WO2012149939A2 - Procédé de préparation d'un stratifié composite - Google Patents

Procédé de préparation d'un stratifié composite Download PDF

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Publication number
WO2012149939A2
WO2012149939A2 PCT/DK2012/050147 DK2012050147W WO2012149939A2 WO 2012149939 A2 WO2012149939 A2 WO 2012149939A2 DK 2012050147 W DK2012050147 W DK 2012050147W WO 2012149939 A2 WO2012149939 A2 WO 2012149939A2
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WO
WIPO (PCT)
Prior art keywords
resin
layer
layers
resin film
viscosity
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.)
Ceased
Application number
PCT/DK2012/050147
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English (en)
Other versions
WO2012149939A3 (fr
Inventor
Jed Richter
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.)
Vestas Wind Systems AS
Original Assignee
Vestas Wind Systems AS
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
Application filed by Vestas Wind Systems AS filed Critical Vestas Wind Systems AS
Publication of WO2012149939A2 publication Critical patent/WO2012149939A2/fr
Publication of WO2012149939A3 publication Critical patent/WO2012149939A3/fr
Anticipated expiration legal-status Critical
Ceased 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
    • B29C70/30—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
    • B29C70/342—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 using isostatic pressure
    • 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
    • B29C70/443—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 and impregnating by vacuum or injection
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B29L2031/082—Blades, e.g. for helicopters
    • B29L2031/085—Wind turbine blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product

