Classifications

• • H—ELECTRICITY
  • H01—ELECTRIC ELEMENTS
  • H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
  • H01F27/00—Details of transformers or inductances, in general
  • H01F27/08—Cooling; Ventilating
  • H01F27/22—Cooling by heat conduction through solid or powdered fillings
• • H—ELECTRICITY
  • H01—ELECTRIC ELEMENTS
  • H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
  • H01F27/00—Details of transformers or inductances, in general
  • H01F27/06—Mounting, supporting or suspending transformers, reactors or choke coils not being of the signal type
• • H—ELECTRICITY
  • H01—ELECTRIC ELEMENTS
  • H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
  • H01F37/00—Fixed inductances not covered by group H01F17/00
• • H—ELECTRICITY
  • H01—ELECTRIC ELEMENTS
  • H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
  • H01F27/00—Details of transformers or inductances, in general
  • H01F27/24—Magnetic cores
  • H01F27/26—Fastening parts of the core together; Fastening or mounting the core on casing or support
  • H01F27/266—Fastening or mounting the core on casing or support

Definitions

• the present invention relates to the field of thermal regulation of electronic power components for an aeronautical application.
• An aircraft conventionally comprises a large number of electronic power components, in particular, for the actuation of flight controls or the filtering of electrical signals.
• the power electronic components for aeronautical applications are adapted to develop powers of the order of several tens of kilowatts.
• the electronic power components are used transiently for periods of the order of a few seconds which generates a small amount of heat Joule effect; this heat is absorbed by the mass of the electronic component.
• the temperature of the electronic power component increases only slightly which does not affect its operation.
• a wound-up electronic power component 1 hereinafter referred to as the wound component 1
• the wound component 1 comprises a toroidal-shaped magnetic core 1 1, hereinafter designated torus 1 1, around which metal turns 12 are wound, preferably copper.
• torus 1 a toroidal-shaped magnetic core 1 1, hereinafter designated torus 1 1, around which metal turns 12 are wound, preferably copper.
• the magnetic properties of the torus January 1 are degraded and the operation of the wound component 1 is no longer optimal.
• the wound component 1 conventionally comprises fastening lugs 13 connecting turns 12 of the wound component 1 to a base 2 on which the wound component 1 is mounted.
• the temperature of the base 2 is lower than that of the wound component 1 during its operation.
• the base 2 forms, from a thermal point of view, a cold source.
• the core 1 1 and the turns 12 of the coiled component 1 heat up.
• only the turns 12 are in contact with the fastening tabs 13, which makes it possible to drain the calories of the turns 12 into the base 2.
• the calories generated by the Joule effect in the torus 1 1 are not drained satisfactorily. Indeed, to drain the calories torus 1 1 in the fastening lugs 13, they must flow through the turns 12.
• a first solution consists in increasing the diameter of the wound component in order to limit losses by Joule effect. Such a solution increases the mass and bulk of the wound component and is undesirable.
• a second solution is to use a rotating fan to generate a flow of air to cool the wound component. The integration of a rotating fan in an aeronautical application has drawbacks in terms of reliability. This solution is also excluded.
• a third solution would be to use resins, for example of the epoxy type, in which the wound components would be embedded. In practice, such resins do not sufficiently limit heating of a wound component.
• the object of the invention is to form a wound electronic power component whose operating temperature is regulated while ensuring a mechanical strength compatible with an aeronautical application in which the component is subjected to vibrations, accelerations and at outside temperatures. varying between -50 ° C and +1 10 ° C.
• Another object of the invention is to form coiled components of reduced mass and size.
• the invention relates to a wound power electronic component intended to be mounted on a base, the component comprising an axially extending magnetic core on which is wound a plurality of turns, so as to form a magnetic coil, and at least one attachment support to said base including at least one drainage surface in thermal contact with the magnetic core and / or the plurality of turns so as to drain the calories from the magnetic core and / or the plurality of turns towards the base during the operation of the component, component in which the mounting bracket has an equivalent thermal conductivity greater than 400 Wm ⁇ .K ⁇ 1 , preferably greater than 600 Wm " .K " 1 .
• thermal conductivity is defined according to the main direction of the fixing support so as to drive the calories from the hot source to the cold source.
• thermal conductivity is set at room temperature, i.e., at 20 ° C.
• An equivalent high thermal conductivity attachment support effectively drain the calories of the wound component while allowing for vibration resistance.
• the mounting bracket consists of only one element
• the thermal conductivity of the material of the single element corresponds to the equivalent thermal conductivity.
• the fixing support comprises several elements (for example a fixing lug and a thermal drainage device), the equivalent thermal conductivity corresponds to the thermal conductivity of all of said elements.
• the fixing support is non-magnetic so as not to heat up by induction. More preferably, the fixing support consists of a composite material. Such a material has the advantage of being passive and has a high resistance to vibrations. Furthermore, it is possible to obtain a chosen form of fixation support, a composite material that can be easily worked.
• the fixing support comprises a composite material loaded with particles of high thermal conductivity chosen from: carbon nanotubes, carbon fibers, diamond particles and graphite particles.
• particles of high thermal conductivity chosen from: carbon nanotubes, carbon fibers, diamond particles and graphite particles.
• Such materials exhibit high thermal conductivities and are compatible for aeronautical application in which the coiled component is subjected to vibrations, accelerations and external temperatures ranging from -50 ° C to +110 ° C.
• the fixing support comprises a two-phase thermal drainage device so as to increase the equivalent thermal conductivity and thus boost the drainage of calories.
• the two-phase thermal drainage device is a heat pipe.
• the two-phase thermal drainage device is an oscillating heat pipe.
• the two-phase thermal drainage device is a steam chamber or "vapor chamber”.
• the fixing support having at least one fixing lug on the base, the two-phase thermal drainage device is mounted on the fixing lug which improves the maintenance of the thermal drainage device.
