Patent Application
20250114985
The present invention relates to a method of manufacturing an embedding element for embedment in a shell structure of a wind turbine rotor blade and to an embedding element obtainable by said method. The present invention also relates to a wind turbine rotor blade comprising a plurality of said embedding elements, and to methods of manufacturing said blade.
In view of climate change and an increasingly unsustainable fossil fuel use, wind proves to be a cost-effective, clean and renewable source of energy. Wind turbines usually comprise a tower, generator, gearbox, nacelle, and one or more rotor blades. Wind turbine blades capture kinetic energy of wind using known airfoil principles. Modern wind turbines may have rotor blades that exceed 100 meters in length.
Wind turbine blades are typically made from a fibre-reinforced polymer material and comprise a pressure side shell half and a suction side shell half. The cross-sectional profile of a typical blade includes an airfoil for creating an air flow leading to a pressure difference between both sides. The resulting lift force generates torque for producing electricity.
The shell halves of wind turbine blades are usually manufactured using moulds. First, a blade gel coat or primer is applied to the mould. Subsequently, fibre reinforcement and/or fabrics are placed into the mould followed by resin infusion. Vacuum is then typically used to draw epoxy resin material into a mould. Alternatively, prepreg technology can be used in which a fibre or fabric pre-impregnated with resin forms a homogenous material which can be introduced into the mould. Several other moulding techniques are known for manufacturing wind turbine blades, including compression moulding and resin transfer moulding. The shell halves are assembled by being glued or bolted together substantially along a chord plane of the blade. The root region of each shell half typically has a circular cross section.
The connection between the blade and a hub of a wind turbine must be able to transfer heavy dynamic forces. The circular end face of a rotor blade root is usually fastened to a circular metal flange on the turbine hub by means of bolts or threaded rods. A typical root region of a blade comprises layers of fibres forming an outer layer and an inner layer in between which fastening members in the form of bushings are placed. Separately formed stiff inserts or embedding elements may be placed in between each pair of adjacent bushings, whereby the bushings are mutually separated by the stiff inserts. Known inserts are made of glass fibres embedded in a suitable stiffening resin.
Typically, the connection and transfer of loads from the blade to the hub is provided by mounting the blade to the hub by screwing bolts into the bushings placed in the root or by means of nuts screwed onto stud bolts screwed into the bushings. In case the number of bolts and thereby the number of bushings has to be increased to handle a given load, the remaining area of the fibre composite material between the bushings is reduced. This may result in the root connection being insufficiently supported to withstand the loads, whereby the connection between the blade root and the hub may fail since the bushings are insufficiently retained in the composite material and thus pulled out of the composite material of the root region. This is especially a problem when long and thereby heavy blades are to be used.
To this end, WO 2012/140039 provides a solution wherein bushings are laminated into a composite structure reinforced with metal fibres, such as steel fibres. The bushings are separated by rigid inserts or embedding elements comprising a wedge-shaped part and an opposing end substantially corresponding to the region between the lateral faces of adjacent bushings. The rigid inserts are manufactured from layers of metal fibres and a second type of fibres, the layers being embedded in a suitable resin such as polyester, epoxy or vinyl ester.
WO 2017/121710 A1 discloses an embedding element comprising a wedge-shaped part which tapers in the direction towards one end portion, the embedding element comprising a fibre material and a binding agent, wherein the fibre material is at least partially joined together by means of the binding agent. The embedding element can be manufactured in a pultrusion process, drawing glass fibre rovings into a heating station, contacting the fibre material with a heated binding agent, and passing the resulting material through an adequately shaped nozzle to form a pultrusion string.
For these known embedding elements it is typically necessary to machine the full surface of the embedding element, for achieving a satisfactory adhesion between the resin and the embedding element in the root end of the blade. This often results in waste production from machine dust of 15-30% of the total mass of the embedding element.
Another possible concern is the formation of wrinkles in the shell fibre material, in particular along the tapered wedge-shaped part of the embedding elements. This is undesirable, because such wrinkles tend to form structurally weak zones, sometimes leading to necessary repair or even failure.
Overall, there is an interest in further improving the strength of existing root end arrangements, in particular with respect to the pull-out strength of the bushings fastened in between the respective embedding elements. The root bushing strength is the main driver for the root diameter of a wind turbine blade. By making a stronger bushing connection the root diameter can potentially be reduced.
It is therefore an object of the present invention to provide an embedding element that overcomes the above-described drawbacks.
It is another object of the present invention to provide a method of manufacturing an embedding element which reduces waste.
In particular, it is an object of the present invention to provide an embedding element which has an improved strength and leads to an improved pull-out resistance of bushings at the root end of the blade.