Definitions

  • the present invention relates to a method of preparing a composite laminate composed of different types of fiber reinforced materials.
  • the invention furthermore relates to a composite laminate and more specifically to wind turbine blade prepared according to such method.
  • one region of the composite component may desirably be constructed from pre-impregnated material whereas an adjacent region may desirably be constructed from e.g. biaxial fabrics where significant cost benefits can be derived from liquid infusion processes of dry fabrics.
  • the use of such different materials in the same composite component may impose several difficulties to the finished component such as e.g. potential adhesion problems between the different materials.
  • the use of differing materials may cause manufacturing difficulties due to potentially likewise differing process parameters to be observed.
  • the resins used for the different material formats may require differing
  • resins in pre-impregnated materials are typically almost solid at room temperature but liquefy at elevated temperatures typically in the range of 60-120°C.
  • Some resins suitable for infusion or injection processes are considered 'liquid' at ambient temperatures, whereas others require a temperature elevation to 60-100°C to reduce their viscosity sufficiently to enable infusion.
  • the different resins are prone to result in unpredictable migration of the resins between the different materials during the manufacture, and thereby correspondingly unpredictable distribution and amount of the different resins the finished composite.
  • the region in which the different types of resins meet and thereby the component as such may suffer from unpredictable material properties and even from void content due to the potentially incomplete impregnation in places.
  • the consequences hereof may be poor structural performance and premature failure.
  • semi-pregs or PIP's where the reinforcing material comprises the full amount of resin but is not fully impregnated so that dry or partially dry regions are present
  • the reinforcing material may be preferentially wet-out by the infusion resin, leading to the semi-preg resin layer remaining a discrete resin-rich region which is undesirable in structural performance terms.
  • a further object of embodiments of the invention is to provide a method of preparing a composite laminate which allows for a wider choice of combinations of applicable resin materials without or with reduced risk of insufficient or uncontrolled resin distribution in the finished composite component caused by the different materials used.
  • said layers comprising a first layer being at least partly pre-impregnated by a resin having a first viscosity and a second layer; - providing a resin of a second viscosity to at least partly impregnate said second layer;
  • the resin flow across the material interface between the first and second layers may be controlled, in that the resin film will act as a barrier reducing or even preventing migration of the structural matrix material (i.e. the resin) between the layers of different material during the preparation of the laminate.
  • This effect may be mainly due to the low-flow properties of the resin film relative to one or both of the resins of the
  • the resin may be provided to the second layer by e.g . injection, or infusion, or a combination hereof, i.e. by resin transfer moulding (RTM) .
  • RTM resin transfer moulding
  • the low-flow properties of the resin film is obtained by choosing the resin film such that its viscosity /v ff/m at the temperature of the resin impregnation is at least comparable to or higher than the most liquid of the two resins of the layers being combined, i.e. /v ff/m ⁇ minfo ⁇ 2 ).
  • the first layer of fiber reinforced material may comprise a prepreg and/or semi-preg .
  • Prepreg materials are fiber reinforced materials which are completely impregnated comprising the full and necessary amount of resin.
  • Semi-pregs likewise comprise the full and necessary amount of resin, but is not completely impregnated in the sense that dry areas may exist. In this way the semi-preg may impregnate itself at the appropriate temperature and consolidation pressure.
  • a semi-preg may comprise the full amount of resin placed in between the layers of the semi-preg leaving the outer surfaces dry to touch, with the advantage that the material becomes easier to handle and store.
  • the resin film may advantageously act to reduce or even prevent the resin from the pre-impregnated layer to migrate into the second layer of dry fibres first, otherwise leading to areas of void in the pre- impregnated layer.
  • the resin film may advantageously act to reduce or even prevent the infusion resin to migrate into the semi-preg causing resin rich areas.
  • the resin film may be fully or at least partly uncured, i.e. uncured in some parts or comprises uncured resin material or combinations hereof. Further, the resin film may be at an intermediate stage of curing. Hereby may be obtained that the film may stay between the layers and is co-cured with the laminate to become an integral part of the laminate without or with only minimal reduction of the structural properties of the finished laminate.
  • the fiber reinforced material may comprise fabrics of e.g. woven, non-woven, stitched, knitted, filted or otherwise fibrous materials.
  • the first and second layers may be placed on top of each other, next to each other, in an overlapping fashion, or placed to form a joint such as e.g. a stepped joint or a scarf joint or any combinations hereof.
  • the stacking order of the materials above and below the resin film is of no importance. I.e. the pre- impregnated layers may be placed either above or below the resin film and the dry fibres to be impregnated.
  • the resin film may be placed across a part of or across the entire the joint surface or interface between the layers of fiber reinforced material. Further, the resin film may be placed to extend a certain distance on one or both sides of the interface between the dry fibres and the pre-impregnated material such as e.g. between 20-50mm to deal with any transverse flow, such as in the range of 30-40 mm.
  • the resin migration may be controlled during the entire resin impregnation of the dry layers or during a longer period hereof in
  • This may e.g. be achieved by using an uncured resin film of e.g. an epoxy, a vinyl-ester or a DCPD, which exhibits highly-controlled flow characteristics in the temperature regions at which the resin migration can occur.
  • the resin film may further have curing characteristics that allow the material to cure at a similar temperature to the prepreg or liquid infusion resin (whichever is the higher) - so the resin film then becomes an integral part of the laminate and remains essentially at or close to the interface of the two other structural materials.
  • the resin film may be chosen such as to have a curing temperature in between or around the curing temperature of either of the surrounding systems, optionally closer to the higher curing temperature, thereby obtaining that a chemical bonds may be formed successfully with both mating materials, which in general may be greatly aided by the resin still being liquid.
  • a high toughness interface with increased resistance to shear and peel forces due to a combination of chemical and mechanical bonding of the resin film to the neighbouring materials.
  • Good chemical bonding and adhesion may be ensured by choosing a resin film of compatible chemistry with both of the mating resin systems. This may be obtained by using resins of the same chemistry group - i.e. epoxy film for epoxy mating systems, vinyl-ester film for vinyl- ester mating systems, etc.
  • different resin types of each of the different materials to be combined may be mixed and matched.
  • a vinyl-ester film may be used to enable a high performance epoxy prepreg to be mated with a low-cost polyester infusion resin.
  • the resin film may be used to enable a stronger bond between the mating parts of the laminate of different resin types.
  • resins of the different materials to be combined whereby may be chosen for instance resins of lower cost, of easier handling, of more appropriate curing temperatures etc.
  • a resin film in accordance with embodiments of the invention may be advantageous in providing structural enhancement of the interface area between the layers to be combined. This effect may especially be obtained by the use of resin films of high toughness (for example adhesive films with a high content of rubber tougheners) known to act as a barrier to crack propagation in the more brittle structural resins at the interfacial region thereby providing a high performance bond.
  • resin films of high toughness for example adhesive films with a high content of rubber tougheners
  • the resin film may optionally in whole or in part be placed on a carrier scrim thereby making it easier to handle prior to and during the preparation of the laminate.
