvan Marcel Robert Berton, Sebastien Alain Christophe Bourgois, Jean-Michel Jacques Campion
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Publication number: 20180051881Abstract: A combustion chamber for a turbomachine that includes a chamber end wall and a plurality of air and fuel injection systems distributed circumferentially about an axis of the combustion chamber. The combustion chamber includes, associated with each injection system, a guide device for guiding an airflow including at least one wall mounted on the injection system and projecting in the upstream direction, one wall acting as an obstacle to a circumferential flow of air around the axis. The one wall of the guide device for guiding the airflow has a shape substantially defining a quarter of a spheroid the interior volume of which forms a guide scoop for guiding the airflow feeding the combustion chamber.Type: ApplicationFiled: April 21, 2016Publication date: February 22, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Sebastien Alain Christophe BOURGOIS, Romain Nicolas LUNEL, Clement BERNARD, Frederic DOS SANTOS, Sebastien LOVAL
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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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Patent number: 9581334Abstract: An annular combustion chamber of a turbine engine, the chamber including inner and outer coaxial walls forming two surfaces of revolution, which are connected together upstream by an annular chamber end wall including injection systems passing therethrough, each including an injector and at least one swirler for producing a rotating air stream that mixes downstream with fuel from the injector, and at least one ignition spark plug mounted in an orifice of the outer wall downstream from the injection systems. The spark plug is situated circumferentially between two adjacent injection systems that are configured to produce two air/fuel mixture sheets rotating in opposite directions.Type: GrantFiled: October 22, 2012Date of Patent: February 28, 2017Assignee: SNECMAInventors: Sebastien Alain Christophe Bourgois, Denis Jean Maurice Sandelis
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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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Patent number: 9127841Abstract: Annular combustion chamber (10) to be fitted on a turbomachine and comprising a chamber end wall (22), a plurality of air and fuel injection systems (32) circumferentially distributed around an axis (34) of the combustion chamber (10) and mounted on said chamber end wall (22), and, an air manifold (100) associated with each injection system (32), comprising at least one wall (96, 98) mounted on the chamber end wall (22) and projecting in the upstream direction to form an obstacle to a circumferential airflow around the axis (34) of the combustion chamber (10), and an air inlet opening (88) formed at the upstream end of the air manifold (100) and opening radially outwards from an axis (44) of said injection system.Type: GrantFiled: March 15, 2010Date of Patent: September 8, 2015Assignee: SNECMAInventors: Sebastien Alain Christophe Bourgois, Romain Nicolas Lunel, Thomas Olivier Marie Noel
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Publication number: 20150222097Abstract: The invention relates to an igniter plug (30) for an aircraft turbomachine, comprising an external electrode (34), an internal electrode (36), as well as a semiconducting body (38) arranged between the external electrode and the internal electrode and set back from these electrodes so as to define an electrical arc forming cavity (40), the bottom of which is formed by an axial end surface (42) of the semiconducting body. According to the invention, the end of the external electrode (34) is equipped with at least one scoop (44) for discharging possible fuel residues present in the cavity (40).Type: ApplicationFiled: January 30, 2015Publication date: August 6, 2015Applicant: SNECMAInventors: Joel Yvan Marcel Robert BERTON, Sebastien Alain Christophe BOURGOIS, Jean-Michel Jacques CAMPION
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Patent number: 8955326Abstract: In a fuel injection device at a base of a combustion chamber, a mixing air inlet screw is manufactured with its peripheral holes extending only over a sector of a circle directed towards the air's propagation cone, wherein the remainder of the periphery of the screw is closed. It is then possible to reduce load loss of the injection system while obtaining an improved quality of the mix supplied to the chamber. Such a device can be used in gas turbines fitted with centrifugal compressors and in which the air flow towards the combustion chamber must therefore be made convergent.Type: GrantFiled: May 18, 2010Date of Patent: February 17, 2015Assignee: SNECMAInventors: Sébastien Alain Christophe Bourgois, Didier Hippolyte Hernandez, Matthieu François Rullaud
