US20070243387A1 - Dual cure resin composite system and method of manufacturing the same - Google Patents

Dual cure resin composite system and method of manufacturing the same Download PDF

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Publication number
US20070243387A1
US20070243387A1 US11/403,674 US40367406A US2007243387A1 US 20070243387 A1 US20070243387 A1 US 20070243387A1 US 40367406 A US40367406 A US 40367406A US 2007243387 A1 US2007243387 A1 US 2007243387A1
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Prior art keywords
layer
curing
functional group
resin
source
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Abandoned
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US11/403,674
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English (en)
Inventor
Wendy Lin
Wenliang Yang
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General Electric Co
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Individual
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Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LIN, WENDY WEN-LING, YANG, WENLIANG PATRICK
Priority to US11/403,674 priority Critical patent/US20070243387A1/en
Application filed by Individual filed Critical Individual
Priority to ES07105592T priority patent/ES2431663T3/es
Priority to DK07105592T priority patent/DK1845126T3/da
Priority to EP20070105592 priority patent/EP1845126B1/en
Priority to BRPI0701379-5A priority patent/BRPI0701379B1/pt
Priority to MX2007004389A priority patent/MX2007004389A/es
Priority to CN2007101097998A priority patent/CN101100120B/zh
Publication of US20070243387A1 publication Critical patent/US20070243387A1/en
Assigned to CITIBANK, N.A., AS COLLATERAL AGENT reassignment CITIBANK, N.A., AS COLLATERAL AGENT SECURITY AGREEMENT Assignors: SABIC INNOVATIVE PLASTICS IP B.V.
Assigned to SABIC INNOVATIVE PLASTICS IP B.V. reassignment SABIC INNOVATIVE PLASTICS IP B.V. RELEASE BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: CITIBANK, N.A.
Priority to US12/828,316 priority patent/US9556315B2/en
Abandoned legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
    • C08J5/12—Bonding of a preformed macromolecular material to the same or other solid material such as metal, glass, leather, e.g. using adhesives
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24058—Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31536—Including interfacial reaction product of adjacent layers