• the fixing support comprises at least one fixing lug on the base, the two-phase thermal drainage device is integrated with the fixing lug, which makes it possible to increase the equivalent thermal conductivity of the fixing support.
• the attachment support has a first drainage surface in thermal contact with the magnetic core and a second drainage surface in thermal contact with the plurality of turns so as to drain the calories from the magnetic core and the plurality of turns. to the base during operation of the component.
• the drainage surfaces of the mounting bracket allow direct draining of calories from the magnetic core and turns which improves the thermal regulation of the component power electronics.
• the presence of drainage surfaces does not increase the mass nor the size of the wound electronic power component.
• the heat generated by the magnetic core does not pass through the turns but is directly drained by the mounting bracket.
• the first drainage surface is substantially equal to the axial section of the magnetic core.
• the turns are wound on the magnetic core and the fixing support which makes it possible to put the fixing support in contact with the turns and the magnetic core.
• the winding of the turns advantageously makes it possible to hold the fixing support together with the magnetic core.
• the second drainage surface is at least partially curved so as to limit the risk of injury of the turns wound on the mounting bracket.
• the fixing support comprises an axially extending thermal contact ring, the first and second transverse faces of the ring respectively forming the first drainage surface and a portion of the second drainage surface.
• one face of the ring is in contact with a transverse face of the magnetic core while the other face of the ring is in contact with the turns.
• the thermal contact ring has an axial surface connected to the second transverse face by a rounded edge.
• a rounded edge makes it possible to limit the risk of injury of the turns which are wound on the second transverse face and the axial surfaces of the ring which together form the second drainage surface.
• a rounded stop also called leave, improves the contact between the turns and the second drainage surface.
• a thermal interface preferably a thermal grease, is placed between the first drainage surface and the magnetic core.
• a thermal interface makes it possible to improve the capacity of drainage of the calories of the magnetic core.
• the attachment support is attached to one end of the magnetic core. Fixing at one end of the magnetic core does not affect the magnetic performance of the core.
• the mounting bracket has at least one bracket to the base.
• the fixing lug makes it possible, on the one hand, to drive the calories taken from the surfaces of drainage to the base and, secondly, to resist vibration and accelerations related to the operation of the aircraft on which the component is attached.
• the component having two mounting brackets the mounting brackets are attached to the ends of the magnetic core.
• the presence of two supports makes it possible to effectively secure the wound component in an environment subject to vibrations and accelerations while limiting its mass and its size.
• Figure 1 is a sectional representation of a power electronic component wound according to the prior art (already commented);
• Figure 2 is a schematic representation of an electronic power component wound according to the invention in a horizontal position, only a few turns being shown;
• FIG. 3 is a representation in axial section of the wound power electronic component of FIG. 2;
• Figure 4 is a schematic representation of an electronic power component wound according to the invention in a vertical position, only a few turns being shown.
• FIG. 2 represents a first embodiment of a wound electronic power component 3 according to the invention for an aeronautical application in which the wound component 3 is subjected to vibrations, accelerations and at external temperatures varying between -50.degree. C and +1 10 ° C.
• the wound component 3 comprises a toroid-shaped magnetic core 31, hereinafter torus 31, on which is wound a plurality of turns 32 so as to form a coil.
• the torus 31 is in the form of a longitudinal cylinder of axis X and circular section.
• the core 31 is made of a magnetic material such as ferrite.
• a plurality of turns 32, preferably of copper, is wound in a conventional manner around the torus 31 so as to form a magnetic coil as shown in FIG. 2.
• Such a coil is adapted to generate currents by induction in order to achieve, by for example, operations for filtering electrical signals.
• the wound component 3 is mounted to a structural base 2 that performs a cold source function, the latter being preferably secured to the aircraft.
• the base 2 is a flat horizontal plate but it goes without saying that the base 2 can be presented _
• the axis X of the torus 31 of the wound component 3 extends horizontally with respect to the base 2. It is said that the wound component 3 is mounted in a horizontal position on the base 2.
• the wound component 3 comprises two identical mounting brackets 4 and mounted at the lateral ends of the torus 31 of the wound component 3 as shown in FIGS. 2 and 3 in order to be able to maintain it. in a secure manner when it is subjected to vibrations and accelerations.
• Each fixing support 4 comprises a circular ring 41 extending axially along the axis X and having a first drainage surface S1 in thermal contact with the torus 31 and a second drainage surface S2 in thermal contact with the plurality of turns 32. in such a way as to drain in parallel the calories of the torus 31 and the plurality of turns 32 towards the base 2.
• Each fixing support 4 further comprises a fixing lug 42, integral with the circular ring 41, which is adapted to The dimensions of the fixing lug 42 are determined to ensure the mechanical strength of the wound component 3 in the event of vibrations and accelerations.
• the mounting bracket 4 is in the form of a single piece to improve the thermal drainage but it goes without saying that the mounting bracket 4 could be modular.
• the fixing support 4 consists of a non-magnetic material, preferably aluminum, so as not to disturb the induction phenomena between the turns 32 and the core 31.
• the car -Heating generated by induction is negligible for a non-magnetic material.
• Aluminum advantageously has a high thermal conductivity as well as a density compatible with an aeronautical application.
• the fixing support 4 has an equivalent thermal conductivity greater than 400 Wm “ .K “ 1 in order to effectively regulate the temperature of the wound component 3 while allowing to withstand mechanical stresses.
• the equivalent thermal conductivity is greater than 600 Wm “ .K “ 1 .
• the fixing support is non-magnetic in order to limit heating of the support by magnetic induction.
• the fixing support consists of a composite material loaded with particles of high thermal conductivity chosen from: diamond particles, carbon nanotubes, carbon fibers and graphite particles.
