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公开(公告)号：US11923736B2
公开(公告)日：2024-03-05
申请号：US17416867
申请日：2019-12-19
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Camel Serghine , Thomas Klonowski , Loïs Pierre Denis Vive
CPC classification number: H02K21/028 , B64D27/24 , H02K1/17 , H02K1/27 , H02K9/00
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.
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公开(公告)号：US11876415B2
公开(公告)日：2024-01-16
申请号：US17416867
申请日：2019-12-19
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Camel Serghine , Thomas Klonowski , Loïs Pierre Denis Vive
CPC classification number: H02K21/028 , B64D27/24 , H02K1/17 , H02K1/27 , H02K9/00
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.
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公开(公告)号：US10415482B2
公开(公告)日：2019-09-17
申请号：US15128375
申请日：2015-03-20
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Patrick Marconi , Romain Thiriet , Camel Serghine
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.
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公开(公告)号：US12009732B2
公开(公告)日：2024-06-11
申请号：US17432245
申请日：2020-02-19
Applicant: SAFRAN , SAFRAN HELICOPTER ENGINES
Inventor： Sabrina Ayat , Camel Serghine , Thomas Klonowski
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.
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公开(公告)号：US11891907B2
公开(公告)日：2024-02-06
申请号：US17757529
申请日：2020-12-18
Applicant: SAFRAN HELICOPTER ENGINES , SAFRAN POWER UNITS
Inventor： Camel Serghine , Denis Antoine Julien Real
CPC classification number: F01D25/18 , B64D27/10 , B64D27/24 , F01D15/10 , B64D2027/026 , F05D2220/323 , F05D2220/76 , F05D2260/609
Abstract: A turbogenerator (1) for an aircraft (2) comprising: a turboshaft engine (3); an electric generator (4) comprising a rotor (5) driven mechanically by the turboshaft engine (3) and a stator (6) supported by a housing (7) of the electric generator (4); characterized in that the turbogenerator (1) comprises a static separator (8) for separating an air/oil mixture coming from the turboshaft engine (3), the static separator (8) being positioned around the housing (7) of the electric generator (4).
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Patent Agency Ranking
公开(公告)号：US11827374B2
公开(公告)日：2023-11-28
申请号：US17041093
申请日：2019-03-25
Applicant: SAFRAN , SAFRAN ELECTRICAL & POWER , SAFRAN HELICOPTER ENGINES , SAFRAN POWER UNITS , SAFRAN ELECTRONICS & DEFENSE
Inventor： Thomas Klonowski , Thomas Barraco , Camel Serghine
CPC classification number: B64D35/02 , B64C27/08 , B64D27/24 , H02J7/0063 , B64D2027/026 , B64D2221/00 , B64U30/20
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.
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公开(公告)号：US10054053B2
公开(公告)日：2018-08-21
申请号：US15023216
申请日：2014-09-29
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Romain Thiriet , Vincent Poumarede , Camel Serghine
CPC classification number: F02C7/06 , F01D25/10 , F01D25/18 , F01D25/36 , F02C3/04 , F02C6/18 , F02C7/268 , F05D2220/32 , F05D2220/76 , F05D2240/35 , F05D2260/213 , F05D2260/85 , Y02T50/675
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.
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公开(公告)号：US11085376B2
公开(公告)日：2021-08-10
申请号：US16309137
申请日：2017-06-12
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Thomas Klonowski , Camel Serghine
IPC: F02C7/224 , B64D37/34 , F02C9/26 , H01L25/07 , H01L23/427 , H01L25/16 , H01L23/373 , H01L25/18 , H01L23/498
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).
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公开(公告)号：US10686358B2
公开(公告)日：2020-06-16
申请号：US15756816
申请日：2016-09-01
Applicant: Safran Helicopter Engines
Inventor： Camel Serghine , Thomas Klonowski , Stéphane Beddok , Stéphane Richard
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), said electrodes (17) in each pair being spaced apart from each in a direction that is perpendicular to said magnetic field (B) and to the flow direction of the working fluid through the channel (16) defined by the pair of arms (15) and by said walls (12, 13).
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10.发明授权公开(公告)号：US10253699B2
公开(公告)日：2019-04-09
申请号：US15514320
申请日：2015-09-21
Applicant: Safran Helicopter Engines
Inventor： Romain Thiriet , Jean-Michel Bazet , Camel Serghine , Patrick Marconi , Jérôme Irigoyen , Stephen Langford
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.
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