EP4392239A1 - Patch de préforme et méthode de renforcement ultérieur d'un composant composite fibreux - Google Patents

Patch de préforme et méthode de renforcement ultérieur d'un composant composite fibreux

Info

Publication number
EP4392239A1
EP4392239A1 EP22769109.4A EP22769109A EP4392239A1 EP 4392239 A1 EP4392239 A1 EP 4392239A1 EP 22769109 A EP22769109 A EP 22769109A EP 4392239 A1 EP4392239 A1 EP 4392239A1
Authority
EP
European Patent Office
Prior art keywords
layer
fiber
matrix material
patch
preform
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.)
Pending
Application number
EP22769109.4A
Other languages
German (de)
English (en)
Inventor
Dominik Dierkes
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Faserverbund Innovations UG (haftungsbeschrankt)
Original Assignee
Faserverbund Innovations UG (haftungsbeschrankt)
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from DE102021122791.7A external-priority patent/DE102021122791A1/de
Application filed by Faserverbund Innovations UG (haftungsbeschrankt) filed Critical Faserverbund Innovations UG (haftungsbeschrankt)
Publication of EP4392239A1 publication Critical patent/EP4392239A1/fr
Pending legal-status Critical Current

Links

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
    • B29C70/28—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
    • B29C70/546—Measures for feeding or distributing the matrix material in the reinforcing 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
    • 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
    • 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
    • B29C70/544—Details of vacuum bags, e.g. materials or shape
    • 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
    • B29C73/10—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 patches sealing on the surface of the article
    • 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

Definitions

  • Custom fabric plies are stacked onto a peel ply into a patch, the patch is placed in a preform patch, a sealed enclosure is then created around the repair surface, and a matrix material is infused into the repair.
  • a preform patch can be designed in order to distribute the matrix material reliably and without blistering on the surface of the repair site. In particular, it is not specified where and how the vacuum is applied during the infusion process.
  • the object of the present invention is to create a preform patch that is easy to produce, its special structure allows the matrix material to flow reliably through the preform patch and is easy to process, as well as a corresponding method for reinforcing a fiber composite component .
  • the object is achieved for a generic method by using a preform patch in which at least one layer of a tear-off fabric is arranged as the first layer on its side facing the surface of the fiber composite component, at least one layer of a flow aid is arranged thereover and at least one layer of a vacuum film is arranged thereover where the at least one layer of the flow aid is arranged in a distribution space for distributing the matrix material over a fiber layer of a fiber material, the distribution space is delimited by the vacuum film on the side facing away from the fiber composite component, the preform patch has a gas-permeable but matrix material-impermeable membrane and a Having layer of a spacer fabric, wherein the space filled by the spacer fabric forms a suction space which is sealed against the distribution space matrix material-tight, the preform patch is placed on a fiber layer of a fiber material, which previously placed on the fiber composite component was placed, the preform patch is vacuum-tightly connected to the fiber composite component and matrix material is introduced into the preform patch until the fiber layer
  • a preform patch can in particular have several layers of a flow aid.
  • the flow aid can be designed in multiple layers, in particular where a greater flow rate of the matrix material is desired.
  • the multiple layers can therefore also only be implemented in certain areas.
  • Multi-layer flow aids can also form pockets between them, which have a larger conveying cross section than a single-layer flow aid.
  • the material layer with the membrane and the spacer fabric is arranged at least partially overlapping the flow aid in at least one edge area of the flow aid. Due to the overlap, the matrix material is brought up to the membrane. If the flow aid does not completely overlap the layer of material, a kind of braking zone results for the matrix material, in which the flow front of the matrix material runs out. If the braking zones are formed outside or in the edge area of the areas in which the fiber layer of a fiber material is located, the fiber layer is completely reached and wetted by the matrix material.
  • Such a reinforcement or repair attempt would be regarded as having failed, with the result that the areas of the fiber layer of a fiber material saturated with the matrix material would also have to be removed from the fiber composite component and a new attempt would be required to reinforce or repair the fiber composite component.
  • the layer of flow aid arranged in different planes forms a hydrostatic column with the matrix material collected therein, in which the matrix material can flow faster through the flow aid due to gravity and the weight of the matrix material flowing on.
  • the arranged in the different plane position of the flow aid can in particular as a Web be formed, which protrudes from the rest of the preform patch. With the same dimensioning of the channel sizes, the matrix material can thus reach the areas of the preform patch that are further away from the inlet connection more quickly than is possible via the areas in which the matrix material at least partially seeps away into the fiber layer. Due to the flow aid arranged in a different plane, the matrix material can therefore reach the areas further away from the inlet connection more quickly, before the matrix material begins to harden.
  • the flow aid arranged in a different plane is also covered on the outside by at least one vacuum film, so that no loss of matrix material can occur there and the vacuum present in the suction chamber reaches into the flow aid located in the different plane.
  • the flow aid located in the different plane ends at one end in the plane of the flow aid layer lying on the fiber layer of a fiber material, matrix material transported in the different plane can still seep into the layer of flow aid lying on the fiber layer and spread redistribute there.
  • matrix material transported in the different plane can still seep into the layer of flow aid lying on the fiber layer and spread redistribute there.
  • more or less matrix material gets into the area of the flow aid above the fiber layer.
  • the flow aids in the mouth area can be designed without contact, only abutting one another or also more or less overlapping.
  • the layer of flow aid arranged in a different plane can be located in a tab that is movable relative to the rest of the preform patch.
  • the tab Before use, the tab can lie flat on the rest of the preform patch to save space and fold away to the side when it is filled with matrix material.
  • the flow aid arranged in the different planes then has enough space to bulge and thereby take up a larger volume of matrix material. In this way, the layer of flow aid arranged in a different plane forms a separate line for conveying the matrix material.
  • the preform patch only partially has a gas-permeable membrane that is impermeable to matrix material and a layer of spacer fabric, and the preform patch is aligned on the fiber composite component in such a way that the suction space formed by the membrane and the spacer fabric contains the matrix material in a direction across the horizontal len sucks through the distributor space.
  • the transverse distribution of the matrix material in the preform patch is supported by the suction of the gas in the distribution chamber through the membrane.
  • the lateral distribution acts in particular in the area that is not covered by the membrane.
  • Fig. 2 a view of a wind turbine
  • gravity can also be used to distribute the matrix material 6 particularly quickly over the length and surface of the preform patch 2 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