The present inventors have found that one or more of these objects are achieved in a surprisingly efficient solution by providing a method of manufacturing an embedding element for embedment in a shell structure of a wind turbine rotor blade, the method comprising the steps of
It was found that this method is not only more cost-efficient, resulting in a 15-30% waste reduction as compared to known methods which rely on machining of the part, but that this method surprisingly also results in considerable structural improvement, in particular providing considerably stronger connections to bushings at the root end of the blade. Furthermore, a reduction of wrinkle formation at the root end of the blade is observed. In the method of the present invention, essentially no machining is required after the part is released from the mould. Another advantage is that the resulting embodiment is not too rigid part, i.e. being a comparatively soft and flexible element that can easily be arranged within the root end of the blade.
The pull-out strength of interjacent bushings at the blade insert, i.e. bushings separated by adjacent embedding elements, was tested in a piston test. In this experimental setup, a slice of the root end arrangement is produced by cutting the arrangement along a plane normal to the longitudinal blade axis, the thickness of the slice being 10 mm. The load applied to the bushing for effecting displacement (pull-out) from the surrounding fibre composite is recorded. Using this approach it was found that the embedding elements obtainable by the method of the present invention convey an increased pull-out resistance of interjacent bushings which is about 30% higher as compared to known embedding elements produced in a pultrusion process.
The embedding element is preferably an elongate embedding element. The length of the embedding element may be at least 50 cm. In a preferred embodiment, the embedding element has a first end portion and a second end portion, wherein the embedding element comprises a wedge-shaped part which tapers in the direction towards the second end portion. In some embodiments, the wedge-shaped part extends over at least 30% In a preferred embodiment, at least the first end portion of the embedding element comprises a butterfly-shaped cross section.
The embedding element comprises a fibre material and a binding agent, wherein preferably the fibre material is at least partially joined together by means of the binding agent, and wherein preferably the binding agent is present in an amount of 0.1-15 wt % relative to the weight of the fibre material.
Such embedding elements are typically embedded together with fastening members, such as bushings, in the root region of a blade shell structure in between an outer shell part or an outer skin and an inner shell part or an inner skin. Usually, one embedding element is placed between each pair of adjacent bushings, such that the adjacent embedding elements and bushings follow the circumference of the root region cross section. Thereby, the lateral face of each embedding element engages a lateral face of an adjacent bushing. For manufacturing the root end of the blade, subsequently, a resin material is infused in between the outer shell part and the inner shell part for fixing the embedding elements and bushings within the shell structure.
Preferably, the embedding element has a first part comprising lateral faces which are substantially complementary to the lateral faces of the adjacent fastening members, such as bushings, so as to substantially abut the latter. In other words, when the fastening members have a cylindrical shape, the outer lateral surfaces of the first element part may advantageously have a concave shape complimentary to the cylindrical shape of the lateral faces of the fastening members. The wedge-shaped part of the embedding element part may provide a gradual transition between a relatively high wall thickness in the region of the fastening members and a normally lower wall thickness in the transition region and the airfoil region of the blade.
The lower mould plate, which is preferably an elongate mould plate, comprises a first lateral side, such as a first lateral edge, an opposing second lateral side, such as an opposing second lateral edge, and a top surface extending between the first and second lateral sides. Typically, it will further comprise a front side or front edge, a rear edge or rear side, and a bottom surface on the opposite side of the top surface. In some embodiments, the lateral sides take the form of lateral edges. In some embodiments, the lower mould plate may be part of a 3-dimensional structure, such as a U-shaped mould or a box structure. Thus the lateral side may also be constituted by a side surface or transverse plane going upward or downward, or may take the form of an arched surface or a side wall.
A first movable core member and a second movable core member are arranged on the top surface of the lower mould plate, optionally with a film or foil or similar protective layer therebetween. In a preferred embodiment, each of the movable core members are elongate core members, preferably with a length of at least 50 cm, such as at least 100 cm. In some embodiments, the movable core members have a length which is equal to, or exceeds, the length of the embedding element. In a preferred embodiment, the movable core member have a length which is at least twice the length of the embedding element.
In a preferred embodiment, each core member is provided with a longitudinally extending lateral surface for engaging the fibre material, at least part of the lateral surface extending convexly in a cross-sectional view perpendicular to the longitudinal axis of the core member, and wherein the respective lateral surfaces face each other when the first movable core member and a second movable core member are arranged on the top surface of the lower mould plate. Thus, it is preferred that at least part of the respective lateral surfaces of the core members, which faces inward, i.e. towards the fibre material of the embedding element bulges outward, or is convex in a transverse cross section. Such convex surface can be used to compress and shape the fibre material into the butterfly cross section.
