Patents by Inventor Stéphane Beddok
Stéphane Beddok 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: 10766629Abstract: An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.Type: GrantFiled: March 20, 2015Date of Patent: September 8, 2020Assignees: SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITSInventors: Fabien Mercier-Calvairac, Stéphane Beddok, Stéphane Chevalier, Sophie Humbert
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Patent number: 10686358Abstract: The invention relates to the field of magnetohydrodynamic generators, and more precisely to such a generator (10) comprising a working fluid flow passage (11) that is defined by a first wall (12) and a second wall (13), an ionizing device (14) for ionizing the working fluid, a pair of arms (15), each connecting together the first and second walls (12, 13) downstream from said ionizing device (14) so as to define, within the flow passage (11), a channel (16) between said arms (15) and said walls (12, 13), said channel (16) being arranged to be traversed by a portion of the working fluid after it has been ionized, a magnet for generating a magnetic field (B) oriented in a direction that is perpendicular to the flow of the working fluid through the channel (16) defined by the pair of arms (15) and said walls (12, 13), and at least one pair of electrodes (17), each of the electrodes (17) in each pair being arranged on a respective side of the channel (16) defined by the pair of arms (15) and said walls (12, 13),Type: GrantFiled: September 1, 2016Date of Patent: June 16, 2020Assignee: Safran Helicopter EnginesInventors: Camel Serghine, Thomas Klonowski, Stéphane Beddok, Stéphane Richard
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Patent number: 10214296Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low DC voltage onboard network (7) for supplying helicopter equipment during flight, characterized in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).Type: GrantFiled: March 20, 2015Date of Patent: February 26, 2019Assignee: SAFRAN HELICOPTER ENGINESInventors: Fabien Mercier-Calvairac, Sophie Humbert, Stephane Beddok
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Publication number: 20180254693Abstract: The invention relates to the field of magnetohydrodynamic generators, and more precisely to such a generator (10) comprising a working fluid flow passage (11) that is defined by a first wall (12) and a second wall (13), an ionizing device (14) for ionizing the working fluid, a pair of arms (15), each connecting together the first and second walls (12, 13) downstream from said ionizing device (14) so as to define, within the flow passage (11), a channel (16) between said arms (15) and said walls (12, 13), said channel (16) being arranged to be traversed by a portion of the working fluid after it has been ionized, a magnet for generating a magnetic field (B) oriented in a direction that is perpendicular to the flow of the working fluid through the channel (16) defined by the pair of arms (15) and said walls (12, 13), and at least one pair of electrodes (17), each of the electrodes (17) in each pair being arranged on a respective side of the channel (16) defined by the pair of arms (15) and said walls (12, 13),Type: ApplicationFiled: September 1, 2016Publication date: September 6, 2018Applicant: Safran Helicopter EnginesInventors: Camel SERGHINE, Thomas KLONOWSKI, Stéphane BEDDOK, Stéphane RICHARD
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Patent number: 9982758Abstract: A transmission assembly for an aircraft, and a helicopter including such an assembly for controlling independently the speed of rotation of an engine and of a torque receiver. According to the invention, the assembly comprises a first inlet shaft (10a) configured to receive torque from a first engine (10), an outlet shaft (60a) configured to transmit torque to a torque receiver (60), a first transmission member (20) having at least two degrees of freedom and comprising first, second, and third movable portions, a first reversible electrical regulator machine (30), and a first reversible electrical balancing machine (40), wherein the inlet shaft (10a) is coupled to the first movable portion, the outlet shaft (60a) is coupled to the second movable portion, the first electrical regulator machine (30) is coupled to the third movable portion, and the first electrical balancing machine (40) is coupled in series with the inlet shaft or the outlet shaft (60a).Type: GrantFiled: March 20, 2015Date of Patent: May 29, 2018Assignee: SAFRAN HELICOPTER ENGINESInventors: Stéphane Beddok, Jean-Michel Bazet
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Publication number: 20170175856Abstract: A transmission assembly for an aircraft, and a helicopter including such an assembly for controlling independently the speed of rotation of an engine and of a torque receiver. According to the invention, the assembly comprises a first inlet shaft (10a) configured to receive torque from a first engine (10), an outlet shaft (60a) configured to transmit torque to a torque receiver (60), a first transmission member (20) having at least two degrees of freedom and comprising first, second, and third movable portions, a first reversible electrical regulator machine (30), and a first reversible electrical balancing machine (40), wherein the inlet shaft (10a) is coupled to the first movable portion, the outlet shaft (60a) is coupled to the second movable portion, the first electrical regulator machine (30) is coupled to the third movable portion, and the first electrical balancing machine (40) is coupled in series with the inlet shaft or the outlet shaft (60a).Type: ApplicationFiled: March 20, 2015Publication date: June 22, 2017Applicant: SAFRAN HELICOPTER ENGINESInventors: Stéphane BEDDOK, Jean-Michel BAZET
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Publication number: 20170152055Abstract: An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.Type: ApplicationFiled: March 20, 2015Publication date: June 1, 2017Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITSInventors: Fabien Mercier-Calvairac, Stéphane Beddok, Stéphane Chevalier, Sophie Humbert
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Publication number: 20170096233Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low DC voltage onboard network (7) for supplying helicopter equipment during flight, characterised in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).Type: ApplicationFiled: March 20, 2015Publication date: April 6, 2017Inventors: Fabien MERCIER-CALVAIRAC, Sophie HUMBERT, Stephane BEDDOK