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1. 发明授权

US11923736B2 Electric machine with device for forcibly demagnetising permanent magnets 有权
公开(公告)号：US11923736B2
公开(公告)日：2024-03-05
申请号：US17416867
申请日：2019-12-19
申请人： SAFRAN HELICOPTER ENGINES
发明人： Camel Serghine , Thomas Klonowski , Loïs Pierre Denis Vive
IPC分类号： H02K21/02 , B64D27/24 , H02K1/17 , H02K1/27 , H02K9/00
CPC分类号： H02K21/028 , B64D27/24 , H02K1/17 , H02K1/27 , H02K9/00
摘要： 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.

2. 发明授权

US11876415B2 Electric machine with device for forcibly demagnetising permanent magnets 有权
公开(公告)号：US11876415B2
公开(公告)日：2024-01-16
申请号：US17416867
申请日：2019-12-19
申请人： SAFRAN HELICOPTER ENGINES
发明人： Camel Serghine , Thomas Klonowski , Loïs Pierre Denis Vive
IPC分类号： H02K21/02 , B64D27/24 , H02K1/17 , H02K1/27 , H02K9/00
CPC分类号： H02K21/028 , B64D27/24 , H02K1/17 , H02K1/27 , H02K9/00
摘要： 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.

3. 发明申请

US20220177144A1 HYBRID PROPULSION UNIT FOR AN AIRCRAFT 有权
公开(公告)号：US20220177144A1
公开(公告)日：2022-06-09
申请号：US17600391
申请日：2020-03-30
申请人： SAFRAN HELICOPTER ENGINES
发明人： Thomas Klonowski , Thomas Bruno Barraco
IPC分类号： B64D27/02 , B64D27/24 , B64C27/08 , B64C27/12 , B60L53/20 , F02B61/00
摘要： A hybrid propulsion unit for an aircraft with multi-rotor rotary wings includes an electrical generator driven by an internal combustion engine, a rectifier configured to convert an AC current sent by the electrical generator into DC current, a DC-AC converter, an electrical network connecting the rectifier to the converter and including a high-voltage DC current bus, electric motors powered by propeller converters coupled to the electric motors, electrical energy storage connected to the electrical network, the electrical storage including at least one primary storage element and at least one secondary storage element.

4. 发明申请

US20220185497A1 METHOD FOR CONTROLLING AN ELECTRICAL POWER SUPPLY NETWORK FOR AN AIRCRAFT 有权
公开(公告)号：US20220185497A1
公开(公告)日：2022-06-16
申请号：US17603202
申请日：2020-04-10
申请人： SAFRAN HELICOPTER ENGINES
发明人： Thomas Barraco , Thomas Klonowski , Vincent Poumarede
IPC分类号： B64D41/00 , H02J7/34
摘要： Methods for controlling an electrical power supply network for an aircraft, include pre-charging at least one capacitor in a normal operating mode when a gas turbine is available, pre-charging the at least one capacitor in a backup operating mode when the gas turbine is not available, and discharging the at least one capacitor at the end of use of the electrical power supply network when the at least one capacitor is charged.

5. 发明授权

US11085376B2 Integration of a phase-change material for limiting the temperature of fuel from an electronic module 有权
公开(公告)号：US11085376B2
公开(公告)日：2021-08-10
申请号：US16309137
申请日：2017-06-12
申请人： SAFRAN HELICOPTER ENGINES
发明人： Thomas Klonowski , Camel Serghine
IPC分类号： F02C7/224 , B64D37/34 , F02C9/26 , H01L25/07 , H01L23/427 , H01L25/16 , H01L23/373 , H01L25/18 , H01L23/498
摘要： 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).

