FR3121382A1 - Repair of a composite material part - Google Patents

Repair of a composite material part Download PDF

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Publication number
FR3121382A1
FR3121382A1 FR2103259A FR2103259A FR3121382A1 FR 3121382 A1 FR3121382 A1 FR 3121382A1 FR 2103259 A FR2103259 A FR 2103259A FR 2103259 A FR2103259 A FR 2103259A FR 3121382 A1 FR3121382 A1 FR 3121382A1
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FR
France
Prior art keywords
composite material
recessed portion
filler piece
filler
fibrous
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
Application number
FR2103259A
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French (fr)
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FR3121382B1 (en
Inventor
Matthieu Patrick Jean Roger Perlin
Geneviève MOUGEY
Mattéo MINERVINO
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2103259A priority Critical patent/FR3121382B1/en
Publication of FR3121382A1 publication Critical patent/FR3121382A1/en
Application granted granted Critical
Publication of FR3121382B1 publication Critical patent/FR3121382B1/en
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Classifications

    • 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
    • B29C70/04—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
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • 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
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-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
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
    • 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
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
    • B29C73/06—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements using plugs sealing in the hole
    • 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
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/24—Apparatus or accessories not otherwise provided for
    • B29C73/30—Apparatus or accessories not otherwise provided for for local pressing or local heating
    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B11/00—Making preforms
    • B29B11/14—Making preforms characterised by structure or composition
    • B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
    • 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
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/24—Apparatus or accessories not otherwise provided for
    • B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
    • B29C2073/264—Apparatus or accessories not otherwise provided for for mechanical pretreatment for cutting out or grooving the area to be repaired
    • 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
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/18—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated tools
    • 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
    • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
    • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
    • B29C65/4835—Heat curing adhesives
    • 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
    • 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
    • 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
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
    • B29C66/812—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the composition, by the structure, by the intensive physical properties or by the optical properties of the material constituting the pressing elements, e.g. constituting the welding jaws or clamps
    • B29C66/8122—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the composition, by the structure, by the intensive physical properties or by the optical properties of the material constituting the pressing elements, e.g. constituting the welding jaws or clamps characterised by the composition of the material constituting the pressing elements, e.g. constituting the welding jaws or clamps
    • 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
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/24—Apparatus or accessories not otherwise provided for
    • B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
    • B29K2105/0809—Fabrics
    • B29K2105/0827—Braided fabrics
    • 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
    • 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
    • B29L2031/748—Machines or parts thereof not otherwise provided for
    • B29L2031/7504—Turbines
    • 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
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/10—Fibres of continuous length
    • B32B2305/18—Fabrics, textiles
    • B32B2305/184—Braided fabrics
    • 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
    • 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
    • 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
    • F05D2300/6034—Orientation of fibres, weaving, ply angle

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Textile Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Woven Fabrics (AREA)
  • Reinforced Plastic Materials (AREA)

Abstract

Réparation d’une pièce en matériau composite Procédé de réparation d’une pièce en matériau composite (1) comprenant un renfort fibreux présentant un tissage tridimensionnel caractérisé en ce qu’il comprend : - l’identification d’au moins une zone endommagée (20) à la surface de l’aube (11), - la réalisation d’une portion évidée (40) par retrait du matériau composite au niveau de la zone endommagée (20), - le tissage tridimensionnel d’une préforme fibreuse de comblement ayant une forme correspondant à la forme de la portion évidée (40), - l’imprégnation de la préforme fibreuse de la pièce de comblement avec une résine précurseur d’une matrice, - la polymérisation de la résine en matrice afin d’obtenir une pièce de comblement (4) en matériau composite comprenant une préforme fibreuse tissée 3D, - le collage de la pièce de comblement (4) dans la portion évidée (40), ladite pièce de comblement occupant le volume défini par la portion évidée. Figure pour l’abrégé : Fig. 7Repairing a part made of composite material Method for repairing a part made of composite material (1) comprising a fibrous reinforcement having a three-dimensional weave, characterized in that it comprises: - the identification of at least one damaged zone (20 ) on the surface of the blade (11), - the production of a recessed portion (40) by removing the composite material at the level of the damaged zone (20), - the three-dimensional weaving of a fibrous filler preform having a shape corresponding to the shape of the recessed portion (40), - the impregnation of the fibrous preform of the filler piece with a resin precursor of a matrix, - the polymerization of the resin in matrix in order to obtain a piece filler (4) made of composite material comprising a 3D woven fiber preform, - gluing the filler (4) in the recessed portion (40), said filler occupying the volume defined by the recessed portion. Figure for abstract: Fig. 7

Description

Réparation d’une pièce en matériau compositeRepair of a composite material part

L’invention concerne les réparations de pièces en matériau composite de turbomachines, et plus particulièrement, mais non exclusivement, les réparations d’aubes pour moteurs aéronautiques.The invention relates to the repair of composite material parts of turbomachines, and more particularly, but not exclusively, the repair of blades for aeronautical engines.

