EP4688405A1 - Systèmes et procédés de fabrication de pièces composites par empilement - Google Patents

Systèmes et procédés de fabrication de pièces composites par empilement

Info

Publication number
EP4688405A1
EP4688405A1 EP23726184.7A EP23726184A EP4688405A1 EP 4688405 A1 EP4688405 A1 EP 4688405A1 EP 23726184 A EP23726184 A EP 23726184A EP 4688405 A1 EP4688405 A1 EP 4688405A1
Authority
EP
European Patent Office
Prior art keywords
laminate
stacked
shape
laminate layers
layers
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
EP23726184.7A
Other languages
German (de)
English (en)
Inventor
Stefaan VAN NIEUWENHOVE
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.)
GE Vernova Infrastructure Technology LLC
Original Assignee
GE Vernova Infrastructure Technology LLC
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 GE Vernova Infrastructure Technology LLC filed Critical GE Vernova Infrastructure Technology LLC
Publication of EP4688405A1 publication Critical patent/EP4688405A1/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
    • 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
    • B29D99/0028—Producing blades or the like, e.g. blades for turbines, propellers, or wings hollow blades
    • 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
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/30—Mounting, exchanging or centering
    • B29C33/308—Adjustable moulds
    • 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
    • B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
    • B29C70/205—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres the structure being shaped to form a three-dimensional configuration
    • B29C70/207—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres the structure being shaped to form a three-dimensional configuration arranged in parallel planes of fibres crossing at substantial angles
    • 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
    • B29C2793/00—Shaping techniques involving a cutting or machining operation
    • B29C2793/0081—Shaping techniques involving a cutting or machining operation before shaping
    • 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
    • B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
    • 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
    • B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
    • B29C70/088—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of non-plastics material or non-specified material, e.g. supports
    • 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
    • B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
    • 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 disclosure relates generally to rotor blades, and more particularly to systems and methods for manufacturing composite parts via stacking that can be used to manufacture rotor blades.
  • Wind power is considered one of the cleanest, most environmentally friendly energy sources presently available, and wind turbines have gained increased attention in this regard.
  • a modern wind turbine typically includes a tower, a generator, a gearbox, a nacelle, and one or more rotor blades.
  • the rotor blades capture kinetic energy of wind using known foil principles.
  • the rotor blades transmit the kinetic energy in the form of rotational energy so as to turn a shaft coupling the rotor blades to a gearbox, or if a gearbox is not used, directly to the generator.
  • the generator then converts the mechanical energy to electrical energy that may be deployed to a utility grid.
  • the rotor blades generally include a suction side shell and a pressure side shell typically manufactured using molding processes and then bonded together at bond lines along the leading and trailing edges of the blade.
  • the pressure and suction shells are relatively lightweight and have structural properties (e.g., stiffness, buckling resistance and strength) which are not configured to withstand the bending moments and other loads exerted on the rotor blade during operation.
  • the body shell is typically reinforced using one or more structural components (e.g., opposing spar caps with a shear web configured therebetween).
  • the spar caps are typically constructed of various materials, including but not limited to glass fiber laminate composites and/or carbon fiber laminate composites.
  • the shell of the rotor blade is generally built around the spar caps of the blade by stacking layers of fiber fabrics in a shell mold. The layers are then typically shaped and infused together with a resin.
  • conventional infusion processes such as vacuum assisted resin transfer molding (VARTM)
  • VARTM vacuum assisted resin transfer molding
  • Such challenges may include, for example, quality issues such as in-plane and/or out-of- plane wrinkling, damaged or broken fibers, locally separated layers of the fiber fabrics, and/or local changes to the fiber volume fraction due to matrix material movement.
  • design safety margins need to be higher, especially as manufacturing costs increase.
  • the ability to thermoform flat, fiber- reinforced reinforced laminates with a thermoplastic resin to form a three-dimensional object is limited due to the uncontrolled behavior of the fibers and stresses generated inside the laminate. This behavior becomes more severe with thicker laminates or when component parts having smaller radiuses are required.
  • the art is continuously seeking new and improved methods for manufacturing composite parts that can be used to manufacture rotor blades and components thereof. Accordingly, the present disclosure is directed to systems and methods for manufacturing composite parts via stacking that can be used to manufacture rotor blades that address the aforementioned limitations.
  • the present disclosure is directed to a method of manufacturing a composite part.
  • the method includes manufacturing a plurality of laminate layers by integrating a fiber material with a matrix material.
  • the method also includes stacking the plurality of laminate layers atop each other to form a stacked laminate part.
  • the method also includes applying a partial vacuum to the stacked laminate part.
  • the method also includes modifying a shape of the stacked laminate part by allowing one or more of the plurality of laminate layers to slide with respect to each other under the partial vacuum.
  • the method also includes applying a full vacuum to the modified shape of the stacked laminate part and heating the stacked laminate part to fuse the plurality of laminate layers together to manufacture the composite part.
  • the matrix material includes a thermoplastic resin.
  • the partial vacuum includes a pressure of less than about one (1) bar.
  • the method further includes applying heat to the stacked laminate part before or while the shape of the stacked laminate part is modified.
