FR3060940A1 - METHOD FOR MANUFACTURING A COOLING STRUCTURE ASSEMBLY AND ELECTRIC POWER COMPONENT FOR AN AIRCRAFT - Google Patents
METHOD FOR MANUFACTURING A COOLING STRUCTURE ASSEMBLY AND ELECTRIC POWER COMPONENT FOR AN AIRCRAFT Download PDFInfo
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- FR3060940A1 FR3060940A1 FR1601791A FR1601791A FR3060940A1 FR 3060940 A1 FR3060940 A1 FR 3060940A1 FR 1601791 A FR1601791 A FR 1601791A FR 1601791 A FR1601791 A FR 1601791A FR 3060940 A1 FR3060940 A1 FR 3060940A1
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- Prior art keywords
- power component
- cooling structure
- electrical power
- aircraft
- assembly
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/20—Direct sintering or melting
- B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L21/00—Processes or apparatus adapted for the manufacture or treatment of semiconductor or solid state devices or of parts thereof
- H01L21/02—Manufacture or treatment of semiconductor devices or of parts thereof
- H01L21/04—Manufacture or treatment of semiconductor devices or of parts thereof the devices having at least one potential-jump barrier or surface barrier, e.g. PN junction, depletion layer or carrier concentration layer
- H01L21/48—Manufacture or treatment of parts, e.g. containers, prior to assembly of the devices, using processes not provided for in a single one of the subgroups H01L21/06 - H01L21/326
- H01L21/4814—Conductive parts
- H01L21/4871—Bases, plates or heatsinks
- H01L21/4882—Assembly of heatsink parts
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L23/00—Details of semiconductor or other solid state devices
- H01L23/34—Arrangements for cooling, heating, ventilating or temperature compensation ; Temperature sensing arrangements
- H01L23/36—Selection of materials, or shaping, to facilitate cooling or heating, e.g. heatsinks
- H01L23/367—Cooling facilitated by shape of device
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L23/00—Details of semiconductor or other solid state devices
- H01L23/34—Arrangements for cooling, heating, ventilating or temperature compensation ; Temperature sensing arrangements
- H01L23/36—Selection of materials, or shaping, to facilitate cooling or heating, e.g. heatsinks
- H01L23/373—Cooling facilitated by selection of materials for the device or materials for thermal expansion adaptation, e.g. carbon
- H01L23/3736—Metallic materials
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/2089—Modifications to facilitate cooling, ventilating, or heating for power electronics, e.g. for inverters for controlling motor
- H05K7/209—Heat transfer by conduction from internal heat source to heat radiating structure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F2005/005—Article surface comprising protrusions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Abstract
L'invention se rapporte à un procédé de fabrication d'un ensemble (10) de structure refroidissante (19)et de composant de puissance électrique (13) pour un aéronef comprenant des étapes dans lesquelles : A. on dispose le composant de puissance électrique (10) comprenant une base dissipatrice (25) une surface destinée à recevoir l'ajout de matière (21) dans un outillage au fond du réservoir comportant de la matière (21), B. on dépose par raclage de la matière directement sur la surface de sorte à obtenir une couche mince (27) de matière fusionnable, C. on utilise un faisceau laser pour solidifier une partie de la matière (21) selon le motif prédéfinie, D. on répète les étapes B et C sorte à solidifier par fusion couche après couche pour obtenir la forme prédéterminée de la structure refroidissante (19). L'invention se rapporte également à d'un ensemble (10) de structure refroidissante (19) et de composant de puissance électrique (13) pour un aéronef obtenu par un tel procédé.The invention relates to a method of manufacturing an assembly (10) of cooling structure (19) and electric power component (13) for an aircraft comprising steps in which: A. the power component is available (10) comprising a dissipating base (25) a surface for receiving the addition of material (21) in a tool at the bottom of the reservoir comprising material (21), B. is deposited by scraping the material directly on the surface so as to obtain a thin layer (27) of meltable material, C. a laser beam is used to solidify a part of the material (21) according to the predefined pattern, D. steps B and C are repeated so as to solidify by layer-by-layer melting to obtain the predetermined shape of the cooling structure (19). The invention also relates to an assembly (10) of cooling structure (19) and electric power component (13) for an aircraft obtained by such a method.