Précédemment réalisées en matériau métallique, les aubes de turbomachines sont maintenant réalisées en matériau composite, c’est-à-dire à partir d’une préforme fibreuse densifiée par une matrice, ce qui permet de réaliser des pièces ayant une masse globale moins élevée que ces mêmes pièces lorsqu'elles sont réalisées en matériau métallique tout en présentant une résistance mécanique au moins équivalente sinon supérieure. Les aubes peuvent notamment posséder un renfort fibreux réalisé par tissage tridimensionnel, afin d’améliorer encore leurs propriétés mécaniques.Previously made of metallic material, turbine engine blades are now made of composite material, that is to say from a fibrous preform densified by a matrix, which makes it possible to produce parts having an overall mass lower than these same parts when they are made of metallic material while having at least equivalent if not greater mechanical strength. The blades may in particular have a fibrous reinforcement produced by three-dimensional weaving, in order to further improve their mechanical properties.

Si l’utilisation d’aubes en matériau composite permet de réduire la masse globale de la turbomachine, leur réparation en cas d’endommagement peut être problématique. En effet, une solution existante, comme celle décrite dans le document US 2007/0095457, consiste à coller un patch fibreux pré-imprégné sur la zone endommagée ou la zone à reprendre de la pièce en matériau composite, le patch pouvant être constitué d’un ou plusieurs plis fibreux. Toutefois, ce type de solution présente un risque de délaminage du patch collé et fait perdre une partie des avantages d’un tissage tridimensionnel.If the use of blades made of composite material makes it possible to reduce the overall mass of the turbomachine, their repair in the event of damage can be problematic. Indeed, an existing solution, such as that described in document US 2007/0095457, consists in sticking a pre-impregnated fibrous patch on the damaged zone or the zone to be repaired of the part made of composite material, the patch possibly consisting of one or more fibrous folds. However, this type of solution presents a risk of delamination of the bonded patch and loses some of the advantages of a three-dimensional weaving.

Le document WO2020178500 propose une solution plus adaptée aux pièces réalisées par tissage tridimensionnel, qui consiste à évider la zone endommagée de la pièce et à la combler par une préforme fibreuse pré-imprégnée. La préforme fibreuse est pré-imprégnée avant ou après avoir été insérée dans la portion évidée, et est ensuite polymérisée afin d’adhérer totalement à la pièce à réparer. Toutefois, cette solution requiert un outillage complet et une installation conséquente pour pouvoir pré-imprégner et polymériser la préforme fibreuse de comblement dans la pièce à réparer. Cette méthode de réparation n’est donc pas adaptée à tous les sites de réparation. En outre, cette méthode de réparation implique un faible contrôle de la géométrie de la préforme fibreuse de comblement, du fait de son caractère pré-imprégné. Ainsi, ses dimensions peuvent difficilement être corrigées si l’insertion pose problème.Document WO2020178500 proposes a solution more suitable for parts made by three-dimensional weaving, which consists in hollowing out the damaged zone of the part and filling it with a pre-impregnated fibrous preform. The fibrous preform is pre-impregnated before or after being inserted into the hollowed out portion, and is then polymerized in order to fully adhere to the part to be repaired. However, this solution requires complete tools and substantial installation to be able to pre-impregnate and polymerize the fibrous filler preform in the part to be repaired. This repair method is therefore not suitable for all repair sites. In addition, this repair method involves little control of the geometry of the fibrous filling preform, due to its pre-impregnated character. Thus, its dimensions can hardly be corrected if the insertion poses a problem.

L’invention a pour but de proposer une solution pour la réparation d’une pièce en matériau composite réalisée par tissage tridimensionnel, par exemple une aube de turbomachine, ne présentant pas les inconvénients de l’art antérieur.The aim of the invention is to propose a solution for repairing a part made of composite material produced by three-dimensional weaving, for example a turbine engine blade, which does not have the drawbacks of the prior art.

