Patents by Inventor Sebastien Christophe CHALAUD
Sebastien Christophe CHALAUD 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: 11466625Abstract: A method for controlling the fuel injection of a turbine engine using a fuel supply circuit. The supply circuit includes a pilot injection line and a main injection line. During a transition of the supply distribution between the pilot injection line and the main supply line, the method includes the following steps: a) determining at least a minimum value to be maintained for a pressure value; b) determining at least one hydraulic quantity of the supply circuit; c) based on the determined hydraulic quantity of the supply circuit, calculating a calculated fuel supply distribution value corresponding to the minimum value to be maintained; and switching the fuel supply distribution to the calculated fuel distribution value.Type: GrantFiled: December 21, 2018Date of Patent: October 11, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Mohammed-Lamine Boutaleb, Sebastien Christophe Chalaud, Gwenole Yann Le Pache
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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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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: 10934889Abstract: A feed system for feeding lubricating oil to members of a turbine engine including a reduction gearbox, the feed system including a nonpositive-displacement pump device for connecting upstream to an oil tank and driven in rotation at a speed that is not correlated with an operating speed of the turbine engine; a separator node connected to the outlet of the nonpositive-displacement pump device; a first delivery branch for lubricating the RGB connected to the nonpositive-displacement pump device via the separator node; a second delivery branch for lubricating other members connected to the nonpositive-displacement pump device via the separator node, the second delivery branch including a positive-displacement pump; and at least one fluid metering device having a metering slot fed by the nonpositive-displacement pump device via the separator node for the purpose of feeding the RGB.Type: GrantFiled: November 18, 2016Date of Patent: March 2, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventor: Sebastien Christophe Chalaud
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Patent number: 10890117Abstract: A fluid supply system (1) for turbine engine, includes a high pressure volumetric pump (4), a fluid metering device (6) and a control valve (8) configured to vary the flow rate of fluid in a bypass circuit (14) so as to regulate the pressure difference between an input and an output of the metering device (6). The control valve (8) includes an obturator, the variable position of which is measured by a sensor (20). An electronic regulation system (3) compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (14). The flow rate of the high pressure pump (4) is commanded so that the measured position of the obturator adapts to the position set-point.Type: GrantFiled: June 22, 2018Date of Patent: January 12, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Christophe Chalaud, Pierre Charles Mouton
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Patent number: 10837317Abstract: A bypass turbojet engine including a low pressure shaft supported by at least two low pressure bearings, a high pressure shaft supported by at least two high pressure bearings, a fan shaft supported by at least two fan bearings, a reduction system coupling the low pressure shaft, with the fan shaft, enclosures housing the low pressure bearings, the high pressure bearings, the fan bearings and the reduction system, and a lubrication assembly including a closed oil circuit configured to supply oil to the enclosures in order to cool the bearings and the reduction system and at most five recovery pumps configured to recover oil from the enclosures.Type: GrantFiled: March 15, 2017Date of Patent: November 17, 2020Assignee: Safran Aircraft EnginesInventors: Romain Guillaume Cuvillier, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Sebastien Christophe Chalaud, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
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Patent number: 10823074Abstract: A supply system for supplying a turbomachine with fluid. The supply system includes at least one centrifugal pump and a fluid recirculation branch. The fluid recirculation branch includes an inlet situated downstream of the centrifugal pump and an outlet situated upstream of the centrifugal pump or fluidically connected with a node situated upstream of the centrifugal pump, in such a way that at least one portion of the fluid circulates in the centrifugal pump. The fluid recirculation branch includes a valve situated between the inlet and the outlet, the valve including a shutter configured to open/close as a function of the temperature of the fluid.Type: GrantFiled: October 21, 2016Date of Patent: November 3, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventor: Sebastien Christophe Chalaud
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Patent number: 10683774Abstract: An oil tank for a turbine engine comprising a closed enclosure having the shape of an arc of circle adapted to receive oil, with the enclosure having a lower portion and an upper portion at a distance from each other, and an oil level control device in the enclosure, wherein the oil level control device comprises a first sensor positioned in the lower portion of the enclosure so as to control the oil level, and a second sensor separate from the first sensor and positioned in the upper portion of the enclosure so as to control the oil level.Type: GrantFiled: November 27, 2017Date of Patent: June 16, 2020Assignee: Safran Aircraft EnginesInventors: Sébastien Christophe Chalaud, Lise Jeanine Léonie Domecq, Yves Emprin
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Patent number: 10392952Abstract: A guide vane for a dual flow aircraft turbine engine, the aerodynamic part of the vane including an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. A heat conduction matrix is lodged in the duct, and presents main heat transfer wings extending parallel to the direction, and laid out in staggered rows.Type: GrantFiled: March 29, 2017Date of Patent: August 27, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cedric Zaccardi, Mohamed-Lamine Boutaleb, Sebastien Christophe Chalaud, Eric Pierre Georges Lemarechal, Thierry Georges Paul Papin