Description
(57) L'invention se rapporte à un procédé de fabrication d'un ensemble (10) de structure refroidissante (19)et de composant de puissance électrique (13) pour un aéronef comprenant des étapes dans lesquelles:(57) The invention relates to a method of manufacturing an assembly (10) of cooling structure (19) and of electrical power component (13) for an aircraft comprising steps in which:
A. on dispose le composant de puissance électrique (10) comprenant une base dissipatrice (25) une surface destinée à recevoir l'ajout de matière (21) dans un outillage au fond du réservoir comportant de la matière (21),A. the electrical power component (10) is arranged comprising a dissipating base (25) a surface intended to receive the addition of material (21) in a tool at the bottom of the tank comprising material (21),
B. on dépose par raclage de la matière directement sur la surface de sorte à obtenir une couche mince (27) de matière fusionnable,B. the material is scraped directly onto the surface so as to obtain a thin layer (27) of fusible material,
C. on utilise un faisceau laser pour solidifier une partie de la matière (21) selon le motif prédéfinie,C. a laser beam is used to solidify part of the material (21) according to the predefined pattern,
D. on répète les étapes B et C sorte à solidifier par fusion couche après couche pour obtenir la forme prédéterminée de la structure refroidissante (19).D. repeating steps B and C so as to solidify by fusion layer after layer to obtain the predetermined shape of the cooling structure (19).
L'invention se rapporte également à d'un ensemble (10) de structure refroidissante (19) et de composant de puissance électrique (13) pour un aéronef obtenu par un tel procédé.The invention also relates to an assembly (10) of cooling structure (19) and of electrical power component (13) for an aircraft obtained by such a method.
Procédé de fabrication d’un ensemble de structure refroidissante et composant de puissance électrique pour un aéronefMethod of manufacturing an assembly of cooling structure and electrical power component for an aircraft
L’invention concerne un procédé de fabrication d’un ensemble structure refroidissante et composant de puissance électrique pour un aéronef.The invention relates to a method for manufacturing a cooling structure and electrical power component assembly for an aircraft.
Les composants de puissances électriques employés dans les aéronefs dissipent une quantité importante de calories sous forme de chaleur. De tels composants possèdent généralement un package qui intègre une surface plane de dissipation. Cette surface facilite l’échange thermique avec une source froide tel qu’un radiateur ou une plaque à eau.The electrical power components used in aircraft dissipate a significant amount of calories in the form of heat. Such components generally have a package which incorporates a flat dissipation surface. This surface facilitates heat exchange with a cold source such as a radiator or a water plate.
Il existe de nombreux dissipateurs pour composant de puissance électrique qui viennent se visser, se coller ou se souder avec la base dissipatrice du composant. Généralement, le contact se fait entre les deux surfaces par un ajout de matière, graisse/pad thermique, colle ou soudure.There are many dissipators for electrical power components which are screwed, glued or welded with the dissipative base of the component. Generally, contact is made between the two surfaces by adding material, grease / thermal pad, glue or solder.
L’ajout de matière peut être réalisé par un procédé de fabrication additive. Ce type de procédé implique un empilement de couches de matière successives nécessitant l’utilisation d’un morceau de métal simple, peu coûteux à fabriquer comme support sur le piston de la zone d’impression, dans la machine de fabrication additive. Cette base sera imbriquée dans la pièce finale totalement solidaire des couches rapportées.The addition of material can be achieved by an additive manufacturing process. This type of process involves a stack of successive layers of material requiring the use of a simple piece of metal, inexpensive to manufacture as a support on the piston of the printing zone, in the additive manufacturing machine. This base will be nested in the final part which is completely integral with the added layers.
Comme représenté sur la figure 3, un composant de puissance électrique de l’art antérieur 1 comprend une base comportant la puissance électrique 3. Une interface métallique thermique 7 est rapportée par une vis 5 sur la base 3. Sur l’interface thermique 7 est fixé un dissipateur 9 par fabrication additive.As shown in FIG. 3, an electrical power component of the prior art 1 comprises a base comprising the electrical power 3. A metallic thermal interface 7 is attached by a screw 5 to the base 3. On the thermal interface 7 is fixed a sink 9 by additive manufacturing.
