FR3133335A1 - Process for manufacturing a part and a test piece - Google Patents
Process for manufacturing a part and a test piece Download PDFInfo
- Publication number
- FR3133335A1 FR3133335A1 FR2202208A FR2202208A FR3133335A1 FR 3133335 A1 FR3133335 A1 FR 3133335A1 FR 2202208 A FR2202208 A FR 2202208A FR 2202208 A FR2202208 A FR 2202208A FR 3133335 A1 FR3133335 A1 FR 3133335A1
- Authority
- FR
- France
- Prior art keywords
- preform
- reinforcement
- resin
- intended
- mold
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 10
- 238000000034 method Methods 0.000 title claims description 23
- 230000002787 reinforcement Effects 0.000 claims abstract description 48
- 229920005989 resin Polymers 0.000 claims abstract description 20
- 239000011347 resin Substances 0.000 claims abstract description 20
- 239000002699 waste material Substances 0.000 claims abstract description 18
- 239000011159 matrix material Substances 0.000 claims abstract description 10
- 239000003292 glue Substances 0.000 claims description 12
- 238000000926 separation method Methods 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 3
- 229920000647 polyepoxide Polymers 0.000 claims description 3
- 239000002759 woven fabric Substances 0.000 claims description 3
- 229910052751 metal Inorganic materials 0.000 description 9
- 239000002184 metal Substances 0.000 description 9
- 239000002131 composite material Substances 0.000 description 5
- 238000004026 adhesive bonding Methods 0.000 description 3
- 238000000465 moulding Methods 0.000 description 3
- 230000035882 stress Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 239000011888 foil Substances 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000006116 polymerization reaction Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 238000003908 quality control method Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 238000011179 visual inspection Methods 0.000 description 1
Classifications
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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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
- B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/02—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements, e.g. non-specified reinforcements, fibrous reinforcing inserts and fillers, e.g. particulate fillers, incorporated in matrix material, forming one or more layers and with or without non-reinforced or non-filled layers
- B29C70/021—Combinations of fibrous reinforcement and non-fibrous material
- B29C70/023—Combinations of fibrous reinforcement and non-fibrous material with reinforcing inserts
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/545—Perforating, cutting or machining during or after moulding
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/78—Moulding material on one side only of the preformed part
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
- B29C70/887—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced locally reinforced, e.g. by fillers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
-
- 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
- B29C2793/00—Shaping techniques involving a cutting or machining operation
- B29C2793/0027—Cutting off
-
- 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
- B29C2793/00—Shaping techniques involving a cutting or machining operation
- B29C2793/009—Shaping techniques involving a cutting or machining operation after shaping
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
-
- 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
-
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
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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
- F05D2260/00—Function
- F05D2260/83—Testing, e.g. methods, components or tools therefor
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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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Textile Engineering (AREA)
- Processing And Handling Of Plastics And Other Materials For Molding In General (AREA)
- Reinforced Plastic Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
L’invention concerne un procédé de fabrication d’au moins une pièce (1) et d’au moins une éprouvette de caractérisation d’une telle pièce (1), caractérisé en ce qu’il comporte les étapes consistant à placer au moins une préforme tissée dans un moule, ladite préforme étant destinée à former un renfort fibreux de la pièce (1), placer au moins un renfort principal (9) dans ledit moule au niveau d’au moins une zone principale (2) de la préforme, placer au moins un renfort auxiliaire (10) au niveau d’au moins une zone auxiliaire de la préforme destinée à former une zone de rebut (8) de la pièce (1), insérer une résine dans ledit moule, ladite résine étant destinée à former une matrice, chauffer le moule de façon à polymériser ladite résine et à former ladite pièce (1), séparer au moins une zone de rebut (8) de la pièce (1). Figure à publier avec l’abrégé : [Fig. 3]The invention relates to a method of manufacturing at least one part (1) and at least one test piece for characterizing such a part (1), characterized in that it comprises the steps consisting of placing at least one preform woven in a mold, said preform being intended to form a fibrous reinforcement of the part (1), placing at least one main reinforcement (9) in said mold at least one main zone (2) of the preform, place at least one auxiliary reinforcement (10) at least one auxiliary zone of the preform intended to form a waste zone (8) of the part (1), insert a resin into said mold, said resin being intended to form a matrix, heat the mold so as to polymerize said resin and form said part (1), separate at least one waste zone (8) from the part (1). Figure to be published with the abstract: [Fig. 3]
Description
L’invention concerne un procédé de fabrication d’au moins une pièce et d’au moins une éprouvette de caractérisation d’une telle pièce.The invention relates to a method of manufacturing at least one part and at least one test piece for characterizing such a part.