  • the heat applied is less than the glass transition temperature of the matrix material of the plurality of laminate layers.
  • the method further includes placing the stacked laminate part on an adaptable tool where the adaptable tool includes a surface that changes shape.
  • the step of modifying a shape of the stacked laminate part by allowing one or more of the plurality of laminate layers to slide with respect to each other under the partial vacuum includes changing the shape of the surface of the adaptable tool, thereby allowing the one or more of the plurality of laminate layers to slide with respect to each other under partial vacuum to form the shape.
  • the step of heating the stacked laminate part to fuse the plurality of laminate layers together to manufacture the composite part includes applying a heat above the glass transition temperature of the matrix material of the plurality of laminate layers.
  • the method further includes placing the stacked laminate part within a vacuum unit.
  • the method further includes machining the plurality of laminate layers prior to stacking.
  • the adaptable tool includes a radius of curvature less than the desired radius of curvature for the composite part.
  • the adaptable tool includes a radius of curvature greater than the desired radius of curvature for the composite part.
  • the method further includes applying an adhesive material or a core material between one or more of the plurality of laminate layers before the plurality of laminate layers are stacked atop each other.
  • at least one of a top laminate layer or a bottom laminate layer of the plurality of laminate layers includes a different material providing a different surface than surfaces of inner laminate layers of the plurality of laminate layers.
  • the different material includes a coating material.
  • the different material includes an attachment location for a pre-manufactured part of a rotor blade
  • the method further includes positioning the pre-manufactured part of the rotor blade with the plurality of laminate layers before the stacked laminate part is fused together.
  • the pre-manufactured part includes at least one of a patch, an attachment block, or a stiffener.
  • the pre-manufactured part includes a profile having at least one of a tube-shape, angled-shape, L-shape, square-shape, or a T-shape.
  • the composite part is part of a rotor blade.
  • the present disclosure is directed to a method for manufacturing a composite part.
  • the method includes manufacturing a plurality of laminate layers of at least one fiber material and a matrix material.
  • the method also includes stacking the plurality of laminate layers atop each other to form a stacked laminate part.
  • the method also includes placing the stacked laminate part within a vacuum bag.
  • the method also includes placing the vacuum bag on an adaptable tool.
  • the method also includes providing a partial vacuum within the vacuum bag around the stacked laminate part.
  • the method also includes modifying a shape of the stacked laminate part, via the adaptable tool, by allowing one or more of the plurality of laminate layers to slide with respect to each other under the partial vacuum.
  • the method also includes applying a full vacuum to the modified shape of the stacked laminate part and heating the stacked laminate part to fuse the plurality of laminate layers together to manufacture the composite part.
  • the present disclosure is directed to a system of manufacturing a composite part of a rotor blade.
  • the system includes a plurality of laminate layers stacked atop each other to form a stacked laminate part, the plurality of laminate layers each including a fiber material and a matrix material.
  • the system also includes a vacuum unit for applying a partial vacuum and a full vacuum to the stacked laminate part.
  • the system also includes an adaptable tool for receiving the stacked laminate part where the adaptable tool includes a surface that changes shape, and the stacked laminate part changes shape when placed atop the adaptable tool and the surface of the adaptable tool changes shape by allowing one or more of the plurality of laminate layers to slide with respect to each other under partial vacuum.
  • the system also includes a heating device configured to provide heat to the stacked laminate part to assist with modifying the shape of the stacked laminate part.
  • FIG. 1 illustrates a perspective view of an embodiment of a wind turbine according to the present disclosure
  • FIG. 2 illustrates a perspective view of an embodiment of a rotor blade of a wind turbine according to the present disclosure
  • FIG. 3 illustrates an exploded view of the modular rotor blade of FIG. 2;
  • FIG. 4 illustrates a cross-sectional view of an embodiment of a leading edge segment of a modular rotor blade according to the present disclosure;
  • FIG. 5 illustrates a cross-sectional view of an embodiment of a trailing edge segment of a modular rotor blade according to the present disclosure
  • FIG. 6 illustrates a cross-sectional view of the modular rotor blade of FIG. 2 according to the present disclosure
  • FIG. 7 illustrates a cross-sectional view of the modular rotor blade of FIG. 2 according to the present disclosure
  • FIG. 8 illustrates a flow diagram of an embodiment of a method of manufacturing a composite part via stacking according to the present disclosure
  • FIG. 9 illustrates a simplified diagram of an embodiment of a laminate according to the present disclosure
  • FIG. 10 illustrates a simplified diagram of an embodiment of a laminate being machined according to the present disclosure
  • FIGS. 11 A-l IB illustrate cross-sectional views of various embodiments of a stacked laminate part according to the present disclosure
  • FIG. 12 illustrates a cross-sectional view of an embodiment of the stacked laminate part according to the present disclosure, particularly illustrating various surfaces, profiles, and core materials of the stacked laminate part;
  • FIG. 13 illustrates a simplified diagram of an embodiment of an adaptable tool having a plurality of laminate layers assembled thereon according to the present disclosure
  • FIGS. 14A-14C illustrate simplified diagrams of an embodiment of a process of assembling and shaping laminate layers on an adaptable tool according to the present disclosure.
  • FIGS. 15A-15B illustrate simplified diagrams of an embodiment of a process of assembling and forming laminate layers within a vacuum bag according to the present disclosure.
  • the laminate layers can be manufactured by integrating a fiber material with a matrix material, such as a resin. Once manufactured, the laminate layers can then be stacked atop each other to form a stacked laminate part, and the stacked laminate part can be prepared for forming into the shape of the composite part.
