FR3094253A1 - PROCESS FOR BONDING A METAL PART ON A COMPOSITE MATERIAL ELEMENT OF AN AIRCRAFT TURBOMACHINE - Google Patents
PROCESS FOR BONDING A METAL PART ON A COMPOSITE MATERIAL ELEMENT OF AN AIRCRAFT TURBOMACHINE Download PDFInfo
- Publication number
- FR3094253A1 FR3094253A1 FR1903352A FR1903352A FR3094253A1 FR 3094253 A1 FR3094253 A1 FR 3094253A1 FR 1903352 A FR1903352 A FR 1903352A FR 1903352 A FR1903352 A FR 1903352A FR 3094253 A1 FR3094253 A1 FR 3094253A1
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- metal
- powder
- bonding
- heat treatment
- Prior art date
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- Granted
Links
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 43
- 239000002184 metal Substances 0.000 title claims abstract description 43
- 238000000034 method Methods 0.000 title claims abstract description 29
- 239000002131 composite material Substances 0.000 title claims abstract description 8
- 239000000843 powder Substances 0.000 claims abstract description 55
- 239000002245 particle Substances 0.000 claims abstract description 10
- 238000010438 heat treatment Methods 0.000 claims description 18
- 238000005219 brazing Methods 0.000 claims description 14
- 239000003292 glue Substances 0.000 claims description 12
- 239000000853 adhesive Substances 0.000 claims description 10
- 238000000151 deposition Methods 0.000 claims description 10
- 239000000203 mixture Substances 0.000 claims description 10
- 230000001070 adhesive effect Effects 0.000 claims description 9
- 229910001092 metal group alloy Inorganic materials 0.000 claims description 9
- 239000011230 binding agent Substances 0.000 claims description 7
- 238000005507 spraying Methods 0.000 claims description 5
- 229910018134 Al-Mg Inorganic materials 0.000 claims description 4
- 229910018467 Al—Mg Inorganic materials 0.000 claims description 4
- 239000002390 adhesive tape Substances 0.000 claims description 4
- 230000008021 deposition Effects 0.000 claims description 4
- 238000002360 preparation method Methods 0.000 claims description 4
- 229910018131 Al-Mn Inorganic materials 0.000 claims description 3
- 229910018125 Al-Si Inorganic materials 0.000 claims description 3
- 229910018461 Al—Mn Inorganic materials 0.000 claims description 3
- 229910018520 Al—Si Inorganic materials 0.000 claims description 3
- 229910002482 Cu–Ni Inorganic materials 0.000 claims description 3
- 229910004696 Ti—Cu—Ni Inorganic materials 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910000679 solder Inorganic materials 0.000 claims description 3
- 239000000126 substance Substances 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 239000011159 matrix material Substances 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 229920000642 polymer Polymers 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 239000003125 aqueous solvent Substances 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000001311 chemical methods and process Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 229910001338 liquidmetal Inorganic materials 0.000 description 1
- 239000002923 metal particle Substances 0.000 description 1
- 239000003960 organic solvent Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 238000010408 sweeping Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
- 238000009941 weaving Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/02—Preparation of the material, in the area to be joined, prior to joining or welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
- B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
- B29C66/112—Single lapped joints
- B29C66/1122—Single lap to lap joints, i.e. overlap joints
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/301—Three-dimensional joints, i.e. the joined area being substantially non-flat
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/303—Particular design of joint configurations the joint involving an anchoring effect
- B29C66/3032—Particular design of joint configurations the joint involving an anchoring effect making use of protrusions or cavities belonging to at least one of the parts to be joined
- B29C66/30321—Particular design of joint configurations the joint involving an anchoring effect making use of protrusions or cavities belonging to at least one of the parts to be joined making use of protrusions belonging to at least one of the parts to be joined
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
- B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
- B29C66/53—Joining single elements to tubular articles, hollow articles or bars
- B29C66/532—Joining single elements to the wall of tubular articles, hollow articles or bars
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
- B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
- B29C66/54—Joining several hollow-preforms, e.g. half-shells, to form hollow articles, e.g. for making balls, containers; Joining several hollow-preforms, e.g. half-cylinders, to form tubular articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/721—Fibre-reinforced materials
