Electrical energy receiving system of an electromagnetic induction electrical energy transfer device incorporating at least one cooling system

Abstract

Electrical energy receiving system of an electromagnetic induction electrical energy transfer device incorporating at least one cooling system. The invention relates to an electrical energy receiving system (40) of a contactless electromagnetic induction electrical energy transfer device, the electrical energy receiving system (40) comprising at least one cooling system (50) integrated into at least one of its components. The invention also relates to an aircraft comprising at least one such electrical energy receiving system (40). This solution makes it possible to reduce the temperature rise during energy transfer and to limit the impact on the aircraft's onboard mass due to the addition of the cooling system (50). Figure 4

Description

Title of the invention: Electrical energy receiving system of an electromagnetic induction electrical energy transfer device incorporating at least one cooling system

[0001] The present application relates to an electrical energy receiving system of an electromagnetic induction electrical energy transfer device incorporating at least one cooling system.

[0002] Before takeoff or after landing, an aircraft moves on the ground by taxiing along a taxiway of an airport facility between its parking area and the runway. To move on the ground, the aircraft uses the thrust generated by its propulsion systems and / or by its auxiliary power unit (APU).

[0003] This solution is not optimal because the aircraft consumes energy in the form of fuel stored in its tanks to move on the ground, which leads to increased fuel consumption and the aircraft's onboard mass.

[0004] Document EP4339096 proposes an alternative solution, visible in figures 1 to 3, allowing the aircraft's fuel consumption to be reduced during ground movements.

[0005] As illustrated in [Fig.1], an aircraft 10 comprises a fuselage 12 extending between a front tip 12.1 and a rear tip 12.2, wings 14 connected to the fuselage 12, a front landing gear 16 connected to the fuselage 12 and positioned at or near the front tip 12.1, and two main landing gears 18 connected to the fuselage 12 or to the wings 14.

[0006] The aircraft 10 also includes at least one electric motor 20 configured to drive in rotation at least one wheel of one of the landing gear 16, 18 and at least one electrical power receiver system 22 configured to power the electric motor 20.

[0007] As illustrated in [Fig.2], an airport facility 24 comprises at least one parking area 24.1, at least one runway 24.2 and at least one taxiway 24.3 connecting the parking area 24.1 to the runway 24.2. The airport facility 24 also comprises at least one electrical power-generating system 26 located on the ground S, along the taxiway 24.3.

[0008] In operation, the electrical energy transmitter and receiver systems 26, 22 form an electrical energy transfer device 28 which allows, when the aircraft 10 moves along the ground, transferring electrical energy from the electrical energy emitting system 26 to the electrical energy receiving system 22. As illustrated in [Fig. 3], the electrical energy transfer device 28 is of the contactless type, the electrical energy emitting system 26 present on the ground S being configured to generate an electromagnetic field 30, the electrical energy receiving system 22 being an electromagnetic induction system configured to generate an electric current when positioned in the electromagnetic field 30 generated by the electrical energy emitting system 26. In this case, the electrical energy receiving system 22 comprises at least one winding 32 as well as at least one rectification and regulation system 34 configured to rectify and regulate the current generated by the winding 32.

[0009] The electrical energy receiving system 22 comprises, in addition to the winding 32, at least one support 36 made of plastic, for example, and at least one ferromagnetic element 38 made of ferrite, for example. Depending on one configuration, each ferromagnetic element 38 is a bar or a solid plate.

[0010] The electrical energy transfer device 28 is configured to ensure energy transfer with a high power output on the order of one or more hundred megawatts. During operation, this energy level causes a significant temperature rise that can damage the components of the electrical energy receiving system 22.

[0011] To limit the temperature rise, one solution is to provide several electrical energy transfer devices 28 in order to distribute the transferred power and reduce the temperature rise for each of them. However, this solution is not satisfactory because it leads to an increase in the onboard mass.

[0012] A second solution consists of combining the electrical energy transfer system with a specific cooling system, dedicated solely to cooling, to dissipate the heat generated during energy transfer. As before, this solution is not satisfactory because it leads to an increase in the onboard mass.

[0013] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0014] The invention relates to an electrical energy receiving system of a non-contact electrical energy transfer device by electromagnetic induction, the electrical energy receiving system comprising at least one winding, at least one support on which the winding is wound, at least one ferromagnetic element for concentrating and / or guiding lines of a magnetic field and optionally at least one shielding plate.

[0015] According to the invention, the electrical energy receiving system includes at least one cooling system integrated into at least one element among the ferromagnetic element, the support and / or the shielding plate.

[0016] The cooling system helps limit temperature rise, which contributes to reducing the risk of damage to the components of the electrical power receiving system. Furthermore, integrating the cooling system into at least one of the components of the electrical power receiving system reduces the impact on the aircraft's onboard mass.

[0017] According to another feature, the element among the ferromagnetic element, the support and / or the shielding plate integrating the cooling system comprises a body which has at least one face as well as fins projecting from the face, the body and the fins forming a single piece.