  • An example of preparing the stacked laminate part may include placing a partial vacuum around the stacked laminate part to help control the movement of the individual laminate layers of the stacked laminate part.
  • the stacked laminate part can then be modified into a desired shape for the composite part, and then the desired shape can be set by fusing the individual laminate layers together.
  • the final shape may be set by applying a full vacuum and heat to the stacked laminate part.
  • the composite part can be used in a variety of applications, such as in manufacturing a wind turbine rotor blade.
  • the process and the composite parts produced from such a process described herein may also be used in a number of applications.
  • the process and the composite parts produced from such a process may be used as rotor blades in other applications, parts in watercraft, and/or parts in aircraft.
  • the systems and methods described herein provide many advantages not present in the prior art.
  • the systems and methods allow for thinner laminate layers to be used to form composite parts than those previously available.
  • the behavior of the fibers of the laminate layers may be more readily controlled when forming the composite part.
  • various quality issues associated with conventional thicker laminate layers may be avoided.
  • the present disclosure avoids the issues of in-plane and/or out-of-plane wrinkling, damaged or broken fibers, locally separated layers of the fiber fabrics, and local changes to the fiber volume fraction due to matrix material movement. This advantage is especially evident when compared to laminate layers with higher thicknesses or composite parts that require small radii of curvature.
  • the individual laminate layers may be more easily customized based on the desired application of the composite part.
  • the size, shape, fiber orientations, fiber volume fraction, or fiber materials may vary between individual laminate layers, thereby optimizing the mechanical properties for the particular application. This optimization may also result in composite parts with a lower total mass which is especially beneficial in the field of wind turbine rotor blades.
  • the laminate layers of the present disclosure can be prefabricated and stacked together in a separate step(s). By performing these steps separately, the processing time related to the formation of the laminate layers into a desired shape is reduced when compared to conventional methods.
  • FIG. 1 illustrates one embodiment of a wind turbine 10 according to the present disclosure.
  • the wind turbine 10 includes a tower 12 with a nacelle 14 mounted thereon.
  • a plurality of rotor blades 16 are mounted to a rotor hub 18, which is in turn connected to a main flange that turns a main rotor shaft.
  • the wind turbine power generation and control components are housed within the nacelle 14.
  • the view of FIG. 1 is provided for illustrative purposes only to place the present invention in an exemplary field of use. It should be appreciated that the invention is not limited to any particular type of wind turbine configuration.
  • the present invention is not limited to use with wind turbines, but may be utilized in any application using resin materials. Further, the methods described herein may also apply to manufacturing any similar structure that benefits from the resin formulations described herein.
  • the illustrated rotor blade 16 has a segmented or modular configuration. It should also be understood that the rotor blade 16 may include any other suitable configuration now known or later developed in the art.
  • the modular rotor blade 16 includes a main blade structure 15 and at least one blade segment 21 secured to the main blade structure 15. More specifically, as shown, the rotor blade 16 includes a plurality of blade segments 21.
  • the main blade structure 15 may include any one of or a combination of the following: a pre-formed blade root section 20, a pre- formed blade tip section 22, one or more one or more continuous spar caps 48, 50, 51, 53, one or more shear webs 35 (FIGS. 6-7), an additional structural component 52 secured to the blade root section 20, and/or any other suitable structural component of the rotor blade 16.
  • the blade root section 20 is configured to be mounted or otherwise secured to the rotor 18 (FIG. 1).
  • the rotor blade 16 defines a span 23 that is equal to the total length between the blade root section 20 and the blade tip section 22. As shown in FIGS.
  • the rotor blade 16 also defines a chord 25 that is equal to the total length between a leading edge 24 of the rotor blade 16 and a trailing edge 26 of the rotor blade 16.
  • the chord 25 may generally vary in length with respect to the span 23 as the rotor blade 16 extends from the blade root section 20 to the blade tip section 22.
  • any number of blade segments 21 or panels (also referred to herein as blade shells) having any suitable size and/or shape may be generally arranged between the blade root section 20 and the blade tip section 22 along a longitudinal axis 27 in a generally span-wise direction.
  • the blade segments 21 generally serve as the outer casing/covering of the rotor blade 16 and may define a substantially aerodynamic profile, such as by defining a symmetrical or cambered airfoil-shaped cross-section.
  • the blade segment portion of the blade 16 may include any combination of the segments described herein and are not limited to the embodiment as depicted. More specifically, in certain embodiments, the blade segments 21 may include any one of or combination of the following: pressure and/or suction side segments 44, 46, (FIGS. 2 and 3), leading and/or trailing edge segments 40, 42 (FIGS. 2-6), a non-jointed segment, a single-jointed segment, a multi -jointed blade segment, a J-shaped blade segment, or similar.
  • the leading edge segments 40 may have a forward pressure side surface 28 and a forward suction side surface 30.
  • each of the trailing edge segments 42 may have an aft pressure side surface 32 and an aft suction side surface 34.
  • the forward pressure side surface 28 of the leading edge segment 40 and the aft pressure side surface 32 of the trailing edge segment 42 generally define a pressure side surface of the rotor blade 16.
  • the forward suction side surface 30 of the leading edge segment 40 and the aft suction side surface 34 of the trailing edge segment 42 generally define a suction side surface of the rotor blade 16.
  • leading edge segment(s) 40 and the trailing edge segment(s) 42 may be joined at a pressure side seam 36 and a suction side seam 38.
  • the blade segments 40, 42 may be configured to overlap at the pressure side seam 36 and/or the suction side seam 38.
  • adjacent blade segments 21 may be configured to overlap at a seam 54.