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/721—Fibre-reinforced materials
- B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
- B29C66/72141—Fibres of continuous length
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/74—Joining plastics material to non-plastics material
- B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/205—Constructional features for protecting blades, e.g. coating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/26—Fabricated blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
- B29L2031/082—Blades, e.g. for helicopters
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/237—Brazing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/40—Heat treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/63—Structure; Surface texture coarse
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Powder Metallurgy (AREA)
Abstract
Procédé de collage d’une pièce métallique sur un élément, par exemple en matériau composite, d’une turbomachine d’aéronef, ce procédé comprenant : a) une étape d’augmentation de la rugosité et de fonctionnalisation d’une surface de la pièce métallique, b) une étape de collage de cette surface sur l’élément, caractérisé en ce que l’étape a) comprend la fixation d’au moins une poudre métallique (10, 12) sur la surface (14), cette poudre métallique ayant une granulométrie choisie pour augmenter la rugosité de la surface. Figure pour l'abrégé : Figure 6a-6bA method of bonding a metal part to an element, for example made of composite material, of an aircraft turbomachine, this method comprising: a) a step of increasing the roughness and functionalizing a surface of the part metallic, b) a step of bonding this surface to the element, characterized in that step a) comprises fixing at least one metallic powder (10, 12) on the surface (14), this metallic powder having a particle size chosen to increase the roughness of the surface. Figure for abstract: Figure 6a-6b
Description
Domaine technique de l'inventionTechnical field of the invention
La présente invention concerne un procédé de collage d’une pièce métallique sur un élément, par exemple en matériau composite, d’une turbomachine d’aéronef, cet élément étant par exemple une aube de soufflante.The present invention relates to a method for bonding a metal part to an element, for example made of composite material, of an aircraft turbine engine, this element being for example a fan blade.
Arrière-plan techniqueTechnical background
L’arrière-plan technique est notamment illustré par les demandes antérieures FR-A1-2 957 545, FR-A1-2 989 607 et FR-A1-3 046 557.The technical background is illustrated in particular by the earlier applications FR-A1-2 957 545, FR-A1-2 989 607 and FR-A1-3 046 557.
Une turbomachine d’aéronef comporte une ou plusieurs hélice(s) qui peuvent être carénée(s) ou non carénée(s). La présente invention s’applique notamment aux aubes d’une soufflante, c'est-à-dire aux aubes d’une hélice carénée mais aussi à d’autres types d’hélices, telles que les hélices non carénées des turbopropulseurs par exemple.An aircraft turbine engine comprises one or more propellers which may be ducted or unducted. The present invention applies in particular to the blades of a fan, that is to say to the blades of a ducted propeller, but also to other types of propellers, such as the unducted propellers of turboprop engines for example.
Une hélice de turbomachine est traversée par un flux d’air et ses aubes peuvent subir des dommages par usure ou impact, par exemple du type FOD (acronyme de l’anglaisFlying Object Damage) provoqué par l’impact d’un oiseau par exemple sur les aubes.A turbomachine propeller is crossed by a flow of air and its blades can suffer damage by wear or impact, for example of the FOD type (acronym for English Flying Object Damage ) caused by the impact of a bird for example on the blades.
Afin que les aubes résistent mieux au FOD, il est connu de renforcer leurs bords d’attaque avec des boucliers métalliques, en particulier lorsque ces aubes comportent une pale en composite à matrice organique (CMO). Une pale en CMO comprend une préforme tissée noyée dans une matrice polymérique. La préforme est obtenue par tissage de fibres de carbone en trois dimensions.In order for the blades to better resist FOD, it is known to reinforce their leading edges with metal shields, in particular when these blades include an organic matrix composite (OMC) blade. A CMO blade comprises a woven preform embedded in a polymer matrix. The preform is obtained by weaving carbon fibers in three dimensions.
Un bouclier comporte deux ailes latérales s’étendant respectivement sur un intrados et un extrados de la pale, et un nez reliant les deux ailes. Le bouclier est collé sur le bord d’attaque de la pale.A shield has two side wings extending respectively over an underside and an upper surface of the blade, and a nose connecting the two wings. The shield is glued to the leading edge of the blade.