  • the resin film may be a toughened adhesive film such as e.g. AF163-3 supplied by 3M, Redux 312 supplied by Hexcel, and MTA240 supplied by Advanced Composites Group. These films typically have a relatively high viscosity and limited flow at higher temperatures.
  • the thickness of the resin film may depend on its tendency to flow prior to the infusion or injection, and may be of approximately 0.1- 1.0 mm, such as in the range of 0.3-0.6mm.
  • the resin film may further be perforated or comprise holes in various sizes and patterns. Such perforations may be advantageous in increasing the bond of the resin film to the adjacent materials while the film still acts to reduce the resin migration across the interface.
  • a resin film with a resistance to flow at temperatures between 40-80°C may be practical for application in a manufacturing process with curing temperatures of the mating resin systems between 60-120°C such as between 80-100°C.
  • a resin film such as an adhesive film of a viscosity approximately 1 order of magnitude higher than the prepreg resin would be usable.
  • An appropriate resin film could for example be a resin film such as the epoxy adhesive film of MTA240 manufactured by Advanced Composites Group. This will ultimately co-cure with the prepreg at a final cure temperature of around 120°C.
  • the method described in the preceding further comprises increasing the temperature of the composite laminate to or above the liquefying temperature of the resin film prior to curing the laminate.
  • the bonding of the resin film to the neighboring materials and thereby into the final laminate may be increased.
  • an increase of the temperature to or above the liquefying temperature of the resin film may be performed without or with only minimal effect on the barrier-acting properties of the resin film, as the viscosity of the resin film is still higher than the most liquid resin at the time when the second layer is impregnated.
  • the method further comprises increasing the temperature of the first and second layer prior to providing the resin to the second layer.
  • the resin transfer into the second layers of material may be enhanced.
  • the viscosity of the resin film when providing said resin to said second layer, is between the values of the viscosities of the resins of the first and second layers.
  • the resin film may act as barrier for the resin migration across the film while allowing for a controlled and moderate impregnation of the resin film itself into the surrounding fiber reinforced material. This may further provide a high toughness interface with a combination of chemical and mechanical bonding to resist shear and peel forces.
  • the resin impregnating the second layer is provided by resin infusion and/or resin injection.
  • the resin film comprises a thermosetting resin which may be advantageous as the resin film thereby is compatible to the resin used for the resin transfer.
  • the resin film may be integrated fully into the finished laminate and may increase the interfacial properties such as strength and resistance to wear.
  • the resin film may comprise a thermoplastic resin of a type allowing to bond to the adjacent resins.
  • a further aspect of the invention relates to a composite laminate prepared by a process according to any of the preceding and comprising providing layers of fiber reinforced material, where the layers comprise a first layer being at least partly pre-impregnated by a resin having a first viscosity, and a second layer. Further, a resin of a second viscosity is provided to at least partly impregnate the second layer, and an at least partly uncured resin film is provided between the first and second layers.
  • the invention further relates to a wind turbine blade component comprising a composite laminate prepared by a method according to any of the preceding.
  • the wind turbine blade comprising a root part, a tip part opposite said root part, and an intermediate part between said root part and said tip part, and wherein the intermediate part comprises said first layer of an at least partly pre- impregnated fiber reinforced material and the root part comprises said second layer of fiber reinforced material.
  • the resin film is provided at the interface between the root part of dry fibres to be resin impregnated by resin transfer moulding and the intermediate part comprising pre-impregnated layers such as prepregs or semi-pregs.
  • the proposed resin film may be obtained a better processing control in that the resin amounts in the different parts of the component may be more precisely controlled. Further may be obtained a structural enhancement of the interface between the dry fiber lay-up in the root end to be impregnated by resin transfer moulding and the pre- impregnated layers or slabs in the tip end of the blade.
  • the resin film further enables the use of semipregs which may be advantageous to use in that they generally yield better quality laminates and handling characteristics when compared to fully wet-out prepregs.
  • Fig. 1 shows a sketch of different materials laid-up on a mould in a cross-sectional view
  • Fig. 2 is a sketch of the positioning of a barrier film according to an embodiment of the invention and in a cross-sectional view
  • Fig. 3 is in a cross-sectional view of a part of a component for a wind turbine under manufacture according to an embodiment of the invention. Detailed description of the drawings
  • Figure 1 illustrates in a cross sectional view the manufacture of a hybrid composite component 100 according to prior art, where the fiber reinforcement 101, 102 is laid up on a mould surface 103 and covered with a vacuum bag or foil 104.
  • the laminate 100 comprises a prepreg material 101 and dry fabrics 102 which are to be impregnated by resin infusion or injection .
  • the resin from the prepreg materials 101 will liquefy prior to the resin infusion process. In this case, the resin will migrate unpredictably into the dry materials 102 from the prepreg material 101 as illustrated by the arrows 105.
  • the liquid resins may or may not infuse the region from which the prepreg resin has migrated . Further, the region in which the injected resin and prepreg resin meet can suffer from unpredictable void content and fibre volume fractions leading to poor structural performance and premature failure.
  • a resin film 200 is here provided between the dry fibrous material 102 and the already to some extent impregnated fiber reinforced material 101.
  • the material of the resin film 200 is chosen such as to have a viscosity /v ff/m higher than the lowest viscosity of either of the resins of the materials which it separates, ( ⁇ ⁇ 2 ) i.e. of either the resin injected or infused into the dry fibrous material 102, ⁇ 2 or of the pre-impregnated material 101, /Vi .
  • the resin film is chosen such that /v ff/m ⁇ minfo ⁇ 2 ). In this way the resin film will act as a barrier preventing or reducing the migration of resin between the different types of material 101, 102 of the composite component 100.
  • Figure 3 illustrates the lay-up of a part of a wind turbine blade as seen in a cross-sectional view A-A along the length of the wind turbine blade 400 as indicated in figure 4.
  • the wind turbine blade comprises a root part 401, a tip part 402 opposite the root part, and an intermediate part 403 between the root part and the tip part.
  • the root part 401 comprises layers of dry fiber material 102 to be impregnated by resin infusion and optionally a pre- cured 'spear' or core 301 into which the bushings for the blade connection may be inserted or embedded.
  • the intermediate part 403 comprises layers of pre-impregnated material 101 such as prepreg slabs 302, semi-preg layers 303 and a spar 304 of carbon material extending along the length of the wind turbine blade.
  • pre-impregnated layers and the dry fibre layers are separated by a resin film 200.
  • the resin film here acts as a low-flow barrier reducing or preventing the resin flow from the pre-impregnated materials 302 into the dry fibres 102 or the other way of infused resin into the semi-preg 303 during the resin transfer.
  • the use of the resin film 102 in this way provides a better processing control and control of the fiber-to-resin ratio of the different laminate parts of the blade along with a structural enhancement of the interface between the dry fiber lay-up in the root end and the pre- impregnated layers and carbon slabs further out in the blade.
  • the application of the resin film enables the use of more semi-pregs instead of prepregs, thereby reducing the material count and improving the deposition rate. This may further be advantageous as the handling characteristics of semi-pregs are generally higher than of prepregs where the handling in general involves touching the resin and due to the general tackiness of the prepreg surfaces.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Reinforced Plastic Materials (AREA)
  • Moulding By Coating Moulds (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Abstract