Definitions

  • the invention relates generally to fabrication techniques and, more particularly, composite fabrication techniques and associated polymer composite-based products.
  • Structural composite products such as wind turbine blades and aircraft structures, are composed of multiple layers.
  • the conventional approach for curing these multiple layers involves curing all of the layers together at the same time in an autoclave or oven. In other words, the process involves applying the layers one over the other, and then subsequently curing all of the layers.
  • the adhesion between layers is generally good but other disadvantages sometimes make this approach not practical. For instance, in manufacturing the root section of a wind turbine blades, sagging and dimensional distortion and fiber wrinkling during compaction may occur during curing cycle. Also, excessive reaction exotherm from thick parts may cause problems.
  • Another approach for curing these multiple layers involves sequentially applying and completely curing layers one after another using a single curing mechanism.
  • a first composite layer is cured completely before laying down a second composite layer.
  • the second composite layer is then cured completely before laying down a third composite layer.
  • the process adds additional composite layers in the same sequential manner using the single curing mechanism.
  • this fabrication technique creates relatively weak secondary adhesive bonds between the composite layers. These secondary adhesive bonds result in undesirably low interlaminar strength.
  • a method in accordance with one aspect of the invention, includes activating a first functional group of a resin in a first layer in response to a first curing source. The method further includes sequentially activating a second functional group of the resin in the first layer and the second functional group of the resin in a second layer disposed on the first layer in response to a second curing source. The method further includes creating a first covalent bond across an interface of the first layer and the second layer.
  • a method in accordance with another aspect of the invention, includes providing a first layer comprising a resin having a first functional group and a second functional group. The method also includes applying a first curing source to activate the first functional group and partially cure the first layer. The method further includes applying a second layer comprising the resin having the first and the second functional group onto the first layer. A second curing source is then applied to fully cure the first layer and partially cure the second layer simultaneously by activating the second functional group in the first and second layer.
  • a system in accordance with another aspect of the invention, includes a dual cure composite structure having a first layer with a material having a first and a second functional group.
  • the system also includes a second layer with the material having the first and the second functional group.
  • the system further includes a third layer with the material having the first and the second functional group.
  • the system also includes a first covalent bond across an interface of the first and the second layer.
  • a second covalent bond across another interface of the second and the third layer is also included in the system.
  • the method can be extended beyond the three layer system described here by alternatively activating the first and second functional groups sequentially of the subsequently disposing layers and creating alternating covalent bonds on alternating interfaces.
  • a method including partially curing a first composite layer with a first curing feature is included.
  • the method also includes disposing a second composite layer along the first composite layer.
  • the method further includes simultaneously curing the first and second composite layers with a second curing feature to further cure the first composite layer and to partially cure the second composite layer, wherein the first and second curing features are different from one another.
  • a manufacturing system having one or more curing sources configured to fully or partially cure a layer of a composite structure is included.
  • the system also includes a machine configured to dispose a layer of a dual cure composite structure.
  • FIG. 1 is a cross-sectional view of a dual cure composite structure comprising a resin and illustrating cured layers of a resin with dual functional groups in accordance with embodiments of the present invention
  • FIG. 2 is a flow chart illustrating exemplary steps for a method of curing a dual cure composite structure illustrating a dual cure mechanism in accordance with certain embodiments of the present invention
  • FIG. 3 is a flow chart illustrating exemplary steps for a method of manufacturing a dual cure composite structure comprising layers of resin with dual functional groups in accordance with certain embodiments of the present invention
  • FIG. 4 is a flow chart illustrating exemplary steps for a method of manufacturing a composite structure with a dual cure mechanism in accordance with certain embodiments of the present invention
  • FIG. 5 is a block diagram of a manufacturing system used in a dual curing mechanism in a composite structure in accordance with certain embodiments of the present invention
  • FIG. 6 is a diagrammatical illustration of an exemplary embodiment of the dual cure composite structure used in a wind turbine system comprising blades in accordance with embodiments of the present invention.
  • FIG. 7 is a diagrammatical illustration of the blades in the wind turbine system, such as illustrated in FIG. 6 , in accordance with certain embodiments of the present invention.
  • a dual cure composite structure used herein is defined as a composite structure having multiple layers, wherein the composite structure is manufactured using a “dual cure” mechanism to bond the multiple layers.
  • “Dual cure” mechanism is a mechanism in which initially, a first layer is partially cured by a first curing feature followed by a second layer being disposed on top of the first layer. In a next step, the second layer is partially cured and the first layer is at least further or fully cured simultaneously by a second curing feature.
  • the “dual cure” mechanism may be supplemented with one or more additional curing features, making the mechanism a generally “multi cure” mechanism.
  • the foregoing dual cure scenario may be supplemented by further applying a third layer on top of the second layer, and then partially curing the third layer and further or entirely curing the second layer simultaneously by a third curing feature.
  • the first layer also may be further or entirely cured by the third curing feature simultaneous with the curing of the second and third layers.
