Patents by Inventor Christian Sylvain Vessot
Christian Sylvain Vessot 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: 11255295Abstract: Propulsion assembly comprising: an inner casing (13); an outer casing (3); an inter-duct casing (15) delimiting a primary duct (12) between the inner casing (13) and an outer wall (14), and a secondary duct (16) between the outer casing (3) and an outer wall (17); a fan capable of generating an air flow (24) circulating from downstream to upstream in the secondary duct (16); the assembly further comprising: at least one duct (27) for bleeding air from said flow (24), this bleed duct (27) comprising an inlet port (28) in the outer wall (17) and an outlet port (29) in the inner wall (14); an outer flap (30) movable between an open position and a closed position of the inlet port (28); an inner flap (31) movable between an open position and a closed position of the outlet port (29).Type: GrantFiled: October 17, 2017Date of Patent: February 22, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Rodolphe Jacques Gerard Pouyau, Gabriela Philippart, Christian Sylvain Vessot, Marc Patrick Tesniere
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Patent number: 11199108Abstract: The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.Type: GrantFiled: May 24, 2019Date of Patent: December 14, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Romain Jean-Claude Ferrier, Sébastien Christophe Chalaud, Philippe Gérard Chanez, Lauren Davis, Bastien Pierre Verdier, Christian Sylvain Vessot
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Patent number: 11059597Abstract: An aircraft including a fuselage, a lateral support wing (1) and a propulsion assembly (100) mounted under the wing. The wing includes at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream. The propulsion assembly includes a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The offset fans (102, 104) are attached directly to one of the spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (?) with the axis of the fuselage. The two offset fans (102, 104) are axially offset from one another.Type: GrantFiled: September 29, 2016Date of Patent: July 13, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Bruno Albert Beutin, Nicolas Maurice Herve Aussedat, Nicolas Alain Bader, Philippe Gerard Chanez, Gilles Alain Charier, Mathieu Lallia, Lionel Jean Leon Lefranc, Kevin Morgane Lemarchand, Herve Jean Albert Mouton, Nicolas Joseph Sirvin, Ludovic Michael Laurent Toupet, Christian Sylvain Vessot, Nathalie Nowakowski
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Publication number: 20210207494Abstract: The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.Type: ApplicationFiled: May 24, 2019Publication date: July 8, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Romain Jean-Claude FERRIER, Sebastien Christophe CHALAUD, Philippe Gerard CHANEZ, Lauren DAVIS, Bastien Pierre VERDIER, Christian Sylvain VESSOT
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Patent number: 10814989Abstract: An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.Type: GrantFiled: November 11, 2016Date of Patent: October 27, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Christian Sylvain Vessot, Bruno Albert Beutin, Philippe Gérard Chanez, Mathieu Patrick Jean-Louis Lallia
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Patent number: 10518890Abstract: The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane. According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17?) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.Type: GrantFiled: November 8, 2016Date of Patent: December 31, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gerard Chanez, Mathieu Patrick Jean-Louis Lallia, Christian Sylvain Vessot
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Publication number: 20180281978Abstract: The present invention relates to an aircraft comprising a fuselage, a lateral support wing (1) and propulsion assembly (100) mounted under the wing, the wing comprising at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream, and the propulsion assembly comprising a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans (102, 104) are attached directly to one of the said spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (?) with the axis of the fuselage, the two offset fans (102, 104) are axially offset from one another.Type: ApplicationFiled: September 29, 2016Publication date: October 4, 2018Inventors: Bruno Albert BEUTIN, Nicolas Maurice Herve AUSSEDAT, Nicolas Alain BADER, Philippe Gerard CHANEZ, Gilles Alain CHARIER, Mathieu LALLIA, Lionel Jean Leon LEFRANC, Kevin Morgane LEMARCHAND, Herve Jean Albert MOUTON, Nicolas Joseph SIRVIN, Ludovic Michael Laurent TOUPET, Christian Sylvain VESSOT, Nathalie NOWAKOWSKI
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Publication number: 20180135557Abstract: Propulsion assembly comprising: an inner casing (13); an outer casing (3); an inter-duct casing (15) delimiting a primary duct (12) between the inner casing (13) and an outer wall (14), and a secondary duct (16) between the outer casing (3) and an outer wall (17); a fan capable of generating an air flow (24) circulating from downstream to upstream in the secondary duct (16); the assembly further comprising: at least one duct (27) for bleeding air from said flow (24), this bleed duct (27) comprising an inlet port (28) in the outer wall (17) and an outlet port (29) in the inner wall (14); an outer flap (30) movable between an open position and a closed position of the inlet port (28); an inner flap (31) movable between an open position and a closed position of the outlet port (29).Type: ApplicationFiled: October 17, 2017Publication date: May 17, 2018Inventors: Guillaume Rodolphe Jacques Gerard POUYAU, Gabriela PHILIPPART, Christian Sylvain VESSOT, Marc Patrick TESNIERE
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Publication number: 20170137134Abstract: An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.Type: ApplicationFiled: November 11, 2016Publication date: May 18, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Christian Sylvain Vessot, Bruno Albert Beutin, Philippe Gérard Chanez, Mathieu Patrick Jean-Louis Lallia
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Publication number: 20170137135Abstract: The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane. According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17?) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.Type: ApplicationFiled: November 8, 2016Publication date: May 18, 2017Inventors: Philippe Gerard CHANEZ, Mathieu Patrick Jean-Louis LALLIA, Christian Sylvain VESSOT