EP2761631A1

EP2761631A1 - Coiled electronic power component comprising a heat sinking support

Info

Publication number: EP2761631A1
Application number: EP12775778.9A
Authority: EP
Inventors: Nicolas DELALANDRE; Alain Guerber; Jacques SALAT; Jean-Jacques Simon
Original assignee: Hispano Suiza SA
Current assignee: Safran Electrical and Power SAS
Priority date: 2011-09-28
Filing date: 2012-09-27
Publication date: 2014-08-06
Also published as: JP2014530505A; BR112014006072A2; CA2849048A1; CN103827994A; US20150042432A1; FR2980626A1; RU2014111157A; WO2013045849A1; FR2980626B1

Abstract

A coiled electronic power component (3) intended to be mounted on a base (2), the component (3) comprising a magnetic core (31) extending axially on which is wound a plurality of turns (32), so as to form a magnetic core, and at least one support (4) for fastening to said base (2), the fastening support (4) comprising a first sink surface (S1) in thermal contact with the magnetic core (31) and a second sink surface (S2) in thermal contact with the plurality of turns (32) in such a way as to sink the heat from the magnetic core (31) and from the plurality of turns (32) to the base (2) when the component (3) is operating.

Description

ELECTRONIC COIL POWER COMPONENT COMPRISING A SUPPORT OF

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. Traditionally, 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.

In order to meet the new needs of aircraft manufacturers, it has been proposed to use the electronic power components permanently for periods of the order of a few minutes. In practice, after a few minutes of use, the temperature of the electronic power component begins to rise until reaching a limit temperature from which the operation of the electronic component is no longer optimal.

Among electronic power components, the wound electronic components, used in particular for signal filtering, are affected by the rise in temperature. With reference to FIG. 1, a wound-up electronic power component 1, hereinafter referred to as 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. In practice, from 1 10 ° C, 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. In operation, the core 1 1 and the turns 12 of the coiled component 1 heat up. As shown in FIG. 1, 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. On the contrary, 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. The thermal resistance induced by this assembly is very high. The temperature of the wound component 1 remains high which prevents its optimal operation. To eliminate these disadvantages, 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.

To this end, 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 mounting bracket to said base, the mounting bracket having 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 core calories. magnetic and the plurality of turns to the base during operation of the component.

The thermal drainage surfaces of the mounting bracket directly drain the calories of the magnetic core and turns which improves the thermal regulation of the electronic power component. Advantageously, the presence of drainage surfaces does not increase the mass nor the size of the wound electronic power component. Thus, the heat generated by the magnetic core does not circulate in the turns but is directly drained by the mounting bracket.

Preferably, the first drainage surface is substantially equal to the axial section of the magnetic core. Thus, there is a compromise between the thermal drainage capacity (large drainage area) and a limitation of mass and bulk (reduced drainage area).

Preferably, 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. In addition, the winding of the turns advantageously makes it possible to hold the fixing support together with the magnetic core.

More preferably, 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.

According to one aspect of the invention, 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. Thus, 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.

Preferably, 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. In addition, a rounded stop, also called leave, improves the contact between the turns and the second drainage surface. According to another aspect of the invention, a thermal interface, preferably a thermal grease, is placed between the first drainage surface and the magnetic core. Such a thermal interface makes it possible to improve the capacity of drainage of the calories of the magnetic core.

Preferably, 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.

Preferably still, the mounting bracket has at least one bracket to the base. The fixing lug makes it possible, on the one hand, to drive the heat taken up by the drainage surfaces towards the base and, on the other hand, to withstand the mechanical stresses associated with the operation of the aircraft on which the component is fixed. .

More preferably, 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.

According to one aspect of the invention, the fixing support is non-magnetic so as not to heat up by induction. Preferably, the fixing support has an equivalent thermal conductivity greater than 400 Wm ^~ .K ^{~ 1} , preferably greater than 600 Wm ^" .K ^{" 1} .

The value of the 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.

An equivalent high thermal conductivity attachment support effectively drain the calories of the wound component while allowing for vibration resistance. When the mounting bracket consists of only one element, the thermal conductivity of the material of the single element corresponds to the equivalent thermal conductivity. When 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. 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. Preferably, the composite material is loaded with 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.

More preferably, the fixing support comprises a two-phase thermal drainage device so as to increase the thermal conductivity and thus boost the drainage of calories.

Preferably, the two-phase thermal drainage device is a heat pipe.

According to a first aspect of the invention, the two-phase thermal drainage device is an oscillating heat pipe.

According to another aspect of the invention, the two-phase thermal drainage device is a known vapor chamber or "vapor chamber". Preferably, the fixing support having at least one attachment lug to the base, the two-phase thermal drain device is mounted on the bracket or integrated in said bracket. The invention will be better understood on reading the description which will follow, given solely by way of example, and referring to the appended drawings in which:

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; and

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.

It should be noted that the figures disclose the invention in detail to implement the invention, said figures can of course be used to better define the invention where appropriate. 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. In this example, 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. With reference to FIGS. 2 to 3, the base 2 is a horizontal flat plate, but it goes without saying that the base 2 can be in various forms. With reference to FIGS. 2 and 3, in this first embodiment of the invention, 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 horizontal position on the base 2. In this example, the wound component 3 comprises two identical fixing 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 hold it securely when the latter 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. so 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 secured to the circular ring 41, which is adapted to be mounted on the base 2. The dimensions of the fixing lug 42 are determined to ensure the mechanical strength of the wound component 3 in case of vibrations and accelerations. In this example, 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.