  • a fourth, fifth, sixth, or additional layers may be successively applied over the composite structure, and successively cured in stages of partial, and eventually complete curing via two or more curing features (e.g., the first, second, or more curing features).
  • the curing features generally alternate (e.g., feature 1 , 2 , 1 , 2 , etc.) as each successive layer is applied and simultaneously partially cured along with a previous layer.
  • the disclosed “dual cure” or “multi cure” mechanism may be described as “overlapping stages of curing” or “staged curing” or “step curing” of adjacent layers to create covalent bonds across interface of the layers and hence improve the interlayer adhesion.
  • Rapid curing systems are desirable for large composite structures to obtain the desired manufacturing cycle time, reduce significant plant and equipment investment, and further decrease base cost of a part.
  • This requires integration of appropriate resin chemistry with a corresponding curing source.
  • Curing source is a source used in curing layers of a composite structure.
  • Non-limiting examples of a curing source are ultraviolet frequency radiation, or microwave frequency radiation, or radio frequency, or visible frequency radiation, or ultrasonic, or laser, or electron beam or a combination thereof.
  • FIG. 1 is a cross-sectional view of a dual cure composite structure 10 including a first layer 12 , a second layer 14 and a third layer 16 of a resin or another material in accordance with embodiments of the present invention.
  • resin includes a resin or a resin blend.
  • the composite structure 10 may include two or more layers of a resin. In alternative embodiments, the composite structure 10 may include two or more layers of another type of material.
  • the first layer 12 includes a first functional group 18 and a second functional group 20 .
  • the “functional group” is defined as an atom or a group of atoms in an organic compound that provides the compound with some of its characteristics which make it respond to a specific curing mechanism.
  • Some non-limiting examples of functional groups include aldehydes, amines, hydroxyl, acrylate, methacrylate, vinyl, cyclo-epoxide, glycidyl etherepoxide with amine curatives, urethane, thiol-ene reactive group or a combination thereof.
  • Some non-limiting examples of resins comprising these functional groups are unsaturated polyesters, vinyl esters, melamines, urea-formaledehydes, phenolics, methacrylates, acrylates, epoxies, urethanes, etc.
  • a second layer 14 of the resin including the first functional group 18 and the second functional group 20 is disposed on the first layer 12 .
  • a third layer 16 of the resin including the first 18 and the second 20 functional groups is disposed on the second layer 14 of the resin.
  • the first 12 and the second 14 layers are bonded by a covalent bond formed at an interface 22 of the two layers.
  • the second 14 and the third 16 layers are bonded by a covalent bond at an interface 24 of the two layers.
  • the composite structure 10 includes carbon, fiberglass, basalt fiber, and polymer fiber (such as polyethylene and polyimide) composites.
  • UV First Functional Group Acrylate + photoinitiator Curing Source 1 UV light thermal Second Functional Group Amine + epoxy Curing Source 2 Microwave or Infrared Ex. 2 UV First Functional Group Acrylate + photoinitiator Curing Source 1 UV light thermal Second Functional Group isocyanate + alcohol Curing Source 2 Microwave or Infrared Ex. 3 EB First Functional Group Epoxy + cationic catalyst Curing Source 1 EB thermal Second Functional Group isocyanate + alcohol Curing Source 2 Microwave or Infrared Ex. 4 EB First Functional Group Acrylate Curing Source 1 EB thermal Second Functional Group Amine + epoxy Curing Source 2 Microwave or Infrared Ex.
  • Table 1 illustrates applying a curing source 1 (UV) source to initiate photo curing of the first functional group (acrylate) and applying curing source 2 (infrared) to thermally cure the second functional groups (epoxy with amine) according to the embodiment described in FIG. 1 .
  • UV curing source 1
  • infrared curing source 2
  • FIG. 2 illustrates a method 30 of curing a dual composite structure 10 in accordance with certain embodiments of the present invention.
  • the method 30 includes activating a first functional group of a resin in a first layer in response to a first curing source at step 32 .
  • the method 30 further includes activating a second functional group of the first layer and the second functional group of a second layer disposed on top of the first layer in response to a second curing source at step 34 .
  • the first layer may be fully cured.
  • the layers may include additional functional groups, such that the full curing of the layers may occur over three or more stages of curing with three or more curing sources.
  • the illustrated embodiment includes two curing sources, such that each successive layer is generally completely cured in two stages.
  • activation of the second functional group 20 of the second layer 14 results in partial curing of the second layer 14 .
  • the method 30 further includes activating a first functional group of a third layer and the first functional group of the second layer in response to the first curing source at step 38 .
  • the method 30 further includes activating the second functional group of the third layer in response to the second curing source at step 42 .
  • Simultaneous curing of two layers results in a stronger adhesive bonding than that formed via a single curing mechanism. This results in stronger interlaminar shear strengths and eliminates interlaminar property degradation.
  • FIG. 3 illustrates an exemplary method 50 of manufacturing a dual cure composite structure 10 as referenced to in FIG. 1 comprising a first 12 , a second 14 and a third 16 layer of resin in accordance with certain embodiments of the present invention.
  • the first 12 , the second 14 and the third 16 layers further include a first 18 and a second 20 functional group as referenced in FIG. 1 .
  • the method 50 includes providing a first layer comprising a resin having a first functional group and a second functional group as step 52 .
  • the method 50 further includes applying a first curing source to partially cure the first layer at step 54 .
  • the term ‘partial curing’ refers to curing less than about 100% of a layer of a composite structure.
  • partial curing may be about 10, 20, 30, 40, 50, 60, 70, 80, or 90 percent, or some percentage between these values. In an exemplary embodiment, the partial curing may be between about 30-70 percent, or between 40-60 percent, or about 50 percent. However, the degree of partial curing may vary depending on the particular materials, curing source, layer thickness, and so forth.