L'invention concerne l'utilisation d'un patch de préforme (2) ayant, sur son côté faisant face à la surface du composant composite fibreux (8), au moins une couche d'un tissu d'arrachage (10) en tant que première couche, au-dessus de celle-ci au moins une couche d'un fluidifiant (12), et au-dessus de celle-ci au moins une couche d'un film sous vide (14), la ou les couches du fluidifiant (12) étant disposées dans un espace de distribution (16) pour la distribution du matériau matriciel (6) sur la couche de fibres (4a) d'un matériau fibreux délimité à l'extérieur par le film sous vide (14), et le patch de préforme (2) présente une membrane perméable aux gaz mais imperméable au matériau matriciel (18) et une couche d'un tissu d'espacement (20), l'espace rempli par le tissu d'espacement (20) formant un espace d'aspiration (22) scellé de manière étanche au matériau matriciel par rapport à l'espace de distribution (16).
EP22769109.4A 2021-08-23 2022-08-22 Patch de préforme et méthode de renforcement ultérieur d'un composant composite fibreux Pending EP4392239A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE102021121793 2021-08-23
DE102021122535 2021-08-31
DE102021122791.7A DE102021122791A1 (de) 2021-08-23 2021-09-02 Preform-Patch und Verfahren zur nachträglichen Verstärkung eines Faserverbundbauteils
PCT/EP2022/073334 WO2023025725A1 (fr) 2021-08-23 2022-08-22 Patch de préforme et méthode de renforcement ultérieur d'un composant composite fibreux

Publications (1)

Publication Number Publication Date
EP4392239A1 true EP4392239A1 (fr) 2024-07-03

Family

ID=83283212

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22769109.4A Pending EP4392239A1 (fr) 2021-08-23 2022-08-22 Patch de préforme et méthode de renforcement ultérieur d'un composant composite fibreux

Country Status (2)

Country Link
EP (1) EP4392239A1 (fr)
WO (1) WO2023025725A1 (fr)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5123985A (en) * 1986-09-02 1992-06-23 Patricia Evans Vacuum bagging apparatus and method including a thermoplastic elastomer film vacuum bag
PL2474410T3 (pl) 2011-01-05 2016-09-30 Sposób wytwarzania wstępnie formowanej łaty
GB2531600A (en) * 2014-10-24 2016-04-27 Short Brothers Plc Apparatus and methods for manufacturing and repairing fibre-reinforced composite materials
CN106142593B (zh) * 2015-04-10 2019-11-26 科思创德国股份有限公司 制造纤维增强塑料制品的方法
CA3033270C (fr) * 2016-08-09 2020-12-08 Mitsubishi Heavy Industries, Ltd. Procede de production d'articles moules en resine renforcee de fibres
EP3299154A1 (fr) * 2016-09-27 2018-03-28 Hexcel Reinforcements SAS Dispositif de production d'une partie composite
DE102018111306B4 (de) 2018-05-11 2022-10-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zum Applizieren eines Werkstoffes auf ein Faserverbundbauteil
DE102019121357A1 (de) 2019-08-07 2021-02-11 Airbus Defence and Space GmbH Verfahren zum Reparieren eines Faserverbundbauteils

Also Published As

Publication number Publication date
WO2023025725A1 (fr) 2023-03-02

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