  • the various segments of the rotor blade 16 may be secured together via an adhesive (or mechanical fasteners) configured between the overlapping leading and trailing edge segments 40, 42 and/or the overlapping adjacent leading or trailing edge segments 40, 42.
  • the blade root section 20 may include one or more longitudinally extending spar caps 48, 50 integrated therewith.
  • the blade root section 20 may be configured according to U.S. Application Number 14/753,155 filed June 29, 2015, entitled “Blade Root Section for a Modular Rotor Blade and Method of Manufacturing Same” which is incorporated herein by reference in its entirety.
  • the blade tip section 22 may include one or more longitudinally extending spar caps 51, 53 integrated therewith. More specifically, as shown, the spar caps 48, 50, 51, 53 may be configured to be engaged against opposing inner surfaces of the blade segments 21 of the rotor blade 16. Further, the blade root spar caps 48, 50 may be configured to align with the blade tip spar caps 51, 53. Thus, the spar caps 48, 50, 51, 53 may generally be designed to control the bending stresses and/or other loads acting on the rotor blade 16 in a generally span-wise direction (a direction parallel to the span 23 of the rotor blade 16) during operation of a wind turbine 10.
  • the spar caps 48, 50, 51, 53 may be designed to withstand the span-wise compression occurring during operation of the wind turbine 10. Further, the spar cap(s) 48, 50, 51, 53 may be configured to extend from the blade root section 20 to the blade tip section 22 or a portion thereof. Thus, in certain embodiments, the blade root section 20 and the blade tip section 22 may be joined together via their respective spar caps 48, 50, 51, 53. [0058] Referring to FIGS. 6-7, one or more shear webs 35 may be configured between the one or more spar caps 48, 50, 51, 53. More particularly, the shear web(s) 35 may be configured to increase the rigidity in the blade root section 20 and/or the blade tip section 22. Further, the shear web(s) 35 may be configured to close out the blade root section 20.
  • the additional structural component 52 may be secured to the blade root section 20 and extend in a generally span-wise direction so as to provide further support to the rotor blade 16.
  • the structural component 52 may be configured according to U.S.
  • the structural component 52 may extend any suitable distance between the blade root section 20 and the blade tip section 22.
  • the structural component 52 is configured to provide additional structural support for the rotor blade 16 as well as an optional mounting structure for the various blade segments 21 as described herein.
  • the structural component 52 may be secured to the blade root section 20 and may extend a predetermined spanwise distance such that the leading and/or trailing edge segments 40, 42 can be mounted thereto.
  • FIG. 8 a flow diagram of a method 200 of manufacturing a composite part is illustrated according to the present disclosure. It should be understood that the method 200 may be used to manufacture the laminate layers 100 described herein. Though FIG. 8 depicts steps performed in a particular order for purposes of illustration and discussion, those of ordinary skill in the art, using the disclosures provided herein, will understand that various steps of the method 200 or any of the methods disclosed herein, may be adapted, modified, rearranged, performed simultaneously, or modified in various ways without deviating from the scope of the present disclosure.
  • the method 200 includes manufacturing a plurality of laminate layers by integrating a fiber material with a matrix material. As shown at (204), the method 200 includes stacking the plurality of laminate layers atop each other to form a stacked laminate part. As shown at (206), the method 200 includes applying a partial vacuum to the stacked laminate part. As shown at (208), the method 200 includes modifying a shape of the stacked laminate part by allowing one or more of the plurality of laminate layers to slide with respect to each other under the partial vacuum. As shown at (210), the method 200 includes applying a full vacuum to the modified shape of the stacked laminate part and heating the stacked laminate part to fuse the plurality of laminate layers together to form the composite part.
  • FIG. 9 illustrates a simplified diagram of an embodiment of one of the laminate layers according to the present disclosure.
  • the laminate layer 100 is constructed of a fiber material 102 with a matrix material 104.
  • the laminate layers 100 described herein may include one or more layers produced from the fiber material 102 and the matrix material 104, respectively.
  • each of the laminate layers 100 may include a single layer 106 (see e.g., the middle or bottom laminate layers 100 in FIG. 13) or multiple layers 106 (see e.g., the top laminate layer 100 in FIG. 13).
  • each of the laminate layers 100 may include different fiber materials 102.
  • a first laminate layer 100 may have a fiber length that is greater or smaller than another fiber material 102 in another laminate layer 100.
  • the shape of the fiber material 102 in a first laminate layer 100 may differ from the shape of a fiber material 102 in another laminate layer 100.
  • a first laminate layer 100 may have a fiber material 102 of a smaller width or length than fiber materials of another laminate layer 100.
  • the fiber volume fraction of a first laminate layer 100 may differ from the fiber volume fraction of another laminate layer 100.
  • a first laminate layer 100 may have a greater or lesser volume of fiber material 102 per the total volume of the laminate layer 100 when compared to another laminate layer 100.
  • the fiber orientations may differ between individual laminate layers 100.
  • a first laminate layer 100 may include multi-axial, unidirectional, biaxial, or triaxial fiber orientations while another laminate layer 100 includes a different fiber orientation.
  • the fiber material 102 of a first laminate layer 100 may differ from another laminate layer 100.
  • glass fibers, carbon fibers, polymer fibers, wood fibers, bamboo fibers, ceramic fibers, nanofibers, metal fibers, or combinations may be used for a first laminate layer 100 while a different fiber material 102 may be used for another laminate layer 100.
  • the fiber material(s) 102 described herein may include, but is not limited to glass fibers, carbon fibers, polymer fibers, wood fibers, bamboo fibers, ceramic fibers, nanofibers, metal fibers, or combinations thereof.
  • the direction of the fibers may include multi-axial, unidirectional, biaxial, triaxial, or any other another suitable direction and/or combinations thereof.
  • the fiber material 102 may contain predominantly unidirectional fibers.
  • the fiber material 102 may include woven or non-woven multi-axial fibers.