Afin de réduire la masse et d’augmenter les capacités thermodynamiques de pièces de turbomachine, il est connu de réaliser certaines pièces en matériau composite obtenu à partir d’un renfort fibreux tissé, noyé dans une matrice polymère.In order to reduce the mass and increase the thermodynamic capacities of turbomachine parts, it is known to make certain parts in composite material obtained from a woven fibrous reinforcement, embedded in a polymer matrix.
Il est notamment connu de réaliser des aubes en matériau composite, de telles aubes étant destinées à s’étendre dans une veine d’écoulement d’un flux d’air. Chaque aube comporte classiquement une pale et un pied, la pale comprenant une surface d’intrados et une surface d’extrados reliées l’une à l’autre, à l’amont, par un bord d’attaque et, à l’aval, par un bord de fuite. Le bord d’attaque est exposé aux corps étrangers extérieurs pouvant pénétrer dans la veine d’écoulement d’air, tels que du sable, des grêlons ou encore des oiseaux.It is particularly known to make blades of composite material, such blades being intended to extend in a flow path of an air flow. Each blade conventionally comprises a blade and a root, the blade comprising an intrados surface and an extrados surface connected to each other, upstream, by a leading edge and, downstream , by a trailing edge. The leading edge is exposed to external foreign bodies that may enter the air flow path, such as sand, hailstones or even birds.
Le matériau composite étant sensible aux impacts de tels corps étrangers, différentes solutions ont été développés afin de protéger les bords d’attaque de tels impacts. En particulier, il est connu de rapporter un renfort métallique sur le bord d’attaque, par collage. Ce renfort métallique se présente par exemple sous la forme d’un cliquant qui a été préalablement formé de manière à présenter une forme tridimensionnelle correspondant à la forme tridimensionnelle du bord d’attaque de l’aube à protéger, un film de colle étant appliqué entre le cliquant et ledit bord d’attaque.The composite material being sensitive to the impacts of such foreign bodies, different solutions have been developed to protect the leading edges from such impacts. In particular, it is known to add a metal reinforcement to the leading edge, by gluing. This metal reinforcement is for example in the form of a click which has been previously formed so as to have a three-dimensional shape corresponding to the three-dimensional shape of the leading edge of the blade to be protected, a film of glue being applied between clicking it and said leading edge.
Le document FR 3 090 465 divulgue un procédé de fabrication d’une pièce dans lequel une préforme tissée est placée dans un moule, ladite préforme étant destinée à former un renfort fibreux de la pièce, un renfort métallique étant également placé dans le moule, au niveau du bord d’attaque de la pièce à réaliser. Le renfort métallique se présente sous la forme d’un tissu métallique. Une résine destinée à former la matrice est ensuite injectée dans le moule, puis polymérisée par chauffage du moule. Après polymérisation de la résine, une pièce est obtenue, cette pièce comportant alors une structure de renfort métallique intégrée au bord d’attaque de la pièce.Document FR 3 090 465 discloses a process for manufacturing a part in which a woven preform is placed in a mold, said preform being intended to form a fibrous reinforcement of the part, a metal reinforcement also being placed in the mold, at level of the leading edge of the part to be produced. The metal reinforcement comes in the form of a metal fabric. A resin intended to form the matrix is then injected into the mold, then polymerized by heating the mold. After polymerization of the resin, a part is obtained, this part then comprising a metal reinforcement structure integrated into the leading edge of the part.
Le renfort métallique est ainsi moulé en même temps que la préforme.The metal reinforcement is thus molded at the same time as the preform.