Ce but est atteint grâce à un procédé de réparation d’une pièce en matériau composite comprenant un renfort fibreux présentant un tissage tridimensionnel entre une pluralité de fils de chaîne et une pluralité de fils de trame, le dit renfort fibreux étant densifié par une matrice, caractérisé en ce qu’il comprend :This object is achieved by means of a method for repairing a part made of composite material comprising a fibrous reinforcement having a three-dimensional weave between a plurality of warp threads and a plurality of weft threads, the said fibrous reinforcement being densified by a matrix, characterized in that it comprises:

- l’identification d’au moins une zone endommagée à la surface de la pièce,- the identification of at least one damaged area on the surface of the part,

- la réalisation d’une portion évidée par retrait du matériau composite au niveau de la zone endommagée,- creating a hollowed out portion by removing the composite material from the damaged area,

- le tissage tridimensionnel d’une préforme fibreuse de comblement ayant une forme correspondant à la forme de la portion évidée,- the three-dimensional weaving of a fibrous filling preform having a shape corresponding to the shape of the hollowed out portion,

- l’imprégnation de la préforme fibreuse de la pièce de comblement avec une résine précurseur d’une matrice,- impregnation of the fibrous preform of the filler piece with a resin precursor of a matrix,

- la polymérisation de la résine en matrice afin d’obtenir une pièce de comblement en matériau composite comprenant une préforme fibreuse tissée 3D,- the polymerization of the resin in matrix in order to obtain a filling piece in composite material comprising a 3D woven fibrous preform,

- l’application d’une colle contenant au moins un solvant à la surface de la portion évidée,- the application of an adhesive containing at least one solvent to the surface of the hollowed out portion,

- le placement de la pièce de comblement dans la portion évidée, ladite pièce de comblement occupant le volume défini par la portion évidée.- the placement of the filler piece in the hollowed-out portion, said filler piece occupying the volume defined by the hollowed-out portion.

Cette méthode de réparation permet de réaliser l’étape de placement de la pièce de comblement dans la pièce à réparer sans outillage complexe. Ainsi, le site de réparation peut s’affranchir du matériel nécessaire à une imprégnation, à une densification ou à une polymérisation pour réparer une pièce. Notamment, le site de réparation n’a pas besoin d’être équipé du matériel nécessaire à la réalisation de moulage par transfert dit RTM ("Resin Transfert Moulding"). En effet, la fabrication de la pièce de comblement peut être réalisée sur un autre site. En outre, la pièce de comblement étant solide, celle-ci peut facilement être rectifiée ou usinée si ses dimensions doivent être corrigées avant placement dans la portion évidée.This repair method makes it possible to carry out the step of placing the filler piece in the part to be repaired without complex tools. Thus, the repair site can dispense with the equipment necessary for impregnation, densification or polymerization to repair a part. In particular, the repair site does not need to be equipped with the equipment necessary for carrying out transfer molding called RTM ("Resin Transfer Moulding"). Indeed, the manufacture of the filling piece can be carried out on another site. In addition, since the filler piece is solid, it can easily be ground or machined if its dimensions need to be corrected before placement in the hollowed-out portion.

Selon une caractéristique particulière de l’invention, la pièce en matériau composite est une aube de turbomachine.According to a particular characteristic of the invention, the composite material part is a turbine engine blade.

Selon une autre caractéristique particulière de l’invention, l’étape de placement de la pièce de comblement comprend une mise sous vide de la jonction entre la pièce de comblement et la portion évidée jusqu’à l’élimination du solvant de la colle.According to another particular characteristic of the invention, the step of placing the filler piece comprises vacuuming the junction between the filler piece and the recessed portion until the removal of the solvent from the glue.

Selon une autre caractéristique particulière de l’invention, l’étape de placement de la pièce de comblement comprend une mise sous pression de la pièce de comblement et de la portion évidée.According to another particular characteristic of the invention, the step of placing the filler piece comprises pressurizing the filler piece and the recessed portion.

Selon une autre caractéristique particulière de l’invention, la mise sous pression s’effectue par autoclave.According to another particular characteristic of the invention, the pressurization is carried out by autoclave.

Selon une autre caractéristique particulière de l’invention, la mise sous pression s’effectue à l’aide d’un outillage comprenant au moins une surface chauffante mise en contact avec la pièce de comblement.According to another particular characteristic of the invention, the pressurization is carried out using a tool comprising at least one heating surface brought into contact with the filling piece.