  • the fiber materials 102 may include fibers with a continuous length which span the entire length of a laminate layer 100.
  • the fiber materials 102 may include relatively long fibers, such as greater than about 10 millimeters (mm), more preferably about 15 mm, and still more preferably about 20 mm.
  • the matrix material 104 may be a resin material, such as a thermoplastic material.
  • the thermoplastic materials as described herein generally encompass a plastic material or polymer that is reversible in nature.
  • thermoplastic materials typically become pliable or moldable when heated to a certain temperature and returns to a more rigid state upon cooling.
  • thermoplastic materials may include amorphous thermoplastic materials and/or semi-crystalline thermoplastic materials.
  • Exemplary semi-crystalline thermoplastic materials may generally include, but are not limited to polyolefins, polyamides, fluoropolymer, ethyl-methyl acrylate, polyesters, polycarbonates, and/or acetals.
  • exemplary semi-crystalline thermoplastic materials may include poly(butylene terephthalate) (PBT), poly(ethylene terephthalate) (PET), polytrimethylene terephthalate (PTT), polypropylene, poly(phenyl sulfide), polyethylene, polyamide (nylon), polyetherketone, or any other suitable semicrystalline thermoplastic material.
  • PBT poly(butylene terephthalate)
  • PET poly(ethylene terephthalate)
  • PTT polytrimethylene terephthalate
  • polypropylene poly(phenyl sulfide)
  • polyethylene polyamide
  • nylon polyetherketone
  • any other suitable semicrystalline thermoplastic material may include poly(butylene terephthalate) (PBT), poly(ethylene terephthalate) (PET), polytrimethylene terephthalate (PTT), polypropylene, poly(phenyl sulfide), polyethylene, polyamide (nylon), polyetherketone, or any other suitable semicrystalline thermoplastic material.
  • Amorphous thermoplastic materials as described herein generally encompass a plastic material or polymer that is reversible in nature.
  • amorphous thermoplastic materials typically become pliable or moldable when heated to a certain temperature and returns to a more rigid state upon cooling.
  • Some example amorphous thermoplastic materials may generally include, but are not limited to, styrenes, vinyls, cellulosics, polyesters, acrylics, polysulfones, and/or imides.
  • exemplary amorphous thermoplastic materials may include polystyrene, acrylonitrile butadiene styrene (ABS), poly(m ethyl methacrylate) (PMMA), polyethylene terephthalate glycol (PETG), polycarbonate, poly(vinyl acetate), amorphous polyamide, poly(vinyl chloride) (PVC), poly(vinylidene chloride), polyurethane, or any other suitable amorphous thermoplastic material.
  • ABS acrylonitrile butadiene styrene
  • PMMA poly(m ethyl methacrylate)
  • PETG polyethylene terephthalate glycol
  • PVC poly(vinyl chloride)
  • PVC poly(vinylidene chloride)
  • polyurethane or any other suitable amorphous thermoplastic material.
  • the resin material may also include a thermoset material.
  • the thermoset materials as described herein generally encompass a plastic material or polymer that is non-reversible in nature.
  • thermoset materials once cured, cannot be easily remolded, or returned to a liquid state.
  • thermoset materials are generally resistant to heat, corrosion, and/or creep.
  • Example thermoset materials may generally include, but are not limited to, some polyesters, some polyurethanes, esters, epoxies, or any other suitable thermoset material. If a thermoset material is selected as the matrix material 104, bonding between laminate layers 100 may be enhanced by providing a material such as a core material, (see e.g., FIG. 12).
  • the fiber and matrix materials 102, 104 may be integrated together to manufacture the laminate layer 100. Accordingly, in an embodiment, a plurality of laminate layers 100 can be manufactured and stacked together to form a stacked laminate part 112. (see e.g., FIGS. 1 I-15B).
  • the stacked laminate part 112 can be easily tailored to satisfy specific requirements or specifications for various wind turbine components. For example, if it is known that a particular region of the stacked laminate part 112 will experience a higher amount of mechanical stress than other regions of the part (e.g., due to its location on the rotor blade), the properties of that region may be tailored by providing distinct laminate layers 100 in that region. In addition, if production methods of the stacked laminate part 112 have specific properties, specific laminate layers 100 may be chosen to meet those properties.
  • the laminate layers 100 can be machined prior to being used in the production of the composite part and arranged on the table for subsequent joining.
  • the laminate layers 100 can be placed on the machining table 108 such as a cutting table, and machined into a particular shape.
  • the laminate layers 100 can be cut into individual pieces 110 that can be used as individual laminate layers 100 to produce a composite part. These pieces 110 may be arranged on the machining table 108 in preparation for how the pieces 110 could be arranged on an adaptable tool for shaping.
  • laminate layers 100 have an asymmetrical orientation when stacked together (see e.g., FIGS. 12-14C), the orientation of this asymmetrical stack may be arranged on the machining table 108 in preparation for stacking on an adaptable tool.
  • the individual pieces 110 may be separated and used as laminate layers 100 to produce multiple composite parts.
  • the stacked laminate part 112 includes the laminate layers 100 having a layer of an adhesive material 105, such as a resin, arranged between the individual laminate layers 100.
  • the stacked laminate part 112 includes the laminate layers 100 having the adhesive material 105 deposited directly onto the surface of the laminate layers 100 before the laminate layers 100 are stacked together.
  • the adhesive material 105 may be applied between each of the laminate layers 100.
  • the adhesive material 105 may also be applied only between some of the layers of laminate layers 100. Regardless of whether the adhesive material 105 is deposited as a layer or directly on a surface of the laminate layers 100, adhesive material 105 would further help with the bonding of the individual laminate layers 100 in addition to the matrix material 104 used to manufacture the individual laminate layers 100.
  • the stacked laminate part 112 includes a top laminate layer 101 and a bottom laminate layer 103, at least one of which has a different material 114 that provides a different surface than surfaces of the inner laminate layers 100 of the stacked laminate part 112.
  • the different material 114 may be an erosion-resistant material, such as a coating material.
  • the stacked laminate part 112 may include one or more additional components 116 that can be attached to the top and/or bottom laminate layers 100.