La fabrication de pièces composites et les opérations de collage sont des procédés nécessitant un contrôle qualité continu ou périodique des pièces. Deux techniques sont utilisées communément afin d’assurer un tel contrôle.The manufacturing of composite parts and bonding operations are processes requiring continuous or periodic quality control of the parts. Two techniques are commonly used to ensure such control.
Une première technique consiste à fabriquer une éprouvette d’essai mécanique attenante à la pièce, en même temps que cette dernière.A first technique consists of manufacturing a mechanical test specimen adjacent to the part, at the same time as the latter.
L’inconvénient d’une telle technique est que l’éprouvette subit des contraintes thermiques qui ne sont pas exactement celles de la pièce, rendant cette éprouvette peu représentative de la pièce.The disadvantage of such a technique is that the specimen undergoes thermal stresses which are not exactly those of the part, making this specimen unrepresentative of the part.
Une seconde technique est de réaliser une dissection d’une pièce de manière périodique.A second technique is to dissect a part periodically.
L’inconvénient d’une telle technique est qu’elle est principalement une technique de contrôle visuel qui ne permet en général pas d’obtenir des données mécaniques quantitatives, par exemple au travers d’essais mécaniques. Par ailleurs, une telle technique, du fait de son caractère destructif, ne peut être réalisée que par échantillonnage et ne permet pas de caractériser l’ensemble des pièces fabriquées.The disadvantage of such a technique is that it is mainly a visual inspection technique which generally does not make it possible to obtain quantitative mechanical data, for example through mechanical tests. Furthermore, such a technique, due to its destructive nature, can only be carried out by sampling and does not make it possible to characterize all of the parts manufactured.
Il est à noter également que la bonne exécution d’une opération de collage dépend de nombreux paramètres et que, en cas de défaut d’un tel collage, il est difficile de déterminer quel est le paramètre à l’origine d’un tel défaut.It should also be noted that the proper execution of a gluing operation depends on numerous parameters and that, in the event of a defect in such gluing, it is difficult to determine which parameter is the cause of such a defect. .
L’invention vise à proposer une solution aux problèmes décrits ci-dessus.The invention aims to propose a solution to the problems described above.
A cet effet, l’invention concerne un procédé de fabrication d’au moins une pièce et d’au moins une éprouvette de caractérisation d’une telle pièce, caractérisé en ce qu’il comporte les étapes consistant à :To this end, the invention relates to a method of manufacturing at least one part and at least one test piece for characterizing such a part, characterized in that it comprises the steps consisting of:
- placer au moins une préforme tissée dans un moule, ladite préforme étant destinée à former un renfort fibreux de la pièce,- place at least one woven preform in a mold, said preform being intended to form a fibrous reinforcement of the part,
- placer au moins un renfort principal dans ledit moule au niveau d’au moins une zone principale de la préforme,- place at least one main reinforcement in said mold at least one main zone of the preform,
- placer au moins un renfort auxiliaire au niveau d’au moins une zone auxiliaire de la préforme destinée à former une zone de rebut de la pièce,- place at least one auxiliary reinforcement at the level of at least one auxiliary zone of the preform intended to form a waste zone of the part,
- insérer une résine dans ledit moule, ladite résine étant destinée à former une matrice,- insert a resin into said mold, said resin being intended to form a matrix,
- chauffer le moule de façon à polymériser ladite résine et à former ladite pièce,- heat the mold so as to polymerize said resin and form said part,
- séparer au moins une zone de rebut de la pièce, ladite zone de rebut étant apte à former une éprouvette de caractérisation de la pièce, ladite zone de rebut comportant un renfort fibreux formé par une partie de la préforme et noyé dans une matrice formée par la résine polymérisée, et un renfort auxiliaire solidaire de la matrice et du renfort fibreux.- separate at least one waste zone from the part, said waste zone being capable of forming a test piece for characterizing the part, said waste zone comprising a fibrous reinforcement formed by a part of the preform and embedded in a matrix formed by the polymerized resin, and an auxiliary reinforcement integral with the matrix and the fibrous reinforcement.
Le procédé permet ainsi d’obtenir, lors d’un unique cycle de moulage, une pièce composite et une ou plusieurs éprouvettes représentatives de la pièce, c’est-à-dire ayant été soumises aux mêmes contraintes thermiques et mécaniques que la pièce lors du moulage.The process thus makes it possible to obtain, during a single molding cycle, a composite part and one or more specimens representative of the part, that is to say having been subjected to the same thermal and mechanical stresses as the part during molding.