• particles of high thermal conductivity chosen from: diamond particles, carbon nanotubes, carbon fibers and graphite particles.
• the choice of particles results from a compromise between their thermal conductivity and their price, the latter being a function of their thermal conductivity.
• Such a composite material is passive and thus presents a great ? vibration resistance.
• a two-phase thermal drainage device is mounted on the mounting bracket and allows, due to the phase change, to achieve equivalent thermal conductivities of the order of 5000 Wm ".K" 1 thereby optimally regulate the temperature of the wound component 3.
• the two-phase thermal drainage device is a heat pipe whose operation is controlled, which ensures high reliability, and the cost is low.
• the heat pipe is connected on the one hand to the fixing lug 42 and on the other hand to the base 2.
• the two-phase thermal drain device is an oscillating heat pipe known as the "Pulsating Heat Pipe", which has higher performance and cost, or a steam chamber, more known as the “vapor chamber”, which performs better than a heat pipe for configurations in which the ratios of the cold source / hot source surfaces are high, the cost of a steam chamber being higher than that of a heat pipe. of a heat pipe.
• the circular ring 41 has a first transverse surface, forming the first drainage surface S1, which is in contact with a lateral surface of the torus 31.
• the circular ring 41 has an axial section substantially equal to that of the torus 31. It goes without saying that the section of the circular ring 41 could also be smaller than that of the core 31.
• the thickness of the ring 41 is defined to allow effective thermal drainage while limiting the mass of the wound component 3.
• a ring thickness 41 of the order of 2 to 3 mm ensures a good compromise.
• the circular ring 41 has a second transverse face, opposite to the first transverse face, the two transverse faces of the ring 41 state connected by an inner axial surface SI and by an outer axial surface SE as represented in FIG. with reference to FIG. 2, the torus 31 and the circular rings 41 of the fixing supports 4 form an axial cylinder on which the turns 32 are wound as shown in FIGS.
• the turns 32 being, on the one hand, in contact with the axial surfaces of the torus 31 and, secondly, with the second transverse surface and the axial surfaces SI, SE of the circular rings 41 to drain the calories of the turns 32.
• the second transverse surface and the inner axial surfaces SI and outer SE together form the second thermal drainage surface S2 of each support 4.
• the second transversal surface of the ring 41 is connected to the inner axial surface S1 by an inner edge 61 and to the outer axial surface SE by an outer edge 62.
• the ridges 61, 62 are rounded so as to limit the risk of injury of the turns 32 during their winding around the rings 41. It goes without saying that only one of the edges 61, 62 could be rounded.
• the second drainage surface S 2 bringing the fixing support 4 into contact with the turns 32, is curved so as to limit the risk of wounding the turns 32 and improve the thermal contact between the fixing support 4 and the turns 32.
• the fixing lug 42 of the fixing support 4 preferably comprises securing means to the base 2, preferably fastening orifices 5 adapted to receive fastening screws to the base 2 as shown.
• the torus 31 and the rings 41 of the fixing brackets 4 are held together by the winding of the turns 32.
• the fixing brackets 4 comprise holding means (not shown). adapted to hold together the torus 31 and the two mounting brackets 4 to allow the winding of the turns 32 around the torus 31 and the rings 41 of the mounting brackets 4.
• a rod threaded longitudinal is screwed between the two fixing brackets 4 to adjust the axial distance separating them, which allows to retain the torus 31 and the winding turns 32.
• a bracket 42 comprises a longitudinal thread 6 to allow the screwing of a threaded rod.
• each mounting bracket 4 has a bracket 42 but it goes without saying that it could include several.
• the mounting bracket 4 could contain a bracket 42 connected to a cold source other than the base 2.
• a bracket 42 could include fins to improve the heat transfer with Ambiant air.
• a thermal interface preferably a thermal grease of the Berquist Gap Filler 1500 type, is placed between the first drainage surface S1 (in this example, the first transverse face of the ring 41) and the torus 31 to improve the thermal drainage of the torus 31 to the ring 41.
• the torus 31 conventionally has a surface condition which is not satisfactory to allow a homogeneous pressure with the fixing support 4.
• the addition of a thermal interface makes it possible to improve the surface state of the torus 31 which ensures efficient thermal drainage.
• a thermal interface may be applied between the bracket 42 and the base 2 to facilitate the transfer of calories to the base 2.
• the fixing brackets 4 are mounted at the ends of the magnetic ring 31 of toric shape, the first transverse face of each ring 41 coming into contact with each other. contact with a transverse end face of the core 31.
• a thermal grease is applied to the interface.
• a copper wire is wound on the cylindrical assembly formed by the rings 41 and the torus 31 so as to form turns 32.
• the wound component 3 is fixed to the base 2 by screwing its fixing feet 42 via the orifices 5.
• the turns 32 are connected to other electronic power components in order to implement, for example, a filtering operation for a power converter.
• the wound component 3 can be impregnated with resin.
• FIG. 4 A second embodiment of a wound component 3 'according to the invention is shown in FIG. 4.
• the wound component 3' comprises a toroidal magnetic core 31 'on which are wound coils 32 '.
• the axis X of the core 31' extends orthogonally to the base 2 as shown in FIG. 4. It is said that the wound component 3 'is mounted in a vertical position on the base 2.
• the wound component 3 has two mounting brackets 8, 9 which are different.
• the wound component 3 comprises an upper fixing support 8 comprising a circular ring 81, similar to the ring of the first embodiment, as well as two upper attachment tabs 82 connecting the ring 81 to the base 2 which are diametrically opposite.
• the wound component 3 'furthermore comprises a lower fixing support 9 comprising a circular ring 91, similar to the ring of the first embodiment, as well as two lower fixing tabs 92 connecting the ring 91 to the base 2 .
• the upper fastening tabs 82 are, in this example, bent to allow the base 2 to be connected without disturbing the winding of the turns 32.
• the lower fastening tabs 92 are, in this example, only bearing on the base 2 and do not comprise fixing means, the fixing of the upper fastening tabs 82 ensuring the maintenance of the wound component on the base 2.
• a wound component 3, 3 'according to the invention can be mounted vertically or horizontally on a base 2 which is very advantageous in terms of space.