Afin d’améliorer la tenue du collage et atteindre des caractéristiques mécaniques suffisantes, le bouclier de la pale est soumis dans la technique actuelle à une série d’étapes de préparation avant collage. Une de ces étapes est une attaque dans un bain chimique. Cette étape permet de réaliser une attaque chimique de la surface du bouclier, qui engendre une certaine rugosité de cette surface et la formation d’oxydes stabilisés en prévision d’un collage durable. Toutefois, ce procédé chimique ne permet de créer qu’une faible rugosité (en général inférieure à 1,2 µm) lorsque le substrat d’origine est très lisse, en raison des conditions d’usinage chimique.In order to improve bonding behavior and achieve sufficient mechanical characteristics, the blade shield is subjected in the current technique to a series of preparation steps before bonding. One of these steps is an attack in a chemical bath. This step makes it possible to carry out a chemical attack on the surface of the shield, which generates a certain roughness of this surface and the formation of stabilized oxides in anticipation of a durable bond. However, this chemical process can only create a low roughness (generally less than 1.2 µm) when the original substrate is very smooth, due to the chemical machining conditions.
La présente invention apporte une solution simple, efficace et économique à ce problème et permet de fonctionnaliser chimiquement la surface pour améliorer l’adhésion avec le primaire ou la colle associé.The present invention provides a simple, effective and economical solution to this problem and makes it possible to chemically functionalize the surface to improve adhesion with the associated primer or adhesive.
La présente invention propose un procédé de collage d’une pièce métallique sur un élément, par exemple en matériau composite, d’une turbomachine d’aéronef, ce procédé comprenant :The present invention proposes a method for bonding a metal part to an element, for example made of composite material, of an aircraft turbine engine, this method comprising:
a) une étape d’augmentation de la rugosité et de fonctionnalisation d’une surface de la pièce métallique,a) a step of increasing the roughness and functionalizing a surface of the metal part,
b) une étape de collage de cette surface sur l’élément,b) a step of bonding this surface to the element,
caractérisé en ce que l’étape a) comprend la fixation d’au moins une poudre métallique sur la surface, cette poudre métallique ayant une granulométrie choisie pour augmenter la rugosité de la surface.characterized in that step a) comprises fixing at least one metal powder on the surface, this metal powder having a particle size chosen to increase the roughness of the surface.
Contrairement à la technique antérieure dans laquelle la rugosité de la surface de la pièce est augmentée par attaque ou usinage chimique, et donc par enlèvement de matière, l’invention propose au contraire d’augmenter cette rugosité en ajoutant de la matière sur cette surface. Cette matière est de la poudre métallique. Cette poudre est fixée sur la surface et sa granulométrie est choisie en fonction de la rugosité désirée pour le collage. Autrement dit, la rugosité qui peut être obtenue n’est pas limitée par la pièce métallique ou un procédé de traitement. La poudre peut en outre être choisie pour accentuer l’affinité chimique de la surface par un ajout de matière spécifique, afin d’améliorer les propriétés du collage.Contrary to the prior technique in which the roughness of the surface of the part is increased by attack or chemical machining, and therefore by removal of material, the invention proposes on the contrary to increase this roughness by adding material to this surface. This material is metallic powder. This powder is fixed on the surface and its grain size is chosen according to the roughness desired for the bonding. In other words, the roughness that can be obtained is not limited by the metal part or a treatment process. The powder can also be chosen to accentuate the chemical affinity of the surface by adding specific material, in order to improve the bonding properties.