  • the method 50 includes providing a second layer comprising the resin having the first and the second functional group onto the first layer as step 56 .
  • the method 50 includes applying a second curing source to fully cure the first layer and partially cure the second layer simultaneously as step 58 .
  • the third layer 16 may further be introduced by providing a third layer comprising the resin having the first and the second functional group onto the second layer as step 60 .
  • Simultaneous curing of the second 14 and the third 16 layers occur by applying the first curing source to fully cure the second layer and partially cure the third layer simultaneously as step 62 .
  • Full curing of the third layer 16 occurs by applying the second curing source to fully cure the third layer as step 64 .
  • FIG. 4 illustrates a method 66 of manufacturing and curing a dual cure composite structure 10 as referenced to in FIG. 1 including a first 12 and a second 14 layer in accordance with certain embodiments of the present invention.
  • the method 66 includes partially curing a first composite layer with a first curing feature as step 68 .
  • a second composite layer 14 is introduced by disposing a second composite layer along the first composite layer as step 70 .
  • the method 66 further includes simultaneously curing the first and second composite layers with a second curing feature to further cure the first composite layer and to partially cure the second composite layer, wherein the first and second curing features are different from one another as step 72 .
  • the first and second curing features include different curing mechanisms, or the same curing mechanism having different output characteristics, or a combination of both. For example, several curing mechanisms and characteristics are described in further detail below.
  • FIG. 5 is an illustrated embodiment of a manufacturing system 76 used in a dual curing process of a dual cure composite structure 10 as referenced in FIG. 1 .
  • the manufacturing system 76 comprises one or more curing sources 78 configured to simultaneously cure a first layer 80 and a second layer 82 of the dual cure composite structure 10 .
  • the manufacturing system 76 further includes a machine 84 configured to dispose the second layer 82 on top of the first layer 80 .
  • the machine 84 includes a machine that can be operated manually, or an automated machine, or a combination thereof.
  • the machine 84 may include a flat press, a roll press, hydraulics, springs, pneumatics, gear mechanisms, or other compressive mechanisms to force the layers toward one another.
  • a non-limiting example of an automated machine includes an automated fiber and tape placement head and compaction roller.
  • the one or more curing sources 78 include an ultraviolet frequency radiation source, or a microwave frequency radiation source, or a radio frequency radiation source, or a visible frequency radiation source, or an ultrasonic radiation source, or an infrared, or a laser, or an electron beam or a combination thereof.
  • the one or more curing source 78 may include different curing types or different characteristics of the same curing type.
  • the one or more curing sources may include a single or two curing sources of the same type but emitting radiation (e.g., ultra-violet radiation) at different wavelengths, or frequencies.
  • the one or more curing sources may include two different types such as one curing source with ultra-violet radiation and a different curing source with microwave radiation, or one curing source with electron beam and one curing source with infrared radiation, or one curing source with microwave and one curing source with electron beam, or one curing source with UV-A and one curing source with UV-B, or once curing source with one microwave frequency C and one curing source with another microwave frequency.
  • Joining and assembling of piece-parts and subcomponents into monolithic structures is particularly advantageous and useful for modular design.
  • adhesive bonds generally provide for lower weight designs and a desirable strength.
  • the disclosed dual curing mechanism provides a desirable strength and potential for adhesive bonds in composite structures comprising resins as described in previous paragraphs.
  • Composite structures including resins may be used as materials in mechanical components for desirable adhesive bonding during joining and assembling of mechanical components.
  • FIG. 6 is a diagrammatical illustration of an exemplary embodiment of a dual composite structure 10 as referenced to in FIG. 1 , illustrating a wind turbine system 90 in accordance with embodiments of the present invention.
  • Some of the characteristics that make composites, such as carbon and fiberglass composites, suitable for wind turbine blades are desirable mechanical properties, tailorability of material properties, and versatility of fabrication methods.
  • the carbon and fiberglass composites provide desirable toughness and shorter process cycle time than that known in existing manufacturing processes.
  • the wind turbine system 90 includes a plurality of blades 92 (e.g., three blades).
  • the blades 92 enable the system 90 to capture energy from the wind. Specifically, the wind forces the blades 92 to rotate about an axis, thereby driving an electrical generator disposed within the system 90 .
  • the blades 92 of the wind turbine system 90 have a typical length of about 70 meters to maximize capture of energy and reduce cost of energy. Components of the blade 92 may comprise the dual cure composite structure 10 as discussed below.
  • the blades 92 are coupled to a tower 94 .
  • the height of the tower which determines height of the wind turbine system 90 , plays a significant part in design of the wind turbine system 90 . Due to change in velocity of wind with altitude, also known as wind shear, an optimum height is desirable for optimum performance of the wind turbine system 90 .
  • height of the tower 94 is about two to three times length of the blades 92 for an optimal performance.
  • FIG. 7 illustrates a modular design of a blade 92 as referenced in FIG. 6 of a wind turbine system 90 in accordance with certain embodiments of the present invention.
  • the illustrated blade 92 includes a top skin 96 and a shear web 98 disposed between a pair of spar caps 100 that are coupled to a barrel 102 .
  • the shear web 98 provides desirable strength to the blade 92 and also provides desirable support to the pair of spar caps 100 .
  • the blade 92 further includes a bottom skin 104 disposed below the shear web 98 .
  • the pair of spar caps 100 is made of a dual cure composite 10 , such as a carbon and a fiberglass composite. Since the blade 92 is a significant component of the wind turbine blade system 90 as referenced to in FIG.
  • top skin 96 and the bottom skin 104 may comprise the dual cure composite structure 10 .