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• Engineering & Computer Science (AREA)
• Power Engineering (AREA)
• Cooling Or The Like Of Electrical Apparatus (AREA)
• General Induction Heating (AREA)
• Cooling Or The Like Of Semiconductors Or Solid State Devices (AREA)
• Coils Or Transformers For Communication (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=47071364

Family Applications (1)

Country Status (9)

Families Citing this family (3)

Family Cites Families (16)

• 2011
  • 2011-09-28 FR FR1158671A patent/FR2980625B1/fr active Active
• 2012
  • 2012-09-27 WO PCT/FR2012/052191 patent/WO2013045850A1/fr active Application Filing
  • 2012-09-27 CN CN201280046394.3A patent/CN103827993A/zh active Pending
  • 2012-09-27 JP JP2014532455A patent/JP2014532306A/ja not_active Withdrawn
  • 2012-09-27 BR BR112014006076A patent/BR112014006076A2/pt not_active IP Right Cessation
  • 2012-09-27 US US14/345,497 patent/US20150042431A1/en not_active Abandoned
  • 2012-09-27 EP EP12775779.7A patent/EP2761632A1/de not_active Withdrawn
  • 2012-09-27 CA CA2849049A patent/CA2849049A1/fr not_active Abandoned
  • 2012-09-27 RU RU2014111158/07A patent/RU2014111158A/ru not_active Application Discontinuation

Non-Patent Citations (1)

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