Un tel procédé permet ainsi de réaliser des tests permettant de quantifier précisément différents paramètres de l’interface de collage. Les tests réalisés peuvent par exemple permettre de quantifier la résistance au pelage de l’interface de collage, la résistance à l’impact de l’interface de collage ou tout autre essai permettant de caractériser les propriétés mécaniques d’intérêt représentative des sollicitations de la pièce lors de son service.Such a process thus makes it possible to carry out tests making it possible to precisely quantify different parameters of the bonding interface. The tests carried out can for example make it possible to quantify the peel resistance of the bonding interface, the impact resistance of the bonding interface or any other test making it possible to characterize the mechanical properties of interest representative of the stresses of the part during its service.
Dans le cas de la réalisation de plusieurs éprouvettes dans des zones de rebut situées en plusieurs endroits du moule, il est également possible de caractériser l’homogénéité du moule, et donc de la pièce réalisée.In the case of producing several test pieces in scrap zones located in several places in the mold, it is also possible to characterize the homogeneity of the mold, and therefore of the part produced.
La pièce est une aube de turbomachine.The part is a turbomachine blade.
La pièce est par exemple une aube de soufflante de la turbomachine ou une aube directrice, par exemple une aube de type OGV (pour Outlet Guide Vane en anglais).The part is for example a fan blade of the turbomachine or a guide vane, for example an OGV type blade (for Outlet Guide Vane in English).
L’aube peut comporter une pale et un pied, ladite pale comportant une première extrémité rattachée au pied et une seconde extrémité opposée à la première extrémité, ladite pale comportant en outre une surface d’intrados et une surface d’extrados reliées par un bord d’attaque et par un bord de fuite, au moins un renfort principal étant situé dans une zone de la préforme destinée à former le bord d’attaque, au moins un renfort auxiliaire étant situé dans une zone destinée à former une zone de rebut, à proximité du bord d’attaque et/ou à proximité de la seconde extrémité et/ou à proximité du pied.The blade may comprise a blade and a foot, said blade comprising a first end attached to the foot and a second end opposite the first end, said blade further comprising an intrados surface and an extrados surface connected by an edge leading edge and by a trailing edge, at least one main reinforcement being located in a zone of the preform intended to form the leading edge, at least one auxiliary reinforcement being located in a zone intended to form a waste zone, near the leading edge and/or near the second end and/or near the foot.
Les zones de rebut destinées à former des éprouvettes peuvent ainsi être situées à des endroits d’intérêt de l’aube, où la caractérisation de cette dernière par des essais mécaniques, optiques ou thermiques par exemple est la plus importante.The scrap zones intended to form test pieces can thus be located at places of interest on the blade, where the characterization of the latter by mechanical, optical or thermal tests for example is the most important.
Le renfort principal et/ou le renfort auxiliaire peuvent être métalliques.The main reinforcement and/or the auxiliary reinforcement may be metallic.
Le renfort principal et le renfort auxiliaire peuvent se présenter sous la forme de clinquants métalliques ou sous la forme de tissus métalliques.The main reinforcement and the auxiliary reinforcement can be in the form of metal foils or in the form of metal fabrics.
Un film de colle peut être appliqué entre le renfort principal et/ou le renfort auxiliaire, d’une part, et la préforme, d’autre part.A film of glue can be applied between the main reinforcement and/or the auxiliary reinforcement, on the one hand, and the preform, on the other hand.
La colle est par exemple une résine époxy.The glue is for example an epoxy resin.
En variante, l’adhésion entre le renfort principal ou le renfort auxiliaire et le reste de la préforme peut être obtenu directement à l’aide de la résine servant de matrice.Alternatively, adhesion between the main reinforcement or the auxiliary reinforcement and the rest of the preform can be obtained directly using the resin serving as a matrix.
La préforme peut être réalisée en tissu tissé en trois dimensions, à base de fibres de carbone.The preform can be made from a three-dimensional woven fabric, based on carbon fibers.