Cependant, le fait de mettre en contact un composant de puissance électrique avec un dissipateur nécessite d’avoir de part et d’autre un plan conducteur afin de transmettre les calories tout en ayant une tenue mécanique suffisante. De tels plans créent une surépaisseur qui éloigne la source de chaleur de la zone froide, telle que l’air, l’eau, et donc dégrade les performances thermiques du dissipateur.However, the fact of bringing an electrical power component into contact with a dissipator requires having a conductive plane on both sides in order to transmit the calories while having sufficient mechanical strength. Such plans create an extra thickness which removes the heat source from the cold zone, such as air, water, and therefore degrades the thermal performance of the dissipator.
De plus, les surépaisseurs sont des masses supplémentaires et inutiles au refroidissement du composant de puissance électrique.In addition, the extra thicknesses are additional masses and unnecessary for cooling the electrical power component.
En outre, le fait d’avoir deux pièces impose de prévoir des fixations mécaniques par serrage, colle ou soudure et donc des pièces ou des procédés supplémentaires qui induisent de la masse et des coûts.In addition, the fact of having two parts requires the provision of mechanical fixings by tightening, glue or welding and therefore additional parts or processes which induce mass and costs.
Dans le cas d’une fixation mécanique par serrage, il faut prévoir de plus une interface thermique pour palier au problème de résistance thermique de contact.In the case of mechanical fixing by tightening, a thermal interface must also be provided to overcome the problem of thermal contact resistance.
Il existe donc un besoin de réduire la masse et l’encombrement du composant de puissance électrique tout en préservant les performances thermiques de ce composant de puissance.There is therefore a need to reduce the mass and size of the electrical power component while preserving the thermal performance of this power component.
........Selon un premier aspect, l’invention a pour objet un procédé de . ......... According to a first aspect, the invention relates to a method of. .
fabrication d’un ensemble de structure refroidissante et de composant de puissance électrique pour un aéronef comprenant des étapes dans lesquelles :manufacture of a set of cooling structure and electrical power component for an aircraft comprising steps in which:
A. on dispose le composant de puissance électrique comprenant une base dissipatrice avec une surface destinée à recevoir l’ajout de matière dans un outillage au fond du réservoir comportant de la matière,A. there is the electrical power component comprising a dissipating base with a surface intended to receive the addition of material in a tool at the bottom of the tank comprising material,
B. on dépose par raclage de la matière directement sur la surface, notamment métallique, de sorte à obtenir une couche mince de matière fusionnable,B. the material is deposited by scraping directly on the surface, in particular metallic, so as to obtain a thin layer of fusible material,
C. on utilise un faisceau laser pour solidifier une partie de la 25 matière selon le motif prédéfinie,C. a laser beam is used to solidify part of the material according to the predefined pattern,
D. on répète les étapes B et C sorte à solidifier par fusion couche après couche pour obtenir la forme prédéterminée de la structure refroidissante 19.D. repeating steps B and C so as to solidify by fusion layer after layer to obtain the predetermined shape of the cooling structure 19.
Selon des modes particuliers de l’invention, le dispositif de 30 connexion thermique et électrique peut comprendre l’une ou plusieurs des caractéristiques suivantes prises isolément ou selon toutes les combinaisons possibles :According to particular modes of the invention, the thermal and electrical connection device can comprise one or more of the following characteristics taken in isolation or according to all possible combinations:
- la structure refroidissante est un dissipateur de chaleur,- the cooling structure is a heat sink,
- au cours de l’étape C, les couches de matière sont fusionnées par rayonnement issu d’un faisceau laser dont la longueur d’onde est choisie de manière adéquate,- during step C, the layers of material are fused by radiation from a laser beam, the wavelength of which is chosen appropriately,
- la matière ajoutée par couche et la base dissipatrice du 5 composant de puissance sont réalisées dans des matériaux compatibles et fusionnables,the material added per layer and the dissipating base of the power component are made of compatible and fusable materials,
-le matériau est typiquement de l’aluminium.-the material is typically aluminum.
Selon un autre aspect, l’invention a également pour objet un ensemble de structure refroidissante et de composant de puissance 10 électrique pour aéronef comprenant un composant de puissance électrique et une structure refroidissante, de type dissipateur de chaleur, créée par fusion laser sur une base dissipatrice du composant de puissance électrique, ledit ensemble étant obtenu par le procédé de fabrication selonAccording to another aspect, the invention also relates to a set of cooling structure and electrical power component for aircraft comprising an electrical power component and a cooling structure, of the heat sink type, created by laser fusion on a base. dissipator of the electrical power component, said assembly being obtained by the manufacturing process according to
........l’invention.................. the invention ..........