[0018] According to another feature, the cooling system includes at least one coolant conduit located at least partially in the element among the ferromagnetic element, the support and / or the shielding plate, at least one heat transfer fluid supply system connected to a first end of the coolant conduit and at least one heat transfer fluid discharge system connected to a second end of the coolant conduit.

[0019] According to another feature, the cooling system is integrated into the ferromagnetic element.

[0020] According to another feature, the ferromagnetic element comprises a body which has a hollow profile as well as ribs delimiting cooling fluid channels.

[0021] According to another feature, the ferromagnetic element comprises a body made of a ferromagnetic material and at least one recess, obtained by removing material from the body of the ferromagnetic element, forming the cooling fluid conduit.

[0022] According to another feature, the ferromagnetic element comprises a body made of ferromagnetic material and at least one cooling fluid conduit obtained by molding.

[0023] According to another feature, the ferromagnetic element comprises a body having at least one cooling fluid conduit and at least one ferromagnetic material attached around the cooling fluid conduit(s).

[0024] According to another feature, the reported ferromagnetic material comprises at least one nanocrystalline ribbon wound around the cooling fluid conduit(s).

[0025] The invention also relates to an aircraft comprising at least one electrical energy receiving system according to one of the preceding characteristics.

[0026] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which:

[0027] [Fig-1] is a side view of an aircraft equipped with an electrical energy receiving element illustrating an embodiment of the prior art,

[0028] [Fig.2] is a top view of part of an equipped airport facility of electrical energy-emitting elements illustrating a method of embodiment of the prior art,

[0029] [Fig.3] is a schematic representation of an energy transfer device contactless electrical device illustrating a prior art embodiment

[0030] [Fig.4] is a schematic representation of an energy receiving system electrical illustration of one embodiment of the invention.

[0031] [Fig.5] is a schematic representation of part of a receiving system of electrical energy illustrating one embodiment of the invention,

[0032] [Fig.6] is a schematic representation of part of a receiving system of electrical energy illustrating another embodiment of the invention,

[0033] [Fig.7] is a schematic representation of part of a receiving system of electrical energy illustrating another embodiment of the invention.

[0034] According to an embodiment shown in [Fig. 4], an electrical energy receiving system 40 comprises a housing 42 having a face oriented towards an electrical energy emitting system of a contactless electrical energy transfer device by electromagnetic induction. These latter are not described further as they may be identical to those of the prior art.

[0035] According to one application, an aircraft includes at least one electrical power receiving system 40.

[0036] The electrical energy receiving system 40 includes, inside the housing 42, at least one winding 44, also called a receiving coil, as well as at least one ferromagnetic element 46 made of ferrite for example.

[0037] According to one configuration, the electrical energy receiving system 40 also includes at least one support 47 on which the winding 44 is wound, as well as at least one shielding plate 48.

[0038] According to a particular feature of the invention, the ferromagnetic element 46 comprises at least one cooling system 50.

[0039] According to one configuration, the ferromagnetic element 46 comprises a body 52, in the shape of a plate for example, which has at least one face F46, generally the first and second faces F46, F46' are opposite. As an example, the ferromagnetic element 46 is made of ferrite.

[0040] According to an embodiment shown in [Fig. 5], the ferromagnetic element 46 comprises several fins 54 projecting from the face F46. In one arrangement, the body 52 and the fins 54 form a single piece. According to a first method, the fins 54 are obtained by adding material, for example by an additive manufacturing process. According to a second method, the fins 54 are obtained by removing material, for example by a machining process.

[0041] These fins 54 are in contact with a heat transfer fluid flow and ensure the transfer of thermal energy between the ferromagnetic element 46 and the heat transfer fluid. These fins 54 increase the contact surface area between the ferromagnetic element 46 and the heat transfer fluid, thereby improving heat dissipation. In one operating mode, the heat transfer fluid flow in contact with the fins 54 is a forced air flow.

[0042] According to another embodiment, the fins 54 are integral with the support 47 and / or the shielding plate 48.

[0043] According to another embodiment shown in [Fig. 6], the cooling system 50 comprises at least one cooling fluid conduit 56 located at least partially within the body 52 of the ferromagnetic element 46, at least one heat transfer fluid supply system connected to a first end of the cooling fluid conduit 56, and at least one heat transfer fluid discharge system connected to a second end of the cooling fluid conduit 56. In one configuration, the cooling system 50 comprises several cooling fluid conduits 56 located at least partially within the body 52. ​​The various cooling fluid conduits 56 may be connected to one or more heat transfer fluid supply systems and to one or more heat transfer fluid discharge systems.

[0044] According to one configuration, the ferromagnetic element 46 comprises a body 52 made of ferromagnetic material and at least one recess, obtained by removing material from the body 52 of the ferromagnetic element 46 made of ferrite, forming a cooling fluid conduit 56.

[0045] According to another configuration, the ferromagnetic element 46 comprises a body 52 made of ferromagnetic material and at least one cooling fluid conduit 56 obtained by molding.