Selon une autre caractéristique particulière de l’invention, le procédé comprend en outre une étape de polymérisation de la colle à une température supérieure à 120°C.According to another particular characteristic of the invention, the method further comprises a step of polymerization of the glue at a temperature above 120°C.

Selon une autre caractéristique particulière de l’invention, le procédé comprend en outre une étape de polymérisation de la colle à température ambiante.According to another particular characteristic of the invention, the method further comprises a step of polymerization of the glue at ambient temperature.

La illustre schématiquement une armure de tissage tridimensionnel de type interlock. The schematically illustrates a three-dimensional interlock-type weave weave.

La est une vue schématique d’une aube de turbomachine comprenant une zone endommagée. The is a schematic view of a turbine engine blade including a damaged area.

La est une vue en coupe partielle de la zone endommagée de l’aube illustrée sur la selon le plan de coupe II. The is a partial cross-sectional view of the damaged area of the blade shown in the according to section plan II.

La est une vue en coupe partielle de la portion évidée selon la méthode « scarf » de l’aube illustrée sur la . The is a partial cross-sectional view of the scooped portion of the vane illustrated in the .

La est une vue en coupe partielle de la portion évidée selon la méthode « scarf » de l’aube illustrée sur la et de la pièce de comblement associée. The is a partial cross-sectional view of the scooped portion of the vane illustrated in the and the associated filler piece.

La est une vue en coupe partielle de la portion évidée selon la méthode « step » de l’aube illustrée sur la . The is a partial cross-sectional view of the portion hollowed out using the "step" method of the vane illustrated on the .

La est une vue en coupe partielle de la portion évidée selon la méthode « step » de l’aube illustrée sur la et de la pièce de comblement associée. The is a partial cross-sectional view of the portion hollowed out using the "step" method of the vane illustrated on the and the associated filler piece.

La est vue en coupe partielle de la portion évidée selon la méthode « step » de l’aube illustrée sur la , comblée par la pièce de comblement associée et disposée dans un outillage de mise sous pression selon l’invention. The is seen in partial cross-section of the portion hollowed out according to the “step” method of the blade illustrated on the , filled with the associated filling piece and placed in a pressurizing tool according to the invention.

Claims (8)

Procédé de réparation d’une pièce en matériau composite (1) comprenant un renfort fibreux présentant un tissage tridimensionnel entre une pluralité de fils de chaîne et une pluralité de fils de trame, le dit renfort fibreux étant densifié par une matrice, caractérisé en ce qu’il comprend :
- l’identification d’au moins une zone endommagée (20) à la surface (11) de la pièce,
- la réalisation d’une portion évidée (30 ; 40) par retrait du matériau composite au niveau de la zone endommagée (20),
- le tissage tridimensionnel d’une préforme fibreuse de comblement ayant une forme correspondant à la forme de la portion évidée (30 ; 40),
- l’imprégnation de la préforme fibreuse de la pièce de comblement avec une résine précurseur d’une matrice,
- la polymérisation de la résine en matrice afin d’obtenir une pièce de comblement en matériau composite (3 ; 4) comprenant une préforme fibreuse tissée 3D,
- l’application d’une colle (130 ; 140) contenant au moins un solvant à la surface de la portion évidée (31 ; 41),
- le placement de la pièce de comblement (3 ; 4) dans la portion évidée, ladite pièce de comblement occupant le volume défini par la portion évidée (30 ; 40).Method for repairing a part made of composite material (1) comprising a fibrous reinforcement having a three-dimensional weave between a plurality of warp threads and a plurality of weft threads, the said fibrous reinforcement being densified by a matrix, characterized in that 'He understands :
- the identification of at least one damaged zone (20) on the surface (11) of the part,
- the production of a recessed portion (30; 40) by removing the composite material at the level of the damaged zone (20),
- the three-dimensional weaving of a fibrous filler preform having a shape corresponding to the shape of the hollowed out portion (30; 40),
- the impregnation of the fibrous preform of the filler piece with a resin precursor of a matrix,
- the polymerization of the matrix resin in order to obtain a composite material filler piece (3; 4) comprising a 3D woven fiber preform,
- the application of an adhesive (130; 140) containing at least one solvent to the surface of the recessed portion (31; 41),
- the placement of the filler piece (3; 4) in the recessed portion, said filler piece occupying the volume defined by the recessed portion (30; 40). Procédé selon la revendication 1, dans lequel la pièce en matériau composite (1) est une aube de turbomachine.Method according to claim 1, in which the composite material part (1) is a turbine engine blade. Procédé selon la revendication 1 ou 2, dans lequel l’étape de placement de la pièce de comblement (3 ; 4) comprend une mise sous vide de la jonction entre la pièce de comblement (3 ; 4) et la portion évidée (30 ; 40) jusqu’à l’élimination du solvant de la colle (130 ; 140).A method according to claim 1 or 2, wherein the step of placing the filler piece (3; 4) comprises vacuuming the junction between the filler piece (3; 4) and the recessed portion (30; 40) until the removal of the solvent from the glue (130; 140). Procédé selon l’une quelconque des revendications 1 à 3, dans lequel l’étape de placement de la pièce de comblement (3 ; 4) comprend une mise sous pression de la pièce de comblement (3 ; 4) et de la portion évidée (30 ; 40).Method according to any one of claims 1 to 3, in which the step of placing the filler piece (3; 4) comprises pressurizing the filler piece (3; 4) and the recessed portion ( 30; 40). Procédé selon la revendication 4, dans lequel la mise sous pression s’effectue par autoclave.Process according to Claim 4, in which the pressurization is carried out by autoclave. Procédé selon la revendication 4, dans lequel la mise sous pression s’effectue à l’aide d’un outillage (5) comprenant au moins une surface chauffante (51) mise en contact avec la pièce de comblement (3 ; 4).Method according to claim 4, in which the pressurization is carried out using a tool (5) comprising at least one heating surface (51) placed in contact with the filling piece (3; 4). Procédé selon l’une quelconque des revendications 1 à 6, comprenant en outre une étape de polymérisation de la colle (130 ; 140) à une température supérieure à 120°C.Method according to any one of claims 1 to 6, further comprising a step of polymerizing the adhesive (130; 140) at a temperature above 120°C. Procédé selon l’une quelconque des revendications 1 à 6, comprenant en outre une étape de polymérisation de la colle (130 ; 140) à température ambiante.Method according to any one of claims 1 to 6, further comprising a step of polymerizing the adhesive (130; 140) at room temperature.
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Citations (8)