L’invention permet ainsi :The invention thus allows:
- la suppression du problème de fixation du dissipateur sur le composant, la suppression de la résistance thermique de contact entre le composant de puissance et le dissipateur,- the elimination of the problem of fixing the dissipator to the component, the elimination of the thermal resistance of contact between the power component and the dissipator,
- de réduire le doublon des semelles thermiques, de réduire le nombre d’éléments de l’ensemble en supprimant notamment les vis et les interfaces thermiques, de réduire le temps de montage de l’ensemble, de réduire la masse de l’ensemble,- to reduce the duplication of the thermal soles, to reduce the number of elements of the assembly by eliminating in particular the screws and the thermal interfaces, to reduce the assembly time of the assembly, to reduce the mass of the assembly,
- d’assembler simultanément plusieurs éléments formant l’ensemble.- to simultaneously assemble several elements forming the whole.
D’autres buts, caractéristiques et avantages de l’invention apparaîtront à la lecture de la description suivante, donnée uniquement à titre d’exemple non limitatif et faite en référence aux dessins annexés sur lesquels :Other objects, characteristics and advantages of the invention will appear on reading the following description, given solely by way of nonlimiting example and made with reference to the appended drawings in which:
- la figure 1 est un plan de coupe partiel d’un composant de puissance électrique selon l’art antérieur, la figure 2 est un plan de coupe partiel du composant selon un mode réalisation de l’invention,FIG. 1 is a partial sectional plane of an electrical power component according to the prior art, FIG. 2 is a partial sectional plane of the component according to an embodiment of the invention,
La figure 3 est une vue schématique partielle d’un mode de réalisation du procédé de l’invention fabriquant le composant de la figure 2.FIG. 3 is a partial schematic view of an embodiment of the method of the invention manufacturing the component of FIG. 2.
Comme illustré sur la figure 2, le composant de puissance 5 électrique 10 de l’invention est destiné à être installé et utilisé dans un aéronef (non représenté). Ledit composant de l’invention 10 comporte une base 13 réalisée dans un matériau métallique. Ledit matériau peut être ainsi de l’aluminium ou toute autre poudre fusionnable avec la matière de la base dissipatrice du composant.As illustrated in FIG. 2, the electrical power component 10 of the invention is intended to be installed and used in an aircraft (not shown). Said component of the invention 10 comprises a base 13 made of a metallic material. Said material can thus be aluminum or any other powder which can be fused with the material of the dissipating base of the component.
La base métallique 13 est configurée pour permettre la puissance électrique et est conductrice de chaleur.The metal base 13 is configured to allow electrical power and is conductive of heat.
Une structure refroidissante, typiquement un dissipateur de chaleur 19, est créé directement sur la surface de la base 13 par dépôt par raclage puis fusion de matière 21..................A cooling structure, typically a heat sink 19, is created directly on the surface of the base 13 by deposition by scraping then melting of material 21 ..................
La matière 21 employée dans la fusion et la partie de la structure refroidissante externe 19 en contact avec ladite matière peuvent être réalisées dans le même matériau.The material 21 used in the melting and the part of the external cooling structure 19 in contact with said material can be made of the same material.
Le matériau peut être avantageusement choisi parmi des aluminiums compatibles dans le procédé de fusion laser et respecter les contraintes mécaniques associées au système dans lequel se trouve le sous-ensemble.The material can advantageously be chosen from compatible aluminum in the laser fusion process and comply with the mechanical constraints associated with the system in which the subassembly is located.
Comme illustré sur la figure 3, le procédé de fabrication du composant de puissance électrique de l’invention comprend des étapes dans lesquelles :As illustrated in FIG. 3, the method for manufacturing the electrical power component of the invention comprises steps in which:
A. on dispose la base 13 du composant de puissance électrique comprenant une surface destinée à recevoir l’ajout de matière 21 dans un outillage au fond du un réservoir 23 comportant de la matière 21,A. there is the base 13 of the electrical power component comprising a surface intended to receive the addition of material 21 in a tool at the bottom of a tank 23 comprising material 21,
B. on dépose par raclage de la matière 21 directement sur la surface métallique 25 de sorte à obtenir une couche de matière mince fusionnable,B. material 21 is scraped off directly on the metal surface 25 so as to obtain a layer of fusible thin material,
C. Le laser fusionne une partie de la matière 21 selon le motif prédéfinie.C. The laser fuses part of the material 21 according to the predefined pattern.
