Patents by Inventor Camel SERGHINE

Camel SERGHINE 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).

  • Publication number: 20220190686
    Abstract: An assembly including a winding and a cooler in contact with conductors of the winding, the cooler including a container forming a heat dissipator and including a phase change material having the ability to absorb a surplus quantity of heat when the conductors of the winding are subject to an increase in their current density and the heat dissipator is composed of at least two hollow parts separate and nestable with one another and intended to house the phase change material.
    Type: Application
    Filed: February 19, 2020
    Publication date: June 16, 2022
    Applicants: SAFRAN, SAFRAN HELICOPTER ENGINES
    Inventors: Sabrina AYAT, Camel SERGHINE, Thomas KLONOWSKI
  • Publication number: 20220177147
    Abstract: A hybrid propulsion system for a multi-rotor rotary-wing aircraft, including: an internal combustion engine, an electric machine coupled to the internal combustion engine, a rectifier connected to the electric machine, a converter, an electric network connecting the rectifier to the converter, electric motors connected to the converter, rotary-blade assemblies coupled to the electric motors, wherein the system includes: a detector configured to detect a reduction in a demand for electrical power within the system to below a predetermined value, a bypass circuit configured to bypass the electric machine when the detector detects a reduction in the demand for electrical power.
    Type: Application
    Filed: April 10, 2020
    Publication date: June 9, 2022
    Inventors: Thomas KLONOWSKI, Lois Pierre Denis VIVE, Camel SERGHINE
  • Publication number: 20220153423
    Abstract: A hybrid/electric propulsion architecture for a multi-rotor rotary wing aircraft, including an electricity generator driven by an internal combustion engine, and configured to operate in motor mode, a rectifier configured to convert an alternating current delivered by the electricity generator into direct current, an electrical network including a high voltage direct current (HVDC) bus, electrical energy storage means connected to the electrical network, during electrical energy regeneration on the HVDC bus, depending on the state of charge of the storage means: the storage means are configured to recover electrical energy, the storage means and the rectifier are configured to recover electrical energy, and the electricity generator operating in motor mode is configured to recover electrical energy.
    Type: Application
    Filed: February 24, 2020
    Publication date: May 19, 2022
    Inventors: Thomas KLONOWSKI, Thomas Michel Andre Gerard BARRACO, Camel SERGHINE
  • Patent number: 11316394
    Abstract: The invention relates to an electrical machine comprising a stator (1) and a rotor (2) designed to be rotated in relation to each other, said rotor (2) or said stator comprising a plurality of permanent magnets (5), at least one permanent magnet comprising at least one fluid-propagation channel (10) extending longitudinally inside the permanent magnet, the propagation channel comprising a fluid inlet and a fluid outlet, the fluid inlet being bell-mouthed and oriented in a preferential direction of rotation of the permanent magnet.
    Type: Grant
    Filed: November 14, 2018
    Date of Patent: April 26, 2022
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Klonowski, Camel Serghine, Jean-Luc Charles Gilbert Frealle, Sebastien Combebias, Jean-Julien Camille Vonfelt
  • Publication number: 20220085706
    Abstract: The present invention relates to an electric machine for an aircraft, comprising a stator and a rotor that is rotationally mobile with respect to the stator, the rotor or the stator comprising a plurality of permanent magnets, the machine comprising a device for demagnetising a permanent magnet, suitable for achieving a temporary increase in the temperature of the permanent magnet, in order to limit, during the temporary increase in temperature, an exciting magnetic flux generated by the permanent magnet. The present invention furthermore relates to an assembly comprising an assembly comprising such an electric machine and a hot-fluid source suitable for delivering hot fluid to the demagnetising device of the electric machine. The hot-fluid source may be a gas stream of a turbine engine.
    Type: Application
    Filed: December 19, 2019
    Publication date: March 17, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Camel SERGHINE, Thomas KLONOWSKI, Loïs Pierre Denis VIVE
  • Patent number: 11264854
    Abstract: An electric machine includes a stator and a rotor configured to be driven in rotation in relation to one another. The rotor includes a plurality of permanent magnets, and the stator further includes a magnetic circuit including poles extending toward the rotor. The machine includes windings of conducting elements around each pole and at least one heat sink arranged inside a conducting element and/or between the conducting elements. The heat sink includes a phase change material.