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Publication number Priority date Publication date Assignee Title
US5882756A (en) * 1995-12-22 1999-03-16 The Boeing Company Composite patches having Z-pin reinforcement
US20030196305A1 (en) * 2002-04-19 2003-10-23 General Electric Company Method for repairing articles of ceramic composites
US20070095457A1 (en) 2005-11-02 2007-05-03 The Boeing Company Fast line maintenance repair method and system for composite structures
US20100144227A1 (en) 2005-06-24 2010-06-10 Snecma Reinforcing fibrous structure for a composite material and a part containing said structure
CH701247A1 (en) * 2009-06-11 2010-12-15 Joerg-Ulrich Zowalla Template and template set for use in the repair of composite materials.
US20120061006A1 (en) * 2009-02-23 2012-03-15 Hans Marquardt Method for at least partially reworking or replacing a reinforcement element of a fibre composite structure and associated connecting device
FR3092787A1 (en) * 2019-02-18 2020-08-21 Safran Aircraft Engines Repair or resumption of manufacture of a composite material part with three-dimensional woven fiber reinforcement
WO2020178500A1 (en) 2019-03-01 2020-09-10 Safran Repairing or resuming production of a component made of composite material

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5882756A (en) * 1995-12-22 1999-03-16 The Boeing Company Composite patches having Z-pin reinforcement
US20030196305A1 (en) * 2002-04-19 2003-10-23 General Electric Company Method for repairing articles of ceramic composites
US20100144227A1 (en) 2005-06-24 2010-06-10 Snecma Reinforcing fibrous structure for a composite material and a part containing said structure
US20070095457A1 (en) 2005-11-02 2007-05-03 The Boeing Company Fast line maintenance repair method and system for composite structures
US20120061006A1 (en) * 2009-02-23 2012-03-15 Hans Marquardt Method for at least partially reworking or replacing a reinforcement element of a fibre composite structure and associated connecting device
CH701247A1 (en) * 2009-06-11 2010-12-15 Joerg-Ulrich Zowalla Template and template set for use in the repair of composite materials.
FR3092787A1 (en) * 2019-02-18 2020-08-21 Safran Aircraft Engines Repair or resumption of manufacture of a composite material part with three-dimensional woven fiber reinforcement
WO2020178500A1 (en) 2019-03-01 2020-09-10 Safran Repairing or resuming production of a component made of composite material

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