Les étapes B et C sont répétées afin de solidifier par fusion couche après couche pour obtenir la forme de la structure refroidissante 19.Steps B and C are repeated in order to solidify by fusion layer after layer to obtain the shape of the cooling structure 19.
Avantageusement, au cours de l’étape C, les couches de matière 5 27 sont fusionnées par rayonnement issu d’un faisceau laser 31 dont la température sera adaptée au type de matière fusionnée.Advantageously, during step C, the layers of material 5 27 are fused by radiation from a laser beam 31 whose temperature will be adapted to the type of material fused.
Claims (6)
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1601791A FR3060940A1 (en) | 2016-12-15 | 2016-12-15 | METHOD FOR MANUFACTURING A COOLING STRUCTURE ASSEMBLY AND ELECTRIC POWER COMPONENT FOR AN AIRCRAFT |
| FR1755363A FR3060942B1 (en) | 2016-12-15 | 2017-06-14 | METHOD FOR MANUFACTURING AN ASSEMBLY COMPRISING A MECHANICAL STRUCTURE AND AN ELECTRIC POWER COMPONENT FOR AN AIRCRAFT |
| PCT/FR2017/053517 WO2018109360A1 (en) | 2016-12-15 | 2017-12-12 | Method for manufacturing an assembly comprising a mechanical structure and an electrical power component for an aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1601791A FR3060940A1 (en) | 2016-12-15 | 2016-12-15 | METHOD FOR MANUFACTURING A COOLING STRUCTURE ASSEMBLY AND ELECTRIC POWER COMPONENT FOR AN AIRCRAFT |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| FR3060940A1 true FR3060940A1 (en) | 2018-06-22 |
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Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR1601791A Pending FR3060940A1 (en) | 2016-12-15 | 2016-12-15 | METHOD FOR MANUFACTURING A COOLING STRUCTURE ASSEMBLY AND ELECTRIC POWER COMPONENT FOR AN AIRCRAFT |
| FR1755363A Active FR3060942B1 (en) | 2016-12-15 | 2017-06-14 | METHOD FOR MANUFACTURING AN ASSEMBLY COMPRISING A MECHANICAL STRUCTURE AND AN ELECTRIC POWER COMPONENT FOR AN AIRCRAFT |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR1755363A Active FR3060942B1 (en) | 2016-12-15 | 2017-06-14 | METHOD FOR MANUFACTURING AN ASSEMBLY COMPRISING A MECHANICAL STRUCTURE AND AN ELECTRIC POWER COMPONENT FOR AN AIRCRAFT |
Country Status (2)
| Country | Link |
|---|---|
| FR (2) | FR3060940A1 (en) |
| WO (1) | WO2018109360A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10741995B2 (en) * | 2016-09-27 | 2020-08-11 | Jenoptik Optical Systems Gmbh | Optical and optoelectronic assembly and method for the production thereof |
Families Citing this family (1)
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| CN112687641B (en) * | 2020-12-19 | 2022-09-27 | 复旦大学 | Method for preparing semiconductor power module heat dissipation water channel through 3D printing |
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| US7866372B2 (en) * | 2006-12-20 | 2011-01-11 | The Boeing Company | Method of making a heat exchanger core component |
| DE102010055201A1 (en) * | 2010-12-20 | 2012-06-21 | Eads Deutschland Gmbh | Method for producing a component |
| US9401590B2 (en) * | 2014-01-06 | 2016-07-26 | Hamilton Sundstrand Corporation | Heat sink for contactor in power distribution assembly |
| US9230726B1 (en) * | 2015-02-20 | 2016-01-05 | Crane Electronics, Inc. | Transformer-based power converters with 3D printed microchannel heat sink |
-
2016
- 2016-12-15 FR FR1601791A patent/FR3060940A1/en active Pending
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2017
- 2017-06-14 FR FR1755363A patent/FR3060942B1/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10741995B2 (en) * | 2016-09-27 | 2020-08-11 | Jenoptik Optical Systems Gmbh | Optical and optoelectronic assembly and method for the production thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| FR3060942B1 (en) | 2019-03-15 |
| FR3060942A1 (en) | 2018-06-22 |
| WO2018109360A1 (en) | 2018-06-21 |
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