Cette invention concerne un procédé de préparation d'un stratifié composite hybride fait de couches d'un matériau composite renforcé de fibres, en résine de différentes viscosités. Le procédé consiste à produire dans un moule une première couche d'un matériau pré-imprégné et une seconde couche. Une couche de résine non durcie est placée entre la première et la seconde couche. Une résine d'une seconde viscosité est utilisée pour imprégner la seconde couche. La viscosité de la couche de résine est égale ou supérieure à la viscosité la plus faible de la première ou de la seconde résine, ce qui permet de réguler la migration de la résine entre les couches fibreuses pendant l'imprégnation de la résine. L'invention concerne en outre un stratifié composite et un constituant de pale d'éolienne préparés par un procédé de l'invention. La pale d'éolienne peut comprendre une partie de base, une partie de pointe, et une partie intermédiaire située entre celles-ci, la partie intermédiaire comprenant une première couche d'un matériau pré-imprégné renforcé de fibres, et la partie de base une seconde couche d'un matériau renforcé de fibres.
PCT/DK2012/050147 2011-05-04 2012-05-03 Procédé de préparation d'un stratifié composite Ceased WO2012149939A2 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DKPA201170218 2011-05-04
DKPA201170218 2011-05-04
US201161482626P 2011-05-05 2011-05-05
US61/482,626 2011-05-05

