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公开(公告)号：EP4227496A1
公开(公告)日：2023-08-16
申请号：EP22156136.8
申请日：2022-02-10
发明人： WU, Eric , VERMEIREN, Sébastien , SHORTTE, Maurice , MIRANDA, Pedro , LAVEAU, Benoit , RÖSICK, Joel
IPC分类号： F01D25/02 , F02C7/047 , F01D25/04 , F01D25/06 , F01D25/36 , F01D15/10 , F01D5/08 , F01D5/10 , B64D27/24
摘要： The present invention provides an electric aircraft engine. It also provides an aircraft, comprising such an electric aircraft engine. According to a first aspect of the present invention, the electric aircraft engine comprises an electric motor with a rotor configured to be driven in rotation about a central axis, a fan having a central yoke mechanically coupled to the rotor for driving the fan and a plurality of fan blades projecting radially outwardly from the yoke, and an anti-icing and/or de-icing system to remove and/or prevent built-up of ice on the fan, said anti-icing and/or de-icing system comprising an electrical power source and a wireless energy transfer system for wirelessly transferring energy for anti-icing and/or de-icing from the electrical power source to the fan. According to a second aspect of the present invention, the electric aircraft engine comprises an electric motor with a rotor configured to be driven in rotation about a central axis, a fan having a central yoke mechanically coupled to the rotor for driving the fan and a plurality of fan blades projecting radially outwardly from the yoke, an anti-icing and/or de-icing control unit configured to deliberately induce electric motor losses and thereby increase temperature and/or vibrations in the electric motor, and a thermal and/or vibrational conduction path for conducting thermal and/or vibrational energy for anti-icing and/or de-icing from the electric motor to the fan.
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公开(公告)号：EP4420986A3
公开(公告)日：2024-10-30
申请号：EP24188514.4
申请日：2022-02-10
发明人： WU, Eric , VERMEIREN, Sébastien , SHORTTE, Maurice , MIRANDA, Pedro , LAVEAU, Benoit , RÖSICK, Joel
IPC分类号： F01D25/02 , F02C7/047 , F01D25/04 , F01D25/06 , F01D25/36 , F01D15/10 , F01D5/08 , F01D5/10 , B64D27/24
摘要： The present invention provides an electric aircraft engine. It also provides an aircraft, comprising such an electric aircraft engine. According to both a first aspect and a second aspect of the present invention, the electric aircraft engine comprises an electric motor with a rotor configured to be driven in rotation about a central axis, a fan having a central yoke mechanically coupled to the rotor for driving the fan and a plurality of fan blades projecting radially outwardly from the yoke, and an anti-icing and/or de-icing system to remove and/or prevent built-up of ice on the fan, said anti-icing and/or de-icing system comprising an electrical power source and a wireless energy transfer system for wirelessly transferring energy for anti-icing and/or de-icing from the electrical power source to the fan. In the first aspect of the present invention, the electric motor comprises an electromagnetically excited resolver for determining an angular position of the rotor of the electric motor, and an anti-icing and/or de-icing control unit is configured to induce losses by adding a high-power, highfrequency component of current and flux to the normal excitation signals of the resolver, thereby heating up the resolver. In the second aspect of the present invention, the wireless energy transfer system consists of two coils, a transmitter coil electrically coupled to the electrical power source and a receiver coil thermally connected to the fan, the energy being transmitted wirelessly by induction via an air gap from the transmitter coil to the receiver coil.
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3.发明公开
公开(公告)号：EP4450394A1
公开(公告)日：2024-10-23
申请号：EP23168656.9
申请日：2023-04-19
发明人： WIEGAND, Daniel , ROESICK, Joel , ANGERER, Martin , LAVEAU, Benoit , BESTHORN, Florian , VERMEIREN, Sebastien , MIRANDA, Pedro Henrique Silva
IPC分类号： B64D27/24
摘要： According to the present invention, at least one power electronic component (3a, 3b, 4a, 4b, 5a, 5b, 6, 7, 8) is embedded in at least one of a plurality of vanes (11) of an electric aircraft engine (1). This enables cooling of the at least one power electronic component (in particular MOSFETs of an inverter for driving an electric motor of the electric aircraft engine) without additional air or liquid cooling equipment (such as cooling fins or radiators), thus reducing mass and thermal losses.
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公开(公告)号：EP4420986A2
公开(公告)日：2024-08-28
申请号：EP24188514.4
申请日：2022-02-10
发明人： WU, Eric , VERMEIREN, Sébastien , SHORTTE, Maurice , MIRANDA, Pedro , LAVEAU, Benoit , RÖSICK, Joel
IPC分类号： B64D27/24
CPC分类号： F01D25/02 , F02C7/047 , F01D25/04 , F01D25/06 , F01D25/36 , F01D15/10 , F01D5/08 , F01D5/10 , F05D2270/06120130101 , F05D2220/7620130101 , B64D27/24 , Y02T50/60 , B64D15/12
摘要： The present invention provides an electric aircraft engine. It also provides an aircraft, comprising such an electric aircraft engine. According to both a first aspect and a second aspect of the present invention, the electric aircraft engine comprises an electric motor with a rotor configured to be driven in rotation about a central axis, a fan having a central yoke mechanically coupled to the rotor for driving the fan and a plurality of fan blades projecting radially outwardly from the yoke, and an anti-icing and/or de-icing system to remove and/or prevent built-up of ice on the fan, said anti-icing and/or de-icing system comprising an electrical power source and a wireless energy transfer system for wirelessly transferring energy for anti-icing and/or de-icing from the electrical power source to the fan. In the first aspect of the present invention, the electric motor comprises an electromagnetically excited resolver for determining an angular position of the rotor of the electric motor, and an anti-icing and/or de-icing control unit is configured to induce losses by adding a high-power, highfrequency component of current and flux to the normal excitation signals of the resolver, thereby heating up the resolver. In the second aspect of the present invention, the wireless energy transfer system consists of two coils, a transmitter coil electrically coupled to the electrical power source and a receiver coil thermally connected to the fan, the energy being transmitted wirelessly by induction via an air gap from the transmitter coil to the receiver coil.
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公开(公告)号：EP4167441A1
公开(公告)日：2023-04-19
申请号：EP21202985.4
申请日：2021-10-15
摘要： Electric engine (10), in particular electric aircraft engine, comprising a ring-shaped stator core (12) and a rotor rotatably supported within the stator core (12), wherein the stator core (12) has a plurality of radially inward-facing teeth (14) and a plurality of windings (16) wound around each of the teeth (14) to form individual coils (18), wherein the windings (16) of each coil (18) have active portions (22) between adjacent teeth (14) and end winding portions (20) arranged at axial ends of each teeth (14), and wherein at least one thermally conductive heat extraction component (26) is provided at the end winding portions (20).
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