  • the additional components 116 may include a pre-manufactured part of the rotor blade 16, such as a patch, an attachment block, or a stiffener.
  • the pre-manufactured part may also be a pre-formed blade root section 20, a pre-formed blade tip section 22, one or more one or more continuous spar caps 48, 50, 51, 53, one or more shear webs 35 (FIGS. 6-7), an additional structural component 52 secured to the blade root section 20, and/or any other suitable structural component of the rotor blade 16.
  • the additional components 116 may also have a general shape required for a particular application, such as a tube-shape, angled-shape, L-shape, square-shape, or a T-shape.
  • the different materials and/or components 114, 116 may be shaped and bonded with the stacked laminate part 112, thereby ensuring a bond between the stacked laminate part 112 and the different materials and/or components 114, 116 without any further needed production steps.
  • the stacked laminate part 112 is shaped by an adaptable tool (see e.g., FIGS. 14A-14C) the different materials and/or components 114, 116 may also be shaped along with the stacked laminate part 112.
  • the stacked laminate part 112 may include one or more core materials 118 between one or more of the laminate layers 100.
  • the core material 118 is configured to assist with altering one or more mechanical properties of the composite part.
  • Some examples of possible core materials 118 may include, for example, plastic, balsa, metal, foam, etc.
  • the core materials 118 may also include materials with particular internal configurations such as a honeycomb framework.
  • the core material 118 may include an uncured thermoset material or a thermoplastic material. In such embodiments, the core materials 118 are configured to further tailor the composite part.
  • FIG. 13 a simplified diagram of an embodiment of an adaptable tool 120 having a plurality of laminate layers 100 assembled thereon is depicted according to the present disclosure.
  • the laminate layers 100 can be stacked together to form the stacked laminate part 112 and the part 112 can be placed atop the tool 120.
  • the adaptable tool 120 is capable of modifying a shape of the stacked laminate part 112.
  • the adaptable tool 120 may include a platform 122 that assists with moving the laminate layers 100 with respect to each other, as will be discussed in greater detail with reference to FIGS. 14A-14C.
  • the adaptable tool 120 may include a vacuum unit 124 capable of providing a partial vacuum and/or a full vacuum around or to the stacked laminate part 112.
  • a partial vacuum may include a pressure which is measured relative to atmospheric pressure. More specifically, in an embodiment, the partial vacuum may include a pressure that is less than about one (1) bar, such as less than about 0.95 bar, such as less than about 0.925 bar, such as less than about 0.9 bar.
  • the vacuum unit 124 may also be capable of providing a full vacuum.
  • a full vacuum may include a pressure that is less than about 0.2 bar, such as less than 0.1 bar, such as less than 0.05 bar.
  • the adaptable tool 120 may also include one or more heating elements 126, 128, 130.
  • one of the heating elements 126, 128, 130 may be provided above, below, or on the side of the stacked laminate part to provide uniform heating to the stacked laminate part 112.
  • each of these heating elements 126, 128, 130 may be capable of providing various temperatures that are particularly advantageous when producing the composite part described herein.
  • the heating elements 126, 128, 130 may be capable of providing a heat that is specific to the matrix material 104 of the laminate layers 100. More specifically, in an embodiment, the heating elements 126, 128, 130 may be capable of providing a heat less than the glass transition temperature of the matrix material 104 of the laminate layers 100. This lower temperature heat could be applied before or during the operation of the adaptable tool 120 and allow for the laminate layers 100 to move or slide while requiring less force be applied than would otherwise be required without the application of heat.
  • the shaping of the stacked laminate part 112 may be performed with less effort or mechanical force.
  • the heating elements 126, 128, 130 may also be capable of providing a heat above the glass transition temperature of the matrix material 104 of the laminate layers 100.
  • the laminate layers 100 may be fused together to form the composite part. Further, by providing a heat above the glass transition temperature, the stresses between the laminate layers 100 may be reduced.
  • the heat applied may be above the glass transition temperature of both the matrix material 104 of the laminate layers 100 and the adhesive material 105 applied between the laminate layers 100.
  • FIGS. 14A-14C simplified diagrams of an embodiment of a process of assembling and shaping laminate layers 100 on an adaptable tool 120 are shown according to the present disclosure.
  • the platform 122 of the adaptable tool 120 can change shape to allow the laminate layers 100 to move and/or slide with respect to each other, thereby forming the stacked laminate part 112 into a desired shape.
  • a partial vacuum and heat e.g., below the glass transition, may be applied via either the vacuum unit 124 and/or the heating elements 126, 128, 130 to assist in controlling the shaping as desired.
  • the adaptable tool 120 may begin with a flat, planar platform 122. Then, the platform 122 may be curved to a define a radius of curvature. As the platform 122 curves, the laminate layers 100 also curve with a similar radius of curvature to reach a desired shape.
  • the selected shape for the platform 122 of the adaptable tool 120 may be the final shape of the composite part 132.
  • the selected shape for the platform 122 of the adaptable tool 120 may include a radius of curvature less than or greater than the final desired radius of curvature for the composite part 132.
  • the radius of curvature of the platform 122 of the adaptable tool 120 may be about 0.5 to about 1.5 times the radius of curvature of the composite part 132.
  • the platform 122 may also provide a variety of other shapes with their own radiuses of curvature similar to the radius of curvature as aforementioned.
  • the pressure within the vacuum unit 124 may be decreased to provide a full vacuum as detailed above.
  • the shape of the stacked laminate part 112 is secured in preparation for fusing.
  • heat above the glass transition temperature may be applied by one or more of the heating elements 126, 128, 130 to fuse the laminate layers 100 together to form the composite part 132.
  • the composite part 132 can be removed from the adaptable tool 120 and used in the desired application (e.g., to manufacture a part of the rotor blade).