Le procédé selon l’invention peut comprendre une ou plusieurs des caractéristiques et/ou étapes ci-dessous, considérées seules ou en combinaison les unes avec les autres :The process according to the invention may comprise one or more of the characteristics and/or steps below, considered alone or in combination with each other:
- l’étape a) comprend une première sous-étape de dépôt d’au moins une poudre métallique sur la surface, et une seconde sous-étape de traitement thermique de cette poudre en vue d’en assurer la fixation sur la surface,- step a) comprises a first sub-step of depositing at least one metal powder on the surface, and a second sub-step of heat treatment of this powder in order to ensure its fixation on the surface,
- la première sous étape comprend le dépôt d’un mélange de poudre métallique et de poudre de brasage, le traitement thermique étant destiné à faire fondre la poudre de brasage et à ne pas affecter la poudre métallique dont les particules sont liées entre elles et à la surface par l’intermédiaire de la poudre de brasage fondue,- the first sub-step comprises the deposition of a mixture of metal powder and brazing powder, the heat treatment being intended to melt the brazing powder and not to affect the metal powder whose particles are bonded together and to the surface through the molten brazing powder,
- la poudre métallique comprend un métal ou un alliage métallique identique à un métal ou à un alliage métallique de la pièce métallique, et est par exemple en TA6V,- the metal powder comprises a metal or a metal alloy identical to a metal or a metal alloy of the metal part, and is for example TA6V,
- la poudre de brasage est en aluminium ou en alliage métallique à base de Al-Si, Al-Mn, Al-Mg, Ti-Cu-Ni, ou Ti-Zr-Cu-Ni,- the brazing powder is made of aluminum or a metal alloy based on Al-Si, Al-Mn, Al-Mg, Ti-Cu-Ni, or Ti-Zr-Cu-Ni,
- la première sous-étape comprend le dépôt d’une colle sur la surface, cette colle étant destinée à retenir sur la pièce le mélange de poudres déposé à la première sous-étape,- the first sub-step includes depositing an adhesive on the surface, this adhesive being intended to retain the mixture of powders deposited in the first sub-step on the part,
- la colle est déposée sur la surface par pulvérisation, à travers un motif d’un masque apposé sur cette surface,- the glue is deposited on the surface by spraying, through a pattern of a mask affixed to this surface,
- la première sous-étape comprend la préparation d’une bande adhésive à partir du mélange de poudres et d’un liant organique, cette bande adhésive étant destinée à être collée sur la surface à la première sous-étape,- the first sub-step comprises the preparation of an adhesive tape from the mixture of powders and an organic binder, this adhesive tape being intended to be bonded to the surface in the first sub-step,
- la seconde sous-étape de traitement thermique comprend le chauffage de la pièce sous vide partiel, par exemple à une température supérieure ou égale à 500°C,- the second heat treatment sub-step comprises heating the part under partial vacuum, for example to a temperature greater than or equal to 500°C,
- la seconde sous-étape de traitement thermique comprend une montée en température présentant au moins un palier, par exemple à environ 200-300°C, de façon à sublimer une éventuelle colle ou un éventuel liant utilisé(s) lors de la première sous-étape,- the second heat treatment sub-step comprises a temperature rise having at least one plateau, for example at approximately 200-300° C., so as to sublimate any glue or any binder used during the first sub-step -stage,
- la seconde sous-étape de traitement thermique comprend une montée en température présentant au moins un palier, par exemple à environ 50 à 100°C en dessous de la température maximale à atteindre afin de permettre une homogénéisation de la température de la pièce,- the second heat treatment sub-step comprises a temperature rise having at least one level, for example at around 50 to 100° C. below the maximum temperature to be reached in order to allow homogenization of the temperature of the part,
- la seconde sous-étape de traitement thermique comprend un palier de diffusion d’une durée comprise entre 1h et 10h, et à une température située à environ 10 à 100°C en dessous de la température maximale à atteindre- the second heat treatment sub-step includes a diffusion stage lasting between 1 hour and 10 hours, and at a temperature approximately 10 to 100°C below the maximum temperature to be reached
- la pièce métallique est en alliage à base de titane, et par exemple en TA6V,- the metal part is made of a titanium-based alloy, and for example TA6V,
- la poudre métallique a une granulométrie comprise entre 1 et 200μm, et de préférence entre 1 et 100μm,- the metal powder has a particle size between 1 and 200 μm, and preferably between 1 and 100 μm,
- une étape de décapage chimique de la surface peut précéder l’étape a) ou suivre l’étape b), et- a step of chemical stripping of the surface can precede step a) or follow step b), and
- à l’issue de l’étape b), la surface revêtue de poudre métallique a une rugosité supérieure ou égale comprise entre 1 et 10µm.- at the end of step b), the surface coated with metallic powder has a greater or equal roughness between 1 and 10 µm.
Brève description des figuresBrief description of figures
D'autres caractéristiques et avantages de l'invention apparaitront au cours de la lecture de la description détaillée qui va suivre pour la compréhension de laquelle on se reportera aux dessins annexés dans lesquels :Other characteristics and advantages of the invention will appear during the reading of the detailed description which will follow for the understanding of which reference will be made to the appended drawings in which:
Description détaillée de l'inventionDetailed description of the invention
La figure 1 montre une aube 10 d’hélice et en particulier de soufflante d’une turbomachine d’aéronef. Cette aube 10 comprend une pale 12 en composite à matrice organique et un bouclier métallique 14 collé sur un bord d’attaque. La pale 12 comporte en outre un bord de fuite 16, opposé au bord d’attaque, et un intrados et un extrados s’étendant entre les bords d’attaque et de fuite de la pale de la pale.FIG. 1 shows a blade 10 of a propeller and in particular of a fan of an aircraft turbomachine. This blade 10 comprises a blade 12 made of organic matrix composite and a metal shield 14 bonded to a leading edge. The blade 12 further comprises a trailing edge 16, opposite the leading edge, and a lower surface and a lower surface extending between the leading and trailing edges of the blade of the blade.