La préforme et la résine peuvent être chauffés à une température comprise entre 80 et 200°C, pendant une durée comprise entre 2 et 6 heures.The preform and the resin can be heated to a temperature between 80 and 200°C, for a period of between 2 and 6 hours.
La séparation entre la zone de rebut et la pièce peut être réalisée par usinage. En variante, une telle séparation peut être réalisée par simple retrait manuel de la pièce, par exemple dans le cas où la zone de rebut est positionnée dans une cavité séparée du moule.The separation between the scrap area and the part can be achieved by machining. Alternatively, such separation can be achieved by simple manual removal of the part, for example in the case where the scrap zone is positioned in a separate cavity of the mold.
La
La pièce 1 est par exemple une aube de soufflante de la turbomachine ou une aube directrice, par exemple une aube de type OGV (pour Outlet Guide Vane en anglais).Part 1 is for example a fan blade of the turbomachine or a guide vane, for example an OGV type blade (for Outlet Guide Vane in English).
Comme illustré à la
Ce procédé comporte une étape E1 consistant à placer au moins une préforme tissée dans une cavité d’un moule d’injection, ladite préforme étant destinée à former un renfort fibreux de la pièce.This method comprises a step E1 consisting of placing at least one woven preform in a cavity of an injection mold, said preform being intended to form a fibrous reinforcement of the part.
La préforme peut être réalisée en tissu tissé en trois dimensions, à base de fibres de carbone.The preform can be made from a three-dimensional woven fabric, based on carbon fibers.
Un film de colle est ensuite apposé, lors d’une étape E2, sur des zones destinées à former la pièce 1 et des zones 8 destinées à former des zones de rebut qui, après séparation avec la pièce 1, pourront former des éprouvettes destinées à caractériser la pièce 1.A film of glue is then applied, during a step E2, to areas intended to form part 1 and areas 8 intended to form waste areas which, after separation with part 1, can form test pieces intended to characterize part 1.
Par exemple, un film de colle peut être apposé du niveau du bord d’attaque 6 et au niveau de zones de rebut 8 situées en dehors de la pièce 1 et à proximité du bord d’attaque 6, à proximité de la seconde extrémité 5 et à proximité du pied 3. La colle est par exemple une résine époxy.For example, a film of glue can be applied at the level of the leading edge 6 and at the level of waste areas 8 located outside the part 1 and near the leading edge 6, near the second end 5 and near the foot 3. The glue is for example an epoxy resin.
Lors d’une étape E3, un renfort principal 9 est apposé sur le film de colle de la pièce 1 et des renforts auxiliaires 10 sont apposés sur les films de colle des zones de rebut 8.During a step E3, a main reinforcement 9 is affixed to the glue film of part 1 and auxiliary reinforcements 10 are affixed to the glue films of the waste areas 8.
Chaque renfort 9, 10 peut se présenter sous la forme d’un cliquant métallique, réalisé par exemple en Titane. Le renfort principal 9 peut présenter une forme tridimensionnelle correspondant à la forme du bord d’attaque 6. Les renforts auxiliaires 10 peuvent se présenter sous la forme de clinquants plans ou globalement plans.Each reinforcement 9, 10 can be in the form of a metallic click, made for example of Titanium. The main reinforcement 9 may have a three-dimensional shape corresponding to the shape of the leading edge 6. The auxiliary reinforcements 10 may be in the form of planar or generally planar foils.
Le moule est ensuite refermé puis, lors d’une étape E4, de la résine est injecté, la préforme, la résine, les films de colle et les renforts 9, 10 étant soumis à une température permettant la polymérisation de la résine et du film de colle. Ces éléments sont par exemple soumis à une température comprise entre 80 et 200°C, pendant une durée comprise entre 2 et 6 heures. La pression d’injection de la résine est par exemple comprise entre 10 et 30 bars.The mold is then closed then, during a step E4, resin is injected, the preform, the resin, the glue films and the reinforcements 9, 10 being subjected to a temperature allowing the polymerization of the resin and the film of glue. These elements are for example subjected to a temperature of between 80 and 200°C, for a period of between 2 and 6 hours. The resin injection pressure is for example between 10 and 30 bars.