  • FIGS. 15A-15B simplified diagrams of an embodiment of a process of assembling and manufacturing laminate layers 100 within a vacuum bag 134 are illustrated according to the present disclosure.
  • the formation of a composite part 132 may also be accomplished through the use of a vacuum bag 134.
  • a vacuum bag 134 may act as a mold or partition in which the stacked laminate 112 may be placed.
  • the vacuum bag 134 may also be capable of acting as a vacuum unit capable of providing a partial of full vacuum similar to vacuum unit 124 described above.
  • the vacuum bag 134 may be moveable between surfaces such as the machining table 108 or the adaptable tool 120 and provide more efficiency of movement of the stacked laminate part 112 when transitioning from the stacking and shaping steps of production.
  • the vacuum bag 134 may be placed on the platform 122 of the adaptable tool 120.
  • a partial vacuum may then be provided around the stacked laminate part 112 via the vacuum bag 134.
  • the shape of the stacked laminate part 112 may then be modified by modifying the shape of the platform 122 of the adaptable tool 120 resulting in the laminate layers 100 sliding with respect to each other under the partial vacuum.
  • the vacuum bag 134 may be connected to the platform 122, and the vacuum bag 134 along with the stacked laminate part 112 may be stretched or modified to the shape the platform 122 takes when the adaptable tool 120 is operated.
  • This shaping step may be similar to the shaping step depicted in FIGS. 14A-14B.
  • a full vacuum may be applied via the vacuum bag 134 and the stacked laminate part 112 may be heated to fuse the laminate layers 100 with each other thereby forming the composite part 132 similar to the fusing step discussed in FIG. 13C.
  • the composite part 132 may be removed from the vacuum bag 134 and used in the desired application.
  • a method of manufacturing a composite part comprising: manufacturing a plurality of laminate layers by integrating a fiber material with a matrix material; stacking the plurality of laminate layers atop each other to form a stacked laminate part; applying a partial vacuum to the stacked laminate part; modifying a shape of the stacked laminate part by allowing one or more of the plurality of laminate layers to slide with respect to each other under the partial vacuum; and applying a full vacuum to the modified shape of the stacked laminate part and heating the stacked laminate part to fuse the plurality of laminate layers together to manufacture the composite part.
  • Clause 3 The method of any of clauses 1-2, wherein the partial vacuum comprises a pressure of less than about one (1) bar.
  • Clause 4 The method of any of the preceding clauses, further comprising applying heat to the stacked laminate part before or while the shape of the stacked laminate part is modified.
  • Clause 6 The method of any of the preceding clauses, further comprising: placing the stacked laminate part on an adaptable tool, wherein the adaptable tool comprises a surface that changes shape, wherein modifying a shape of the stacked laminate part by allowing one or more of the plurality of laminate layers to slide with respect to each other under the partial vacuum further includes changing the shape of the surface of the adaptable tool, thereby allowing the one or more of the plurality of laminate layers to slide with respect to each other under partial vacuum to form the shape.
  • Clause 7 The method of any of the preceding clauses, wherein heating the stacked laminate part to fuse the plurality of laminate layers together to manufacture the composite part comprises applying a heat above the glass transition temperature of the matrix material of the plurality of laminate layers.
  • Clause 8 The method of any of the preceding clauses, further comprising placing the stacked laminate part within a vacuum unit.
  • Clause 9 The method of any of the preceding clauses, further comprising machining the plurality of laminate layers prior to stacking.
  • Clause 13 The method of any of the preceding clauses, wherein at least one of a top laminate layer or a bottom laminate layer of the plurality of laminate layers comprises a different material providing a different surface than surfaces of inner laminate layers of the plurality of laminate layers.
  • Clause 14 The method of clause 13, wherein the different material comprises a coating material.
  • Clause 15 The method of any of clauses 13-14, wherein the different material comprises an attachment location for a pre-manufactured part of a rotor blade, wherein the method further comprises positioning the pre-manufactured part of the rotor blade with the plurality of laminate layers before the stacked laminate part is fused together.
  • Clause 16 The method of clause 15, wherein the pre-manufactured part comprises at least one of a patch, an attachment block, or a stiffener.
  • Clause 17 The method of any of clauses 15-16, wherein the premanufactured part comprises a profile having at least one of a tube-shape, angled- shape, L-shape, square-shape, or a T-shape.
  • Clause 18 The method of any of the preceding clauses, wherein the composite part is part of a rotor blade.
  • a method for manufacturing a composite part comprising: manufacturing a plurality of laminate layers of at least one fiber material and a matrix material; stacking the plurality of laminate layers atop each other to form a stacked laminate part; placing the stacked laminate part within a vacuum bag ; placing the vacuum bag on an adaptable tool; providing a partial vacuum within the vacuum bag around the stacked laminate part; modifying a shape of the stacked laminate part, via the adaptable tool, by allowing one or more of the plurality of laminate layers to slide with respect to each other under the partial vacuum; and applying a full vacuum to the modified shape of the stacked laminate part and heating the stacked laminate part to fuse the plurality of laminate layers together to manufacture the composite part.
  • a system of manufacturing a composite part of a rotor blade comprising: a plurality of laminate layers stacked atop each other to form a stacked laminate part, the plurality of laminate layers each comprising a fiber material and a matrix material; a vacuum unit for applying a partial vacuum and a full vacuum to the stacked laminate part; an adaptable tool for receiving the stacked laminate part, wherein the adaptable tool comprises a surface that changes shape, wherein the stacked laminate part changes shape when placed atop the adaptable tool and the surface of the adaptable tool changes shape by allowing one or more of the plurality of laminate layers to slide with respect to each other under partial vacuum; and a heating device configured to provide heat to the stacked laminate part to assist with modifying the shape of the stacked laminate part.