L’aube présente un axe d’allongement noté A. Une extrémité longitudinale de la pale 12 est libre et l’extrémité longitudinale opposée est reliée à un pied 18 pour la fixation de l’aube à un rotor de la turbomachine.The blade has an axis of elongation noted A. A longitudinal end of the blade 12 is free and the opposite longitudinal end is connected to a foot 18 for fixing the blade to a rotor of the turbomachine.
Comme cela est visible à la figure 2, le bouclier 14 comporte deux ailes latérales 14a s’étendant respectivement sur l’intrados et l’extrados de la pale 12, et un nez 14b reliant les deux ailes 14a.As can be seen in FIG. 2, the shield 14 has two side wings 14a extending respectively over the lower surface and the upper surface of the blade 12, and a nose 14b connecting the two wings 14a.
Les ailes 14a définissent entre elles une cavité de réception du bord d’attaque de la pale 12, ainsi que de colle de solidarisation du bouclier à la pale.The wings 14a define between them a cavity for receiving the leading edge of the blade 12, as well as glue for securing the shield to the blade.
L’invention propose un procédé de collage du bouclier 14 sur une pale 12, qui peut être appliqué à tout collage d’une pièce métallique sur un élément, par exemple en matériau composite, d’une turbomachine d’aéronef.The invention proposes a process for bonding the shield 14 to a blade 12, which can be applied to any bonding of a metal part to an element, for example made of composite material, of an aircraft turbomachine.
La figure 3 illustre un mode de réalisation du procédé selon l’invention, qui comprend essentiellement deux étapes principales : a) d’augmentation de la rugosité d’une surface de la pièce métallique, et en particulier du bouclier dans l’exemple précité, et b) de collage de la surface sur l’élément, et donc du bouclier 14 sur le bord d’attaque.FIG. 3 illustrates an embodiment of the method according to the invention, which essentially comprises two main steps: a) increasing the roughness of a surface of the metal part, and in particular of the shield in the aforementioned example, and b) bonding the surface to the element, and therefore the shield 14 to the leading edge.
Selon l’invention, l’étape a) est réalisée par ajout de matière et elle comprend plus exactement la fixation d’au moins une poudre métallique sur la surface, cette poudre métallique ayant une granulométrie choisie pour augmenter la rugosité de la surface.According to the invention, step a) is carried out by adding material and it comprises more exactly the attachment of at least one metal powder to the surface, this metal powder having a particle size chosen to increase the roughness of the surface.
Dans un mode préféré de réalisation de l’invention, l’étape a) comprend une première sous-étape (ab) de dépôt d’au moins une poudre métallique sur la surface, et une seconde sous-étape (ac) de traitement thermique de cette poudre en vue d’en assurer la fixation sur la surface.In a preferred embodiment of the invention, step a) comprises a first sub-step (ab) of depositing at least one metal powder on the surface, and a second sub-step (ac) of heat treatment of this powder in order to ensure its fixation on the surface.
De manière facultative, le procédé peut comprendre une sous-étape (aa) préliminaire de décapage de la surface de la pièce, sur laquelle l’élément est destiné à être fixé. La surface à fonctionnaliser doit en effet être propre et dégraissée jusqu'à être exempte de copeaux, de résidus, de produits de lavage, etc., et aussi être exempte d'oxydation. Egalement, de manière facultative, le procédé peut comprendre une sous-étape finale (ad) de décapage de la surface de la pièce.Optionally, the method may include a preliminary sub-step (aa) of stripping the surface of the part, on which the element is intended to be fixed. The surface to be functionalized must in fact be clean and degreased until it is free of chips, residues, washing products, etc., and also be free of oxidation. Also, optionally, the method may include a final sub-step (ad) of stripping the surface of the part.