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Publication number: 20150020501Abstract: An annular combustion chamber of a turbine engine, the chamber including inner and outer coaxial walls forming two surfaces of revolution, which are connected together upstream by an annular chamber end wall including injection systems passing therethrough, each including an injector and at least one swirler for producing a rotating air stream that mixes downstream with fuel from the injector, and at least one ignition spark plug mounted in an orifice of the outer wall downstream from the injection systems. The spark plug is situated circumferentially between two adjacent injection systems that are configured to produce two air/fuel mixture sheets rotating in opposite directions.Type: ApplicationFiled: October 22, 2012Publication date: January 22, 2015Applicant: SNECMAInventors: Sebastien Alain Christophe Bourgois, Denis Jean Maurice Sandelis
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Patent number: 8661829Abstract: An annular shroud (42), having an internal face intended to cover the back end wall (33) of an annular combustion chamber (12) of a turbomachine (14) fitted with a centrifugal compressor, together with an external face opposite said internal face, and where said shroud includes multiple apertures (54) intended to allow fuel injectors (38, 40) supported by said back end wall (33) to pass through, together with multiple bosses (56) which extend as projections on said external face radially towards the interior respectively from the respective radially internal edges (58) of said apertures (54), such that each of said bosses (56) delimits an extension (60) of the corresponding aperture (54) open radially towards the exterior so as to form an air intake scoop.Type: GrantFiled: September 13, 2011Date of Patent: March 4, 2014Assignee: SNECMAInventors: Sebastien Alain Christophe Bourgois, Didier Hippolyte Hernandez
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Publication number: 20130160452Abstract: An annular shroud has an internal face intended to cover the back end wall of an annular combustion chamber of a turbomachine fitted with a centrifugal compressor, together with an external face opposite the internal face. The shroud includes multiple apertures intended to allow fuel injectors supported by the back end wall to pass through. The shroud includes multiple bosses which extend as projections on the external face radially towards the interior respectively from the respective radially internal edges of the apertures. Each of the bosses delimits an extension of the corresponding aperture open radially towards the exterior so as to form an air intake scoop.Type: ApplicationFiled: September 13, 2011Publication date: June 27, 2013Applicant: SNECMAInventors: Sebastien Alain Christophe Bourgois, Didier Hippolyte Hernandez
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Publication number: 20120055164Abstract: Annular combustion chamber (10) to be fitted on a turbomachine and comprising a chamber end wall (22), a plurality of air and fuel injection systems (32) circumferentially distributed around an axis (34) of the combustion chamber (10) and mounted on said chamber end wall (22), and, an air manifold (100) associated with each injection system (32), comprising at least one wall (96, 98) mounted on the chamber end wall (22) and projecting in the upstream direction to form an obstacle to a circumferential airflow around the axis (34) of the combustion chamber (10), and an air inlet opening (88) formed at the upstream end of the air manifold (100) and opening radially outwards from an axis (44) of said injection system.Type: ApplicationFiled: March 15, 2010Publication date: March 8, 2012Applicant: SNECMAInventors: Sebastien Alain, Christophe Bourgois, Romain Nicolas Lunel, Thomas Olivier, Marie Noel
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Publication number: 20120047899Abstract: In a fuel injection device at a base of a combustion chamber, a mixing air inlet screw is manufactured with its peripheral holes extending only over a sector of a circle directed towards the air's propagation cone, wherein the remainder of the periphery of the screw is closed. It is then possible to reduce load loss of the injection system while obtaining an improved quality of the mix supplied to the chamber. Such a device can be used in gas turbines fitted with centrifugal compressors and in which the air flow towards the combustion chamber must therefore be made convergent.Type: ApplicationFiled: May 18, 2010Publication date: March 1, 2012Applicant: SNECMAInventors: Sébastien Alain Christophe Bourgois, Didier Hippolyte Hernandez, Matthieu François Rullaud