Ensuite, lors d’une étape E5, les zones de rebut 8 sont séparées de la pièce 1, par exemple par usinage. Comme indiqué précédemment, ces zones de rebut 8 sont destinées à former des éprouvettes représentatives de la pièce 1, c’est-à-dire ayant été soumises aux mêmes contraintes thermiques et mécaniques que la pièce 1 lors du moulage.
Then, during a step E5, the waste zones 8 are separated from part 1, for example by machining. As indicated previously, these waste zones 8 are intended to form specimens representative of part 1, that is to say having been subjected to the same thermal and mechanical stresses as part 1 during molding.
Claims (9)
- placer au moins une préforme tissée dans un moule, ladite préforme étant destinée à former un renfort fibreux de la pièce (1),
- placer au moins un renfort principal (9) dans ledit moule au niveau d’au moins une zone principale (2) de la préforme,
- placer au moins un renfort auxiliaire (10) au niveau d’au moins une zone auxiliaire de la préforme destinée à former une zone de rebut (8) de la pièce (1),
- insérer une résine dans ledit moule, ladite résine étant destinée à former une matrice,
- chauffer le moule de façon à polymériser ladite résine et à former ladite pièce (1),
- séparer au moins une zone de rebut (8) de la pièce (1), ladite zone de rebut (8) étant apte à former une éprouvette de caractérisation de la pièce (1), ladite zone de rebut (8) comportant un renfort fibreux formé par une partie de la préforme et noyé dans une matrice formée par la résine polymérisée, et un renfort auxiliaire solidaire de la matrice et du renfort fibreux.
- placing at least one woven preform in a mold, said preform being intended to form a fibrous reinforcement of the part (1),
- placing at least one main reinforcement (9) in said mold at least one main zone (2) of the preform,
- placing at least one auxiliary reinforcement (10) at least one auxiliary zone of the preform intended to form a waste zone (8) of the part (1),
- insert a resin into said mold, said resin being intended to form a matrix,
- heat the mold so as to polymerize said resin and form said part (1),
- separate at least one waste zone (8) from the part (1), said waste zone (8) being capable of forming a test piece for characterizing the part (1), said waste zone (8) comprising a fibrous reinforcement formed by a part of the preform and embedded in a matrix formed by the polymerized resin, and an auxiliary reinforcement integral with the matrix and the fibrous reinforcement.
Method according to one of the preceding claims, in which the separation between the waste zone (8) and the part (1) is produced by machining.
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Citations (4)
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JP2010150685A (en) * | 2008-12-24 | 2010-07-08 | Toray Ind Inc | Bent-shaped reinforcing fiber base material, laminate using the same, preform, fiber-reinforced resin composite material and methods for producing them |
US9884457B1 (en) * | 2010-07-22 | 2018-02-06 | Benjamin V. Booher | Composite friction elements and pultrusion method of making same |
FR3090465A1 (en) | 2018-12-20 | 2020-06-26 | Safran | PROCESS FOR MANUFACTURING A TURBOMACHINE PART IN COMPOSITE MATERIAL AND CORRESPONDING TURBOMACHINE PART |
EP3776682B1 (en) * | 2018-03-28 | 2022-02-09 | Safran | Method of manufacturing a composite blade with a metallic leading edge for a gas turbine |
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2022
- 2022-03-14 FR FR2202208A patent/FR3133335B1/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
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JP2010150685A (en) * | 2008-12-24 | 2010-07-08 | Toray Ind Inc | Bent-shaped reinforcing fiber base material, laminate using the same, preform, fiber-reinforced resin composite material and methods for producing them |
US9884457B1 (en) * | 2010-07-22 | 2018-02-06 | Benjamin V. Booher | Composite friction elements and pultrusion method of making same |
EP3776682B1 (en) * | 2018-03-28 | 2022-02-09 | Safran | Method of manufacturing a composite blade with a metallic leading edge for a gas turbine |
FR3090465A1 (en) | 2018-12-20 | 2020-06-26 | Safran | PROCESS FOR MANUFACTURING A TURBOMACHINE PART IN COMPOSITE MATERIAL AND CORRESPONDING TURBOMACHINE PART |
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