6. 发明授权

US10686358B2 Magnetohydrodynamic generator 有权
公开(公告)号：US10686358B2
公开(公告)日：2020-06-16
申请号：US15756816
申请日：2016-09-01
申请人： Safran Helicopter Engines
发明人： Camel Serghine , Thomas Klonowski , Stéphane Beddok , Stéphane Richard
IPC分类号： H02K44/10 , H02K44/12 , F01D15/10 , H02K44/08 , H02K44/28 , B64C27/04
摘要： 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).

7. 发明授权

US10151246B2 Assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines 有权
公开(公告)号：US10151246B2
公开(公告)日：2018-12-11
申请号：US15129240
申请日：2015-03-26
申请人： SAFRAN HELICOPTER ENGINES
发明人： Vincent Poumarede , Thomas Klonowski , Fabien Mercier-Calvairac , Camel Serghine
IPC分类号： F02C7/00 , F02C7/275 , B64D35/08 , F02C3/10 , F02C3/107 , F02C7/262 , F02C7/36 , F02C9/42 , B64C27/12 , B64D35/02 , F02C7/32 , H02K7/18 , H02K7/20
摘要： An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.

8. 发明授权

US11988097B2 Aircraft power architecture 有权
公开(公告)号：US11988097B2
公开(公告)日：2024-05-21
申请号：US17056292
申请日：2019-05-09
申请人： SAFRAN HELICOPTER ENGINES
发明人： Olivier Lafargue , Thomas Klonowski
IPC分类号： F01D15/10 , B64C27/12 , F02C7/32 , F02C7/36
CPC分类号： F01D15/10 , B64C27/12 , F02C7/32 , F02C7/36 , F05D2220/323 , F05D2220/329 , F05D2220/50 , F05D2220/76
摘要： The invention relates to an aircraft power architecture comprising a power transmission gearbox (12), located in a first compartment (30), a gas turbine (14), located in a second compartment (32) comprising a gas generator (18) and a free turbine (22) connected to the power transmission gearbox (12) by a power shaft (26) of the gas turbine (14), and an accessory gearbox (16), the gas turbine (14) being set into the main transmission gearbox (12), characterized in that the gas turbine (14) comprises a first electric machine (38), and in that the accessory gearbox (16) is placed in the first compartment (30) and comprises a second electric machine (42) configured to supply energy to the accessory equipment and to receive electrical energy transmitted via the first electric machine (38).

9. 发明申请

US20220411081A1 HYBRID PROPULSION CHAIN FOR AN AIRCRAFT COMPRISING AN AUXILIARY MECHANICAL DRIVE SYSTEM 有权
公开(公告)号：US20220411081A1
公开(公告)日：2022-12-29
申请号：US17621561
申请日：2020-07-07
申请人： SAFRAN HELICOPTER ENGINES
发明人： Camel Serghine , Thomas Klonowski , Lois Pierre Denis Vive
IPC分类号： B64D27/24 , B64D35/04 , H02K7/18
摘要： A hybrid propulsion chain for an aircraft, the hybrid propulsion chain comprising a plurality of propulsion rotors connected to an electrical distribution module by a plurality of electrical connections, the electrical distribution module being connected, on the one hand, to a non-propulsion turbine engine via an electrical generation system and, on the other hand, to an electric battery, each propulsion rotor comprising a stator member and at least one rotor shaft which is configured to be rotated with respect to the stator member when the stator member is electrically powered, the hybrid propulsion chain comprising an auxiliary mechanical drive system mechanically connected to the non-propulsion turbine engine, the auxiliary mechanical drive system comprising a plurality of mechanical connections for mechanically rotating at least one rotor shaft of each propulsion rotor.

10. 发明授权

US11264854B2 Electric machine with phase change material for a turbomachine starter/generator 有权
公开(公告)号：US11264854B2
公开(公告)日：2022-03-01
申请号：US16610144
申请日：2018-05-03
申请人： SAFRAN HELICOPTER ENGINES
发明人： Thomas Klonowski , Camel Serghine
IPC分类号： H02K3/24 , H02K1/32 , H02K3/22 , H02K3/28 , H02K9/20
摘要： 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.

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