Preferably, 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. Advantageously, 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.

More generally, the fixing support 4 is made of a material whose thermal conductivity can be greater than 600 Wm ^" .K ^{" 1 in} order to effectively regulate the temperature of the wound component 3 while allowing to withstand vibration. Preferably, the fixing support is non-magnetic in order to limit heating of the support by magnetic induction. According to a first aspect, 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. 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 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.

Preferably, 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 regulate optimally the temperature of the wound component 3. Preferably, the two-phase thermal drainage device is a heat pipe whose operation is controlled, which ensures high reliability, and the cost is low. Preferably, the heat pipe is connected on the one hand to the fixing lug 42 and on the other hand to the base 2.

Preferably, to achieve high thermal conductivity performance, 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.

In this example, 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. Thus, the calories accumulated by the torus 31 during its operation are transmitted directly to the fixing support 4 via the first transverse surface of the circular ring 41. To optimize the thermal drainage, 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. 2 and 3, 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 fixing support 4. With reference to FIG. 3, the second transverse surface of the 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. Preferably, the edges 61, 62 are rounded so as to limit the risk of wounding the turns. 32 when wound around the rings 41. It goes without saying that only one of the edges 61, 62 could be rounded. More generally, the second drainage surface S2, 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 to 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 fixing holes 5 adapted to receive fastening screws to the base 2 as shown in FIG. 2 In this example, the torus 31 and the rings 41 of the fixing supports 4 are held together by the winding of the turns 32. Preferably, the fixing brackets 4 comprise holding means (not shown) adapted to hold together the torus 31 and the two fixing brackets 4 in order to allow the windings 32 to be wound around the torus 31 and the rings 41 of the fixing supports 4. Preferably, a longitudinal threaded rod is screwed between the two fixing supports 4 for adjust the axial distance separating them, which makes it possible to retain the torus 31 and the winding of the turns 32. With reference to FIG. 2, a fastening tab 42 has a longitudinal thread 6 for allow the screwing of a threaded rod.

In this example, each mounting bracket 4 has a bracket 42 but it goes without saying that it could include several. For example, the mounting bracket 4 could contain a bracket 42 connected to a cold source other than the base 2. Similarly, a bracket 42 could include fins to improve the heat transfer with Ambiant air.

Preferably, 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. In fact, 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. Similarly, a thermal interface may be applied between the bracket 42 and the base 2 to facilitate the transfer of calories to the base 2.

During its manufacture, 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 a transverse end face of the core 31. Preferably, a Thermal grease is applied to the interface. Then, a copper wire is wound on the cylindrical assembly formed by the rings 41 and the torus 31 so as to form turns 32. When mounted on an aircraft, the wound component 3 is fixed to the base 2 by screwing its fixing feet 42 via the orifices 5. Next, the turns 32 are connected to other power electronic components in order to implement, for example, a filtering operation for a power converter. During its operation in steady state, calories are generated by the Joule effect in the torus 31 and the turns 32 and are directly drained by the ring 41 of the fixing support 4 in order to be transferred into the attachment foot 42 to be then fed to the base 2 forming the cold source which allows to regulate the temperature of the wound component 3 during its operation.

To ensure good mechanical strength of the assembly, the wound component 3 can be impregnated with resin. A second embodiment of a wound component 3 'according to the invention is shown in FIG. 4. In a similar manner to the first embodiment, the wound component 3' comprises a toroidal magnetic core 31 'on which are wound coils 32 '. In this second embodiment of the wound component 3 ', 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.

Unlike the first embodiment, 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 fastening 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.

Claims

1. Electronic wound power component (3, 3 ') for mounting on a base

(2), the component (3, 3 ') having an axially extending magnetic core (31, 31') on which is wound a plurality of turns (32, 32 '), so as to form a magnetic coil, and at least one fastening support (4, 8, 9) to said base (2), component (3, 3 '), characterized in that the fastening support (4, 8, 9) comprises at least one fastening lug ( 42, 82, 92) to the base (2) which comprises a first drainage surface (S1) in thermal contact with the magnetic core (31, 31 ') and a second drainage surface (S2) in thermal contact with the plurality of turns (32, 32 ') so as to drain the calories from the magnetic core (31, 31') and the plurality of turns (32, 32 ') to the base (2) during operation of the component (3 , 3 ').

2. Component according to claim 1, wherein the first drainage surface (S1) is substantially equal to the axial section of the magnetic core (31, 31 ').

3. Component according to one of claims 1 to 2, wherein the turns (32) are wound on the magnetic core (31, 31 ') and the mounting bracket (4, 8, 9).

4. Component according to one of claims 1 to 3, wherein the second drainage surface (S2) is at least partially curved.

5. Component according to one of claims 1 to 4, wherein, the fixing support (4, 8,

9) comprises a thermal contact ring (41, 81, 91) extending axially, the first and second transverse faces of the ring (41, 81, 91) respectively forming the first drainage surface (S1) and a portion the second drainage surface (S2).

6. Component according to claim 5, wherein the thermal contact ring (41, 81, 91) has an axial surface (SI, SE) connected to the second transverse face (S2) by a rounded inner edge (61, 62).

7. Component according to one of claims 1 to 6, wherein a thermal interface, preferably a thermal grease, is placed between the first drainage surface (S1) and the magnetic core (31, 31 ').

8. Component according to one of claims 1 to 7, wherein the fixing bracket (4, 8, 9) is attached to one end of the magnetic core (31, 31 ').

9. Component according to one of claims 1 to 8, wherein the fixing support (4, 8, 9) is non-magnetic.