Les figures 4a à 4d représentent un exemple de réalisation de la sous-étape (ab), et la figure 5 représente un autre exemple de réalisation de cette sous-étape (ab). Quant aux figures 6a et 6b, elles représentent un exemple de réalisation de la sous-étape (ac).FIGS. 4a to 4d represent an exemplary embodiment of sub-step (ab), and FIG. 5 represents another exemplary embodiment of this sub-step (ab). As for FIGS. 6a and 6b, they represent an exemplary embodiment of sub-step (ac).
Avantageusement, la sous étape (ab) comprend le dépôt d’un mélange de poudre métallique 10 et de poudre de brasage 12, le traitement thermique de la sous-étape (ac) étant destiné à faire fondre la poudre de brasage 12 et à ne pas affecter la poudre métallique 10 dont les particules sont liées entre elles et à la surface 14 par l’intermédiaire de la poudre de brasage fondue. Cela est rendu possible par le fait que la poudre de brasage a une température de fusion plus faible que la poudre métallique. Lors du refroidissement du lit de métal liquide, engendré par la fusion de la brasure, les poudres métalliques seront figées. Les particules métalliques ainsi figées permettront de créer une rugosité de surface.Advantageously, sub-step (ab) comprises the deposition of a mixture of metal powder 10 and brazing powder 12, the heat treatment of sub-step (ac) being intended to melt the brazing powder 12 and to not not affect the metal powder 10 whose particles are bonded together and to the surface 14 through the molten brazing powder. This is made possible by the fact that brazing powder has a lower melting temperature than metal powder. During the cooling of the bed of liquid metal, generated by the melting of the solder, the metal powders will be frozen. The metal particles thus frozen will create a surface roughness.
Dans le mode de réalisation des figures 4a à 4d, la sous-étape (ab) comprend l’apposition d’une colle 16 sur la surface 14, cette colle étant destinée à retenir le mélange de poudres déposé par la suite.In the embodiment of FIGS. 4a to 4d, sub-step (ab) comprises the affixing of an adhesive 16 to the surface 14, this adhesive being intended to retain the mixture of powders subsequently deposited.
Comme cela est illustré à la figure 4a, la colle 16 peut être déposée sur la surface 14 par pulvérisation, au moyen d’un pulvérisateur 18 contenant la colle, et à travers un motif 20a d’un masque 20 apposé sur la surface 14. Le motif 20a a une forme et des dimensions qui sont déterminées en fonction de la zone de la surface 14 sur laquelle une augmentation de rugosité est recherchée. Les avantages de la pulvérisation de colle est que la colle peut être appliquée sur une surface complexe ou non plane, comme c’est le cas d’un bord d’attaque de pale, et qu’il est plus facile de maîtriser l’épaisseur de colle déposée.As illustrated in Figure 4a, glue 16 may be deposited on surface 14 by spraying, using a sprayer 18 containing the glue, and through a pattern 20a of a mask 20 affixed to surface 14. The pattern 20a has a shape and dimensions which are determined according to the zone of the surface 14 on which an increase in roughness is sought. The advantages of glue spraying are that the glue can be applied to a complex or uneven surface, such as a blade leading edge, and it is easier to control the thickness glue deposited.
Le masque 20a est ensuite retiré (figure 4b), et le mélange de poudres 10, 12 est déposé sur la surface 14 (figure 4c). Les particules des poudres situées sur la colle 16 sont retenues par cette dernière sur la surface 14, et les autres peuvent être retirées par exemple par pulvérisation d’un flux d’air de balayage de la surface 14 (figure 4d).The mask 20a is then removed (FIG. 4b), and the mixture of powders 10, 12 is deposited on the surface 14 (FIG. 4c). The powder particles located on the glue 16 are retained by the latter on the surface 14, and the others can be removed for example by spraying a flow of air sweeping the surface 14 (FIG. 4d).
Dans la variante de la figure 5, la sous-étape (ab) comprend la préparation d’une bande adhésive 22 à partir du mélange de poudres 10, 12 et d’un liant organique 24. La bande adhésive 22 est destinée à être collée sur la surface 14 à la première sous-étape. Le liant organique comprend par exemple un polymère mélangé avec un solvant organique ou aqueux, qui se présente sous la forme d’un gel. Les avantages de cette bande 22 est que son épaisseur est maitrisée, et qu’elle peut être découpée à la forme et aux dimensions de la surface à fonctionnaliser, et enfin il est autocollant ce qui permet de la mettre facilement en place.In the variant of FIG. 5, sub-step (ab) comprises the preparation of an adhesive strip 22 from the mixture of powders 10, 12 and an organic binder 24. The adhesive strip 22 is intended to be glued on surface 14 in the first sub-step. The organic binder comprises for example a polymer mixed with an organic or aqueous solvent, which is in the form of a gel. The advantages of this strip 22 is that its thickness is controlled, and that it can be cut to the shape and dimensions of the surface to be functionalized, and finally it is self-adhesive which makes it easy to put in place.