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  • Chemical & Material Sciences (AREA)
  • Medicinal Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Polymers & Plastics (AREA)
  • Organic Chemistry (AREA)
  • Laminated Bodies (AREA)
  • Moulding By Coating Moulds (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Wind Motors (AREA)
  • Heating, Cooling, Or Curing Plastics Or The Like In General (AREA)
US11/403,674 2006-04-13 2006-04-13 Dual cure resin composite system and method of manufacturing the same Abandoned US20070243387A1 (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US11/403,674 US20070243387A1 (en) 2006-04-13 2006-04-13 Dual cure resin composite system and method of manufacturing the same
ES07105592T ES2431663T3 (es) 2006-04-13 2007-04-04 Sistema de material compuesto de resina de doble curado y procedimiento de fabricación del mismo
DK07105592T DK1845126T3 (da) 2006-04-13 2007-04-04 Dobbelt-hærdende resinkompositsystem og fremgangsmåde til at fremstille dette
EP20070105592 EP1845126B1 (en) 2006-04-13 2007-04-04 Dual cure resin composite system and method of manufacturing the same
BRPI0701379-5A BRPI0701379B1 (pt) 2006-04-13 2007-04-10 Method for curing a composite structure
MX2007004389A MX2007004389A (es) 2006-04-13 2007-04-12 Sistema de material mixto de resina de curado doble y metodo para fabricacion del mismo.
CN2007101097998A CN101100120B (zh) 2006-04-13 2007-04-13 双固化树脂复合体系及其制造方法
US12/828,316 US9556315B2 (en) 2006-04-13 2010-07-01 Dual cure resin composite system and method of manufacturing the same