Publications (2)

Publication Number Publication Date
WO2012149939A2 true WO2012149939A2 (fr) 2012-11-08
WO2012149939A3 WO2012149939A3 (fr) 2013-02-14

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Cited By (8)

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EP2784106A1 (fr) * 2013-03-28 2014-10-01 Siemens Aktiengesellschaft Structure composite
ITMI20131364A1 (it) * 2013-08-08 2015-02-09 Sparco S P A Metodo per produzione di un prodotto composito che prevede una matrice polimerica presentante fibre di rinforzo, e prodotto ottenuto con tale metodo
WO2015114098A1 (fr) 2014-01-31 2015-08-06 Lm Wp Patent Holding A/S Partie de pale d'éolienne fabriquée en deux étapes
WO2015114100A1 (fr) * 2014-01-31 2015-08-06 Lm Wp Patent Holding A/S Pale d'éolienne à transition fibreuse améliorée
WO2016063065A1 (fr) * 2014-10-24 2016-04-28 Short Brothers Plc Appareil et procédés de fabrication et de réparation de matériaux composites renforcés par fibres
DE102016219137A1 (de) * 2016-10-04 2018-04-05 Bayerische Motoren Werke Aktiengesellschaft Verfahren zur Herstellung eines Faserverbundbauteils mit Überlappstoß oder lokaler Verstärkung
CN109916526A (zh) * 2019-03-11 2019-06-21 西北工业大学 一种用于涡轮叶片上ito薄膜热电偶电信号引出的背引线结构及制备方法
EP4454852A1 (fr) * 2023-04-28 2024-10-30 Siemens Gamesa Renewable Energy A/S Table d'emballage pour la fabrication d'un adaptateur d'assemblage utilisé dans un procédé d'assemblage

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Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2784106A1 (fr) * 2013-03-28 2014-10-01 Siemens Aktiengesellschaft Structure composite
US10328676B2 (en) 2013-03-28 2019-06-25 Siemens Gamesa Renewable Energy A/S Composite structure
ITMI20131364A1 (it) * 2013-08-08 2015-02-09 Sparco S P A Metodo per produzione di un prodotto composito che prevede una matrice polimerica presentante fibre di rinforzo, e prodotto ottenuto con tale metodo
US10330074B2 (en) 2014-01-31 2019-06-25 Lm Wp Patent Holding A/S Wind turbine blade with improved fibre transition
WO2015114098A1 (fr) 2014-01-31 2015-08-06 Lm Wp Patent Holding A/S Partie de pale d'éolienne fabriquée en deux étapes
WO2015114100A1 (fr) * 2014-01-31 2015-08-06 Lm Wp Patent Holding A/S Pale d'éolienne à transition fibreuse améliorée
CN106457696B (zh) * 2014-01-31 2021-08-17 Lm Wp 专利控股有限公司 以两个步骤制造的风力涡轮机叶片部件
CN106457696A (zh) * 2014-01-31 2017-02-22 Lm Wp 专利控股有限公司 以两个步骤制造的风力涡轮机叶片部件
US10960617B2 (en) 2014-10-24 2021-03-30 Short Brothers Plc Apparatus and methods for manufacturing and repairing fibre-reinforced composite materials
CN107073848B (zh) * 2014-10-24 2020-07-03 肖特兄弟公司 用于制造和修复纤维增强复合材料的设备和方法
CN107073848A (zh) * 2014-10-24 2017-08-18 肖特兄弟公司 用于制造和修复纤维增强复合材料的设备和方法
WO2016063065A1 (fr) * 2014-10-24 2016-04-28 Short Brothers Plc Appareil et procédés de fabrication et de réparation de matériaux composites renforcés par fibres
DE102016219137A1 (de) * 2016-10-04 2018-04-05 Bayerische Motoren Werke Aktiengesellschaft Verfahren zur Herstellung eines Faserverbundbauteils mit Überlappstoß oder lokaler Verstärkung
DE102016219137B4 (de) 2016-10-04 2026-02-12 Bayerische Motoren Werke Aktiengesellschaft Verfahren zur Herstellung eines Faserverbundbauteils mit Überlappstoß oder lokaler Verstärkung
CN109916526A (zh) * 2019-03-11 2019-06-21 西北工业大学 一种用于涡轮叶片上ito薄膜热电偶电信号引出的背引线结构及制备方法
EP4454852A1 (fr) * 2023-04-28 2024-10-30 Siemens Gamesa Renewable Energy A/S Table d'emballage pour la fabrication d'un adaptateur d'assemblage utilisé dans un procédé d'assemblage
WO2024223204A1 (fr) * 2023-04-28 2024-10-31 Siemens Gamesa Renewable Energy A/S Table d'emballage pour la fabrication d'un adaptateur d'assemblage à utiliser dans un procédé d'assemblage d'une section de pale extérieure à une section de pale intérieure d'une pale d'éolienne divisée longitudinalement et procédé de fabrication d'un adaptateur d'assemblage

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