La seconde sous-étape de traitement thermique (ac) est illustrée aux figures 6a et 6b et comprend le chauffage de la pièce sous vide partiel, par exemple à une température supérieure ou égale à 500°C pour faire fondre la poudre de brasage. Dans un cas particulier où la poudre de brasage utilisée est du Al-Mg (série 40000) et plus précisément la poudre AG5 (Al-5% Mg), le cycle de brasage peut être de 10 minutes à 660°C sous vide à 10-2Pa.The second heat treatment sub-step (ac) is illustrated in Figures 6a and 6b and comprises heating the part under partial vacuum, for example at a temperature greater than or equal to 500° C. to melt the brazing powder. In a particular case where the brazing powder used is Al-Mg (40000 series) and more precisely AG5 powder (Al-5% Mg), the brazing cycle can be 10 minutes at 660°C under vacuum at 10 -2 Pa.
Lors du chauffage, la température est augmentée progressivement et cette montée en température comprend de préférence au moins un palier, par exemple à environ 200-300°C, de façon à sublimer la colle 16 ou le liant 24 utilisé lors de la sous-étape (ab).During heating, the temperature is gradually increased and this rise in temperature preferably comprises at least one level, for example at approximately 200-300° C., so as to sublimate the glue 16 or the binder 24 used during the sub-step (ab).
La poudre métallique 10 comprend de préférence un métal ou un alliage métallique identique à un métal ou à un alliage métallique de la pièce métallique, qui est par exemple en TA6V. La poudre métallique 10 a une granulométrie comprise entre 1 et 200μm, et de préférence entre 1 et 100μm.The metal powder 10 preferably comprises a metal or a metal alloy identical to a metal or a metal alloy of the metal part, which is for example TA6V. The metal powder 10 has a particle size between 1 and 200 μm, and preferably between 1 and 100 μm.
La poudre de brasage 12 peut être en aluminium ou en alliage métallique à base de Al-Si, Al-Mn, Al-Mg, Ti-Cu-Ni, ou Ti-Zr-Cu-Ni.Brazing powder 12 can be aluminum or a metal alloy based on Al-Si, Al-Mn, Al-Mg, Ti-Cu-Ni, or Ti-Zr-Cu-Ni.
L’invention peut permettre de conférer à la surface traitée une rugosité supérieure ou égale comprise entre 1 et 10µm.The invention can make it possible to give the treated surface a greater or equal roughness of between 1 and 10 μm.
Claims (10)
a) une étape d’augmentation de la rugosité et de fonctionnalisation de la surface de la pièce métallique,
b) une étape de collage de cette surface sur l’élément,
caractérisé en ce que l’étape a) comprend la fixation d’au moins une poudre métallique (10, 12) sur la surface (14), cette poudre métallique ayant une granulométrie choisie pour augmenter la rugosité de la surface.Method for bonding a metal part to an element, for example made of composite material, of an aircraft turbomachine, this method comprising:
a) a step of increasing the roughness and functionalizing the surface of the metal part,
b) a step of bonding this surface to the element,
characterized in that step a) comprises fixing at least one metal powder (10, 12) on the surface (14), this metal powder having a particle size chosen to increase the roughness of the surface.
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FR1903352A FR3094253B1 (en) | 2019-03-29 | 2019-03-29 | PROCESS FOR BONDING A METALLIC PART ON A COMPOSITE MATERIAL ELEMENT OF AN AIRCRAFT TURBOMACHINE |
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FR1903352A FR3094253B1 (en) | 2019-03-29 | 2019-03-29 | PROCESS FOR BONDING A METALLIC PART ON A COMPOSITE MATERIAL ELEMENT OF AN AIRCRAFT TURBOMACHINE |
FR1903352 | 2019-03-29 |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
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FR3141965A1 (en) * | 2022-11-14 | 2024-05-17 | Safran | BLADE FOR AIRCRAFT TURBOMACHINE AND ASSOCIATED MANUFACTURING METHOD |
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