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US11/403,674 US20070243387A1 (en) 2006-04-13 2006-04-13 Dual cure resin composite system and method of manufacturing the same

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US12/828,316 Expired - Fee Related US9556315B2 (en) 2006-04-13 2010-07-01 Dual cure resin composite system and method of manufacturing the same

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EP (1) EP1845126B1 (da)
CN (1) CN101100120B (da)
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DK (1) DK1845126T3 (da)
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MX (1) MX2007004389A (da)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090155084A1 (en) * 2007-12-13 2009-06-18 General Electric Company Wind blade joint bonding grid
US20120031649A1 (en) * 2010-04-22 2012-02-09 Endicott Interconnect Technologies, Inc. Coreless layer buildup structure with lga and joining layer
US20120160547A1 (en) * 2010-04-22 2012-06-28 Endicott Interconnect Technologies, Inc. Coreless layer buildup structure
US20120160544A1 (en) * 2010-04-22 2012-06-28 Endicott Interconnect Technologies, Inc. Coreless layer buildup structure with lga
US20120247822A1 (en) * 2011-03-28 2012-10-04 Endicott Interconnect Technologies, Inc. Coreless layer laminated chip carrier having system in package structure
US8360732B2 (en) 2011-05-25 2013-01-29 General Electric Company Rotor blade section and method for assembling a rotor blade for a wind turbine
US20140106148A1 (en) * 2011-06-16 2014-04-17 Evonik Roehm Gmbh Process for continuous inline production of coated polymeric substrates or laminates
US8876483B2 (en) 2010-01-14 2014-11-04 Neptco, Inc. Wind turbine rotor blade components and methods of making same
US20160046813A1 (en) * 2013-11-06 2016-02-18 Sekisui Chemical Co., Ltd. Method for manufacturing cured film, method for manufacturing electronic component, and electronic component
US9297357B2 (en) 2013-04-04 2016-03-29 General Electric Company Blade insert for a wind turbine rotor blade
US9506452B2 (en) 2013-08-28 2016-11-29 General Electric Company Method for installing a shear web insert within a segmented rotor blade assembly
US10137542B2 (en) 2010-01-14 2018-11-27 Senvion Gmbh Wind turbine rotor blade components and machine for making same

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070066698A1 (en) 2005-09-20 2007-03-22 Yang Wenliang P Dual cure compositions, methods of curing thereof and articles therefrom
CN101830096A (zh) * 2010-05-14 2010-09-15 上海飞域实验室设备有限公司 复合型环氧树脂台面板的制造方法
US20120138223A1 (en) 2011-09-29 2012-06-07 General Electric Company Uv-ir combination curing system and method of use for wind blade manufacture and repair
US10357960B2 (en) * 2015-10-30 2019-07-23 Nike, Inc. Three-dimensional curing of a two-dimensionally printed object
CN110561874A (zh) * 2019-09-19 2019-12-13 常州市天润木业有限公司 一种新型暖软表面板的制备工艺

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4265723A (en) * 1979-07-06 1981-05-05 Basf Aktiengesellschaft Photocurable molding, impregnating and coating compositions
US20030078316A1 (en) * 2001-08-28 2003-04-24 Bradford Christopher J. Dual cure coating composition and processes for using the same
US7390559B2 (en) * 2004-10-22 2008-06-24 Ppg Industries Ohio, Inc. Multilayer coating system

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3574040A (en) * 1967-06-29 1971-04-06 Gen Dynamics Corp Apparatus for making laminated structural shapes by the controlled detrusive placement and polymerization of tectonic filamentous tapes
JPS5752052A (en) * 1980-09-12 1982-03-27 Fujitsu Ltd Heat treatment of photosensitive resin
US4642321A (en) * 1985-07-19 1987-02-10 Kollmorgen Technologies Corporation Heat activatable adhesive for wire scribed circuits
US6432236B1 (en) * 1991-03-01 2002-08-13 Foster-Miller, Inc. Ultrasonic method of fabricating a thermosetting matrix fiber-reinforced composite structure and the product thereof
FR2765346B1 (fr) * 1997-06-26 1999-09-24 Alsthom Cge Alcatel Procede de fabrication d'un conducteur optique
US6038464A (en) * 1998-02-09 2000-03-14 Axelgaard Manufacturing Co., Ltd. Medical electrode
US6709717B2 (en) * 1998-06-09 2004-03-23 Margrace Enterprises, Inc. Method for making polymer surfaced composites
US6652943B2 (en) * 2001-06-04 2003-11-25 Saint-Gobain Performance Plastics Corporation Multilayer polymeric article with intercrosslinked polymer layers and method of making same
DE10201420A1 (de) 2002-01-15 2003-07-24 Basf Ag Strahlungshärtbare Beschichtungen mit verbesserter Haftung
DE10248324A1 (de) * 2002-10-17 2004-05-06 Basf Coatings Ag Thermisch und mit aktinischer Strahlung härtbarer Beschichtungsstoff und Verfahren zum Beschichten miktoporöser Oberflächen
EP1645607A1 (en) * 2004-10-05 2006-04-12 Kun-Chung Liu Method for preparing a logo label