Landscapes

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

Abstract

L'invention concerne un procédé de fabrication d'une pièce composite. Le procédé comprend la fabrication d'une pluralité de couches stratifiées (100) par intégration d'un matériau fibreux (102) avec un matériau de matrice (104). Le procédé comprend également l'empilement de la pluralité de couches stratifiées (100) les unes sur les autres pour former une pièce stratifiée empilée (112). Le procédé comprend également l'application d'un vide partiel à la pièce stratifiée empilée (112). Le procédé comprend également la modification d'une forme de la pièce stratifiée empilée (112) en permettant à une ou plusieurs de la pluralité de couches stratifiées (100) de coulisser les unes par rapport aux autres sous le vide partiel. Le procédé comprend également l'application d'un vide complet à la forme modifiée de la pièce stratifiée empilée (112) et le chauffage de la pièce stratifiée empilée (112) pour fusionner la pluralité de couches stratifiées (100) ensemble afin de fabriquer la pièce composite.
EP23726184.7A 2023-05-03 2023-05-03 Systèmes et procédés de fabrication de pièces composites par empilement Pending EP4688405A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IB2023/054608 WO2024228041A1 (fr) 2023-05-03 2023-05-03 Systèmes et procédés de fabrication de pièces composites par empilement

Publications (1)

Publication Number Publication Date
EP4688405A1 true EP4688405A1 (fr) 2026-02-11

Family

ID=86558834

Family Applications (1)

Application Number Title Priority Date Filing Date
EP23726184.7A Pending EP4688405A1 (fr) 2023-05-03 2023-05-03 Systèmes et procédés de fabrication de pièces composites par empilement

Country Status (3)

Country Link
EP (1) EP4688405A1 (fr)
CN (1) CN121419878A (fr)
WO (1) WO2024228041A1 (fr)

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11001016B2 (en) * 2019-04-22 2021-05-11 Massachusetts Institute Of Technology Methods and apparatus for reconfigurable heated mold

Also Published As

Publication number Publication date
WO2024228041A1 (fr) 2024-11-07
CN121419878A (zh) 2026-01-27

Similar Documents

Publication Publication Date Title
US20220065217A1 (en) Methods for manufacturing wind turbine rotor blades and components thereof
EP3775533B1 (fr) Procédés de jonction de composants de pale de pales de rotor au moyen de structures de grille imprimées
US10830206B2 (en) Methods for manufacturing wind turbine rotor blades and components thereof
US10828843B2 (en) Shear webs for wind turbine rotor blades and methods for manufacturing same
CN113039358B (zh) 用于风力涡轮转子叶片构件的连结接口
CN111587178B (zh) 制造具有打印的网格结构的风力涡轮转子叶片面板的方法
CA3098688A1 (fr) Procedes de fabrication de pales de rotor d'eolienne et composants de celles-ci
EP3787871B1 (fr) Procédés de fabrication de pales de rotor d'éolienne et leurs composants
EP3713749B1 (fr) Composants de pale de rotor d'éolienne et leurs procédés de fabrication
WO2024228041A1 (fr) Systèmes et procédés de fabrication de pièces composites par empilement
EP3787887B1 (fr) Méthodes de fabrication de semelles de longeron pour pales de rotor d'éolienne
EP3787882A1 (fr) Procédés de fabrication de composants de pale de rotor pour une éolienne
US20240293992A1 (en) Methods for manufacturing shells with stiffening grid structures
EP3787872A1 (fr) Bandes de cisaillement pour pales de rotor d'éolienne et leurs procédés de fabrication
US20240181733A1 (en) Systems and methods for manufacturing rotor blades

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20251105

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC ME MK MT NL NO PL PT RO RS SE SI SK SM TR

RAP3 Party data changed (applicant data changed or rights of an application transferred)

Owner name: GE VERNOVA INFRASTRUCTURE TECHNOLOGY LLC