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公开(公告)号：US11988112B2
公开(公告)日：2024-05-21
申请号：US18001677
申请日：2021-06-15
IPC分类号： F01D9/02
CPC分类号： F01D9/026 , F05D2220/329 , F05D2240/14
摘要： An aircraft turbomachine having a centrifugal compressor, an annular combustion chamber, an annular casing extending around the chamber and delimiting an annular space (E) in which the chamber is situated, and a heat exchanger. The heat exchanger can include a first circuit supplied with exhaust gas from the turbomachine, and a second circuit connected by first and second volutes respectively to an outlet of the compressor and to the annular space. The first and second volutes can be positioned at an axial distance from one another, and the second volute can be connected to the annular space by a straightener which is situated at least in part outside the casing and which is integrated into an annular connecting pipe which connects the second volute to this casing.
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公开(公告)号：US11846198B2
公开(公告)日：2023-12-19
申请号：US18252278
申请日：2021-11-12
CPC分类号： F01D15/10 , F02C7/275 , F02C7/32 , F05D2220/76 , F05D2260/85
摘要： A turbomachine, particularly for a rotary-wing aircraft, including a gas generator provided with a rotary shaft, a first reversible electric machine, a power turbine rotationally driven by a stream of gas generated by the gas generator, at least one accessory from among an oil pump and a fuel pump, an accessory gearbox comprising a gear train configured to drive said at least one accessory, and a second electric machine.
The second electric machine is reversible, said first electric machine is mechanically coupled to the gas generator, the accessory gearbox and the second electric machine are mechanically coupled to the power turbine, and the turbomachine is devoid of any kinematic coupling between the gear train of the accessory gearbox and the shaft of the gas generator.-
公开(公告)号：US12071853B2
公开(公告)日：2024-08-27
申请号：US18553819
申请日：2022-03-31
CPC分类号： F01D15/12 , B64D27/10 , F02C7/268 , F02C7/32 , F05D2220/76
摘要： A turbomachine including a gas generator endowed with a first shaft, a gear box, at least one reversible electric machine coupled to the gear box, and a free turbine endowed with a second shaft and rotationally driven by a gas stream of the gas generator and at least one accessory coupled to the accessory gear box, wherein the turbomachine includes a first mechanical coupling means configured to mechanically couple said first mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said first mechanical shaft from the accessory gear box in a second configuration, and a second mechanical coupling means configured to mechanically couple said second mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said second mechanical shaft from the accessory gear box in a second configuration.
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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
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.
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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
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.
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公开(公告)号：US11777370B2
公开(公告)日：2023-10-03
申请号：US17597786
申请日：2020-07-24
申请人： SAFRAN HELICOPTER ENGINES , SAFRAN
CPC分类号： H02K7/1823 , B64D27/02 , B64D27/10 , B64D27/24 , F02C6/20 , H02K21/14 , B64D2027/026 , F05D2220/76
摘要： An aeronautical turbogenerator for hybrid electric propulsion includes a heat engine and an electrical generator coupled mechanically to the heat engine and including a rotor and a stator, the rotor extending in an axial direction and including a common magnetized rotor yoke comprising a plurality of permanent magnets defining at least three axially distributed movable annular rings, the stator including a magnetic stator yoke comprising a plurality of electrical windings defining axially and/or circumferentially distributed stationary sectors, at least two stationary sectors, one of which covers axially at least two movable annular rings, being arranged angularly so as not to mutually coincide and thus deliver at least two distinct and independent voltage levels.
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