    Type: Grant
    Filed: May 3, 2018
    Date of Patent: March 1, 2022
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Klonowski, Camel Serghine
  • Publication number: 20210376677
    Abstract: The invention relates to an electrical machine comprising a stator (1) and a rotor (2) designed to be rotated in relation to each other, said rotor (2) or said stator comprising a plurality of permanent magnets (5), at least one permanent magnet comprising at least one fluid-propagation channel (10) extending longitudinally inside the permanent magnet, the propagation channel comprising a fluid inlet and a fluid outlet, the fluid inlet being bell-mouthed and oriented in a preferential direction of rotation of the permanent magnet.
    Type: Application
    Filed: November 14, 2018
    Publication date: December 2, 2021
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas KLONOWSKI, Camel SERGHINE, Jean-Luc Charles Gilbert FREALLE, Sebastien COMBEBIAS, Jean-Julien Camille VONFELT
  • Patent number: 11085376
    Abstract: The invention concerns an assembly comprising: a fuel supply circuit (15, 15a, 15b) configured to supply fuel to a turbine heat engine, an electronic module (14, 14a, 14b), a power source (13, 13a, 13b) for supplying power to the electronic module (14, 14a, 14b), and a heat exchanger (16, 16a, 16b) positioned to allow a flow of heat from the electronic module (14, 14a, 14b) to the fuel supply circuit (15, 15a, 15b), the assembly being characterised in that the electronic module (14, 14a, 14b) comprises a phase-change material (PCM), configured to change state when the temperature of same reaches a predetermined phase-change temperature (Tf).
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: August 10, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Klonowski, Camel Serghine
  • Publication number: 20210139154
    Abstract: In the field of multi-rotor rotary-wing aircraft a propulsion system for such an aircraft includes a reconfigurable electric network for supplying the electric motors driving the rotors. The system includes: a supply source, a supply bus connected to the supply source, at least four drive units each including an electric motor and its control circuit, and an electrical ring network including: an electrical line which is interrupted at each drive unit and whose ends are connected to the supply bus, and, for each drive unit, a first switch and a second switch that are connected between the control circuit and the electrical line, on either side of the interruption.
    Type: Application
    Filed: March 25, 2019
    Publication date: May 13, 2021
    Inventors: Thomas KLONOWSKI, Thomas BARRACO, Camel SERGHINE
  • Patent number: 10858999
    Abstract: The invention relates to a removable reactivation pack for a turboshaft engine of a helicopter, comprising a gas generator equipped with a drive shaft, said turboshaft engine (6) being capable of operating in at least one standby mode during a stable flight of the helicopter, said removable pack comprising: a removable gearbox comprising a gearbox output shaft; controlled means for rotating said gearbox output shaft, referred to as reactivation means of said turboshaft engine; mechanical means for reversibly coupling said gearbox output shaft to said drive shaft of said gas generator.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: December 8, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick Marconi, Romain Thiriet, Camel Serghine, Caroline Seve, Pierre Darfeuil
  • Patent number: 10753280
    Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.
    Type: Grant
    Filed: September 29, 2014
    Date of Patent: August 25, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Vincent Poumarede, Camel Serghine
  • Patent number: 10686358
    Abstract: 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: Grant
    Filed: September 1, 2016
    Date of Patent: June 16, 2020
    Assignee: Safran Helicopter Engines
    Inventors: Camel Serghine, Thomas Klonowski, Stéphane Beddok, Stéphane Richard
  • Patent number: 10662875
    Abstract: A propulsion unit, notably for an aircraft, including a turbomachine; a propeller that can be selectively coupled to the turbomachine; a rotary electrical machine able to drive at least the turbomachine, and selective coupling of the rotary electric machine to the propeller and/or the turbomachine that is able to couple only the propeller to the rotary electrical machine during a defined stage of operation of the propulsion unit and that is able to couple or not couple the rotary electric machine to a gas generator and/or a free turbine of the turbomachine.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: May 26, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Olivier Lafargue, Didier Chartrain, Camel Serghine
  • Publication number: 20200076262
    Abstract: An electric machine including a stator and a rotor configured to be driven in rotation in relation to one another, the rotor including a plurality of permanent magnets, the stator further including a magnetic circuit including poles extending toward the rotor, the machine including windings of conducting elements around each pole and at least one heat sink arranged inside a conducting element and/or between the conducting elements, the heat sink comprising a phase change material.