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4265723A (en) * 1979-07-06 1981-05-05 Basf Aktiengesellschaft Photocurable molding, impregnating and coating compositions
US20030078316A1 (en) * 2001-08-28 2003-04-24 Bradford Christopher J. Dual cure coating composition and processes for using the same
US7390559B2 (en) * 2004-10-22 2008-06-24 Ppg Industries Ohio, Inc. Multilayer coating system

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8221085B2 (en) * 2007-12-13 2012-07-17 General Electric Company Wind blade joint bonding grid
US20090155084A1 (en) * 2007-12-13 2009-06-18 General Electric Company Wind blade joint bonding grid
US9429140B2 (en) 2010-01-14 2016-08-30 Senvion Gmbh Wind turbine rotor blade components and methods of making same
US8876483B2 (en) 2010-01-14 2014-11-04 Neptco, Inc. Wind turbine rotor blade components and methods of making same
US10137542B2 (en) 2010-01-14 2018-11-27 Senvion Gmbh Wind turbine rotor blade components and machine for making same
US9945355B2 (en) 2010-01-14 2018-04-17 Senvion Gmbh Wind turbine rotor blade components and methods of making same
US9394882B2 (en) 2010-01-14 2016-07-19 Senvion Gmbh Wind turbine rotor blade components and methods of making same
US8541687B2 (en) * 2010-04-22 2013-09-24 Endicott Interconnect Technologies, Inc. Coreless layer buildup structure
US20120031649A1 (en) * 2010-04-22 2012-02-09 Endicott Interconnect Technologies, Inc. Coreless layer buildup structure with lga and joining layer
US20120160547A1 (en) * 2010-04-22 2012-06-28 Endicott Interconnect Technologies, Inc. Coreless layer buildup structure
US8536459B2 (en) * 2010-04-22 2013-09-17 Endicott Interconnect Technologies, Inc. Coreless layer buildup structure with LGA
US20120160544A1 (en) * 2010-04-22 2012-06-28 Endicott Interconnect Technologies, Inc. Coreless layer buildup structure with lga
US9351408B2 (en) * 2010-04-22 2016-05-24 I3 Electronics, Inc. Coreless layer buildup structure with LGA and joining layer
US20120247822A1 (en) * 2011-03-28 2012-10-04 Endicott Interconnect Technologies, Inc. Coreless layer laminated chip carrier having system in package structure
US8360732B2 (en) 2011-05-25 2013-01-29 General Electric Company Rotor blade section and method for assembling a rotor blade for a wind turbine
US9630387B2 (en) * 2011-06-16 2017-04-25 Evonik Roehm Gmbh Process for continuous inline production of coated polymeric substrates or laminates
US20140106148A1 (en) * 2011-06-16 2014-04-17 Evonik Roehm Gmbh Process for continuous inline production of coated polymeric substrates or laminates
US9297357B2 (en) 2013-04-04 2016-03-29 General Electric Company Blade insert for a wind turbine rotor blade
US9506452B2 (en) 2013-08-28 2016-11-29 General Electric Company Method for installing a shear web insert within a segmented rotor blade assembly
US20160046813A1 (en) * 2013-11-06 2016-02-18 Sekisui Chemical Co., Ltd. Method for manufacturing cured film, method for manufacturing electronic component, and electronic component
US11220604B2 (en) * 2013-11-06 2022-01-11 Sekisui Chemical Co., Ltd. Method for manufacturing cured film, method for manufacturing electronic component, and electronic component
US20220098419A1 (en) * 2013-11-06 2022-03-31 Sekisui Chemical Co., Ltd. Method for manufacturing cured film, method for manufacturing electronic component, and electronic component
US12077677B2 (en) * 2013-11-06 2024-09-03 Sekisui Chemical Co., Ltd. Method for manufacturing cured film, method for manufacturing electronic component, and electronic component

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CN101100120A (zh) 2008-01-09
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US9556315B2 (en) 2017-01-31
BRPI0701379A (pt) 2007-12-11
BRPI0701379B1 (pt) 2018-01-30
EP1845126B1 (en) 2013-08-14
EP1845126A3 (en) 2009-05-20
ES2431663T3 (es) 2013-11-27
CN101100120B (zh) 2013-10-23
US20100272574A1 (en) 2010-10-28
MX2007004389A (es) 2009-02-16

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