[0046] According to another configuration, the body 52 is obtained by adding material around the cooling fluid conduit(s) 56. According to this configuration, the body 52 comprises at least one cooling fluid conduit 56 as well as at least one ferromagnetic material brought around the cooling fluid conduit(s) 56, such as at least one nanocrystalline ribbon wound around the cooling fluid conduit(s) 56.

[0047] According to another configuration visible in [Fig.7], the body 52 comprises a hollow profile 58 and ribs 60 delimiting cooling fluid conduits 62. The ribs 60 and / or the cooling fluid conduits 62 are configured to promote heat exchange between the body 52 and a heat transfer fluid circulating in the cooling fluid conduits 62. According to one arrangement, the hollow profile 58 has a constant cross-section.

[0048] As in the case of the cooling fluid conduits 56 visible in [Fig.6], the cooling system 50 comprises, in addition to the cooling fluid conduits 62 located in the body 52 of the ferromagnetic element 46, at least one heat transfer fluid supply system connected to a first end of the cooling fluid conduits 62 and at least one heat transfer fluid discharge system connected to a second end of the cooling fluid conduits 62.

[0049] The fluid circulating in the cooling fluid conduit(s) can be a heat transfer liquid or a gas.

[0050] According to another embodiment, the support 47 could be made of plastic and include a hollow profile and ribs delimiting coolant conduits, as illustrated in [Fig.7], or at least one coolant conduit, as illustrated in [Fig.6].

[0051] Regardless of the embodiment, at least one element of the ferromagnetic element 46, the support 47, and / or the shielding plate 48 comprises at least one cooling system 50, such as at least one cooling fluid conduit 56, 62, and / or fins 54. A single element of the ferromagnetic element 46, the support 47, and / or the shielding plate 48 may comprise one or more cooling systems 50 of the same or different types. Thus, this element may comprise fins 54 and a cooling fluid conduit 56, 62.

[0052] The cooling system 50 dissipates the heat generated during the transfer of electrical energy and limits the temperature rise. The fact that the cooling system 50 is integrated into one of the elements of the electrical energy receiving system 40 configured to support a winding 44 as a support 47, concentrate and / or guide lines of a magnetic field as a ferromagnetic element 46, or limit the propagation of the electromagnetic field as the shielding plate 48 allows for the sharing of functions and limits the impact of the cooling system 50 on the aircraft's onboard mass.

Claims

Demands

1. Electrical energy receiving system (40) of a non-contact electrical energy transfer device by electromagnetic induction, the electrical energy receiving system (40) comprising at least one winding (44), at least one support (47) on which the winding (44) is wound, at least one ferromagnetic element (46) for concentrating and / or guiding lines of a magnetic field and optionally at least one shielding plate (48); characterized in that the electrical energy receiving system (40) comprises at least one cooling system (50) integrated into at least one element among the ferromagnetic element (46), the support (47) and / or the shielding plate (48).

2. Electrical energy receiving system (40) according to claim 1, characterized in that the element among the ferromagnetic element (46), the support (47) and / or the shielding plate (48) integrating the cooling system (50) comprises a body (52) which has at least one face (F46) as well as fins (54) projecting from the face (F46), the body (52) and the fins (54) forming a single piece.

3. Electrical energy receiving system (40) according to any one of the preceding claims, characterized in that the cooling system (50) comprises at least one cooling fluid conduit (56, 62) located at least partially in the element among the ferromagnetic element (46), the support (47) and / or the shielding plate (48), at least one heat transfer fluid supply system connected to a first end of the cooling fluid conduit (56, 62) and at least one heat transfer fluid discharge system connected to a second end of the cooling fluid conduit (56, 62).

4. Electrical energy receiving system (40) according to any one of the preceding claims, characterized in that the cooling system (50) is integrated into the ferromagnetic element (46).

5. An electrical energy receiving system (40) according to the preceding claim, characterized in that the ferromagnetic element (46) comprises a body (52) which includes a hollow profile (58) as well as ribs (60) delimiting cooling fluid conduits (62).

6. Electrical energy receiving system (40) according to any one of claims 4 to 5, characterized in that the ferromagnetic element (46) comprises a body (52) of a ferromagnetic material and at least one recess, obtained by removing material from the body (52) of the ferromagnetic element (46), forming the cooling fluid conduit (56).

7. Electrical energy receiving system (40) according to any one of claims 4 to 6, characterized in that the ferromagnetic element (46) comprises a body (52) of ferromagnetic material and at least one cooling fluid conduit (56) obtained by molding.

8. Electrical energy receiving system (40) according to any one of claims 4 to 7, characterized in that the ferromagnetic element (46) comprises a body (52) having at least one cooling fluid conduit (56) and at least one ferromagnetic material attached around the cooling fluid conduit(s) (56).

9. Electrical energy receiving system (40) according to the preceding claim, characterized in that the reported ferromagnetic material comprises at least one nanocrystalline ribbon wound around the cooling fluid conduit(s) (56).

10. Aircraft comprising at least one electrical power receiving system according to one of the preceding claims.

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