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Patent number: 10378556Abstract: A guide vane for a dual flow aircraft turbine engine includes an aerodynamic part. The aerodynamic part includes an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. The aerodynamic part is embodied as a single piece, and includes heat transfer fins arranged in the duct expanding substantially parallel to a direction of the duct. The fins are spaced from each other depending on the direction of the duct and a transversal direction of the vane, so that at least some of the fins are arranged substantially staggered.Type: GrantFiled: January 11, 2017Date of Patent: August 13, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cedric Zaccardi, Mohamed-Lamine Boutaleb, Sebastien Christophe Chalaud, Eric Pierre Georges Lemarechal, Thierry Georges Paul Papin
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Publication number: 20190101081Abstract: A bypass turbojet engine including a low pressure shaft supported by at least two low pressure bearings, a high pressure shaft supported by at least two high pressure bearings, a fan shaft supported by at least two fan bearings, a reduction system coupling the low pressure shaft, with the fan shaft, enclosures housing the low pressure bearings, the high pressure bearings, the fan bearings and the reduction system, and a lubrication assembly including a closed oil circuit configured to supply oil to the enclosures in order to cool the bearings and the reduction system and at most five recovery pumps configured to recover oil from the enclosures.Type: ApplicationFiled: March 15, 2017Publication date: April 4, 2019Applicant: Safran Aircraft EnginesInventors: Romain Guillaume CUVILLIER, Nils Edouard Romain BORDONI, Michel Gilbert Roland BRAULT, Sebastien Christophe CHALAUD, Guillaume Patrice KUBBIAK, Arnaud Nicolas NEGRI, Nathalie NOWAKOWSKI
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Publication number: 20180372006Abstract: A fluid supply system (1) for turbine engine, includes a high pressure volumetric pump (4), a fluid metering device (6) and a control valve (8) configured to vary the flow rate of fluid in a bypass circuit (14) so as to regulate the pressure difference between an input and an output of the metering device (6). The control valve (8) includes an obturator, the variable position of which is measured by a sensor (20). An electronic regulation system (3) compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (14). The flow rate of the high pressure pump (4) is commanded so that the measured position of the obturator adapts to the position set-point.Type: ApplicationFiled: June 22, 2018Publication date: December 27, 2018Inventors: Sébastien Christophe CHALAUD, Pierre Charles MOUTON
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Publication number: 20180371945Abstract: A feed system for feeding lubricating oil to members of a turbine engine including a reduction gearbox, the feed system including a nonpositive-displacement pump device for connecting upstream to an oil tank and driven in rotation at a speed that is not correlated with an operating speed of the turbine engine; a separator node connected to the outlet of the nonpositive-displacement pump device; a first delivery branch for lubricating the RGB connected to the nonpositive-displacement pump device via the separator node; a second delivery branch for lubricating other members connected to the nonpositive-displacement pump device via the separator node, the second delivery branch including a positive-displacement pump; and at least one fluid metering device having a metering slot fed by the nonpositive-displacement pump device via the separator node for the purpose of feeding the RGB.Type: ApplicationFiled: November 18, 2016Publication date: December 27, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventor: Sebastien Christophe CHALAUD
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Publication number: 20180313271Abstract: A supply system for supplying a turbomachine with fluid. The supply system includes at least one centrifugal pump and a fluid recirculation branch. The fluid recirculation branch includes an inlet situated downstream of the centrifugal pump and an outlet situated upstream of the centrifugal pump or fluidically connected with a node situated upstream of the centrifugal pump, in such a way that at least one portion of the fluid circulates in the centrifugal pump. The fluid recirculation branch includes a valve situated between the inlet and the outlet, the valve including a shutter configured to open/close as a function of the temperature of the fluid.Type: ApplicationFiled: October 21, 2016Publication date: November 1, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventor: Sebastien Christophe CHALAUD
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Publication number: 20180156066Abstract: An oil tank for a turbine engine comprising a closed enclosure having the shape of an arc of circle adapted to receive oil, with the enclosure having a lower portion and an upper portion at a distance from each other, and an oil level control device in the enclosure, wherein the oil level control device comprises a first sensor positioned in the lower portion of the enclosure so as to control the oil level, and a second sensor separate from the first sensor and positioned in the upper portion of the enclosure so as to control the oil level.Type: ApplicationFiled: November 27, 2017Publication date: June 7, 2018Applicant: Safran Aircraft EnginesInventors: Sébastien Christophe Chalaud, Lise Jeanine Léonie Domecq, Yves Emprin
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Publication number: 20170284417Abstract: A guide vane for a dual flow aircraft turbine engine, the aerodynamic part of the vane including an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. A heat conduction matrix is lodged in the duct, and presents main heat transfer wings extending parallel to the direction, and laid out in staggered rows.Type: ApplicationFiled: March 29, 2017Publication date: October 5, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Cedric ZACCARDI, Mohamed-Lamine Boutaleb, Sebastien Christophe Chalaud, Eric Pierre Georges Lemarechal, Thierry Georges Paul Papin
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Publication number: 20170204879Abstract: The invention relates to a guide vane (24) for a dual flow aircraft turbine engine, the aerodynamic part (32) of the vane comprising an inner duct (50a) for lubricant cooling extending in a main direction (52a) and being partly bounded by a pressure side wall (70) and a suction side wall (72) of the vane. According to the invention, the aerodynamic part (32) of the vane is embodied from as a single piece, including also the heat transfer fins (80), arranged in the duct (50a) expanding substantially parallel to the direction (52a), the fins (80) being spaced from each other depending on the direction (52a) as well as a transversal direction (60) of the vane, so that at least some of the fins (80) are arranged substantially staggered.Type: ApplicationFiled: January 11, 2017Publication date: July 20, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Cedric ZACCARDI, Mohamed-Lamine BOUTALEB, Sebastien Christophe CHALAUD, Eric Pierre Georges LEMARECHAL, Thierry Georges Paul PAPIN