    Type: Application
    Filed: May 3, 2018
    Publication date: March 5, 2020
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas KLONOWSKI, Camel SERGHINE
  • Publication number: 20190352001
    Abstract: Propulsion system (8) for a single-engine helicopter (1), comprising: a main engine (9) connected to a front drive shaft (5) and a rear drive shaft (7), respectively, suitable for driving a main gearbox (4) referred to as MGB (4) and a tail gearbox (6) referred to as TGB (6); ? an assistance device (10) attached to the main engine (9); characterised in that said propulsion system (8) is designed in order that the assistance device (10) can mechanically drive the TGB and MGB (6, 4) by introducing power to the rear drive shaft (7).
    Type: Application
    Filed: February 5, 2018
    Publication date: November 21, 2019
    Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN HELICOPTER ENGINES
    Inventors: Romain THIRIET, Camel SERGHINE, Alphonse PUERTO, Christian SARRAT
  • Publication number: 20190338709
    Abstract: The invention relates to an auxiliary system for mechanically driving a relay shaft (8) of a helicopter propulsion system, comprising: a hydraulic motor (7), mechanically connected to said relay shaft (8); a hydraulic circuit (10) for supplying a pressurised liquid to said hydraulic motor(7) a controlled, fast-opening hydraulic valve (11) arranged on the hydraulic circuit (10); a pyro-hydraulic storage unit (9) driven by a control unit (12) and connected to said hydraulic valve (11), said pyro-hydraulic storage unit (9)comprising: an enclosure (20) including a piston (16) that defines a main compartment (17) having at least one solid propellant cartridge (19) and a compartment (18) for a liquid supply; an ignition charge (25) connected to said main compartment (17) and suitable for initiating the combustion of at least one solid propellant cartridge (19) upon receiving a command from said control unit (12).
    Type: Application
    Filed: April 24, 2017
    Publication date: November 7, 2019
    Inventors: Romain THIRIET, Camel SERGHINE, Guillaume DEMEZON
  • Publication number: 20190309687
    Abstract: The invention concerns an assembly comprising: a fuel supply circuit (15, 15a, 15b) configured to supply fuel to a turbine heat engine, an electronic module (14, 14a, 14b), a power source (13, 13a, 13b) for supplying power to the electronic module (14, 14a, 14b), and a heat exchanger (16, 16a, 16b) positioned to allow a flow of heat from the electronic module (14, 14a, 14b) to the fuel supply circuit (15, 15a, 15b), the assembly being characterised in that the electronic module (14, 14a, 14b) comprises a phase-change material (PCM), configured to change state when the temperature of same reaches a predetermined phase-change temperature (Tf).
    Type: Application
    Filed: June 12, 2017
    Publication date: October 10, 2019
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas KLONOWSKI, Camel SERGHINE
  • Patent number: 10422285
    Abstract: Emergency start-up device for a turboshaft engine of a helicopter, comprising: a hydraulic motor which is mechanically connected to said turboshaft engine; a hydropneumatic store which is connected to said hydraulic motor by a hydraulic circuit for supplying pressurized liquid to said hydraulic motor; and a hydraulic valve which has controlled quick opening, arranged on the hydraulic circuit between said store and said hydraulic motor, and is suitable for being placed on command at least in an open position in which the liquid can supply said hydraulic motor, or in a closed position in which said hydraulic motor is no longer supplied with pressurized liquid.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: September 24, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Bertrand Moine, Camel Serghine, François Porel
  • Patent number: 10415482
    Abstract: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator, characterized in that it comprises a device (40) for controlled mechanical coupling of said gas generator (5) and said free turbine (6) that is capable of connecting said gas generator (5) and said free turbine (6) mechanically and on demand as soon as the rotational speed of said gas generator (5) reaches a predetermined threshold speed.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: September 17, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick Marconi, Romain Thiriet, Camel Serghine
  • Patent number: 10253699
    Abstract: A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: April 9, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Jean-Michel Bazet, Camel Serghine, Patrick Marconi, Jérôme Irigoyen, Stephen Langford