In some embodiments, each core member may have a middle segment, as seen in the longitudinal direction, with a substantially constant height, the middle segment being enclosed by two outer segments each of which have a height tapering towards the two respective ends of the core member. A convex, or outward protruding lateral surface preferably extends throughout the middle segments and along part of the two outer segments. Similarly, the upper mould plate may comprise a middle segment and two outer segments at either side of the middle segment, wherein the outer segments are inclined downward relative to the middle segment. A wedge-shaped section of the embedding element or a preform thereof can be advantageously provided in this way. In some embodiments, the core member is produced by 3D printing.
Preferably, the core members are slidable core members, preferably slidable in a transverse direction i.e. perpendicular to the longitudinal axis of the core member. Thus, it is preferred that the core members are slidable between a first, retracted position with a first distance between the first and second core members, and a second position with a second distance between the first and second core members, the second distance being less than the first distance. This advantageously enables the fibre material such as fibre rovings to be arranged in the mould cavity when the core members are in the first position, and subsequently the compression and forming of the fibre material and binding agent into the desired shape.
The moving, preferably sliding, of one or both of the core members can be achieved by suitable engagement members, such as one or more screws, bolts, wrenches, or pneumatic cylinders, for example arranged at the respective sides of the mould.
The first movable core member is closer to the first lateral side of the lower mould plate than the second movable core member, or closer to a left side of the mould, and the second movable core member is closer to the second lateral side of the lower mould plate than the first movable core member, or closer to the right side of the mould. Preferably, the longitudinal axes of the respective core members are aligned with, i.e. substantially parallel to, the longitudinal axis of the lower mould plate.
A fibre material and a binding agent are arranged on the lower mould plate, optionally on one or more base layers or foils arranged on the lower mould plate, in between the first movable core member and the second movable core member. In a preferred embodiment, the fibre material comprises glass fibre rovings, preferably texturized glass fibre rovings. Texturized roving can be obtained by processing strands of glass fibre through a high-pressure air jet. The high-pressure air jet curls and coils the strands to make them bulkier. Thus, preferably the glass fibre material is treated with a high-pressure air jet, such as with an air nozzle, prior to the arrangement in the moulding cavity. Preferably, continuous filaments of glass fibre are run through a turbulent stream of compressed air. Thus, the fibre material preferably comprises air jet texturized glass fibre rovings. In some embodiments, the fibre material comprises texturized rovings and non-texturized rovings.
In some embodiments, texturized rovings, bulky or entangled rovings are used as fibre material, including rovings that have been air jet entangled or bulked. In particular when using texturized glass fibre rovings in the method of the present invention, an improved pull-out resistance of interjacent fastening elements, such as bushings, at the root end of the blade is observed. Also, the resulting embedding elements lead to a significant reduction of resin pools at the root end of the blade. Upon resin infusion into the root end arrangement, the binding agent of the embedding element advantageously dissolves into the resin, where upon the texturized glass fibre rovings will expand as the binding agent that previously glued them together is dissolved by the resin. Thus, the fibre material will advantageously fill any cracks or holes surrounding the adjacent bushings.
In some embodiments, the fibre material consists of glass fibre rovings, preferably texturized glass fibre rovings. In a preferred embodiment, the binding agent is present in an amount of 0.1-15 wt % relative to the weight of the fibre material.
In a preferred embodiment, the binding agent is a thermoplastic binding agent. Typically, the fibre material is at least partially joined together by means of the binding agent by thermal bonding. In a preferred embodiment, the binding agent is a binding powder, such as a thermoplastic binding powder.
In a preferred embodiment, the binding agent is present in an amount of 0.5-10 wt %, preferably 0.5-5 wt %, more preferably 0.5-3.5 wt %, relative to the weight of the fibre material. The binding agent may also comprise two or more different substances, as long as the total binding agent is present in an amount of 0.1-15 wt % relative to the weight of the fibre material.
According to another embodiment, the melting point of the binding agent is between 40° and 220° C., preferably between 40 and 180° C., such as between 40 and 170° C., or between 40 and 160° C.
According to a preferred embodiment, the binding agent comprises a polyester, preferably a bisphenolic polyester. An example of such binding agent is a polyester marketed under the name NEOXIL 940. Examples include NEOXIL 940 PMX, NEOXIL 940 KS 1 and NEOXIL 940 HF 2B, all manufactured by DSM Composite Resins AG. Preferably, the binding agent is a polyester, preferably a bisphenolic polyester. In other embodiments, the binding agent is a hotmelt adhesive or based on a prepreg resin.
In a preferred embodiment, the method comprises unwinding glass fibre rovings from one or more bobbins, and arranging the glass fibre rovings on the mould plate, and wherein the glass fibre rovings are contacted with the binding agent prior to the unwinding step, or after the unwinding step but before the arranging step. In other embodiments, the binding agent is applied to the fibre material in the mould.
In a preferred embodiment, the step of arranging the fibre material on the top surface of the lower mould plate comprises arranging fibre rovings of different lengths, successively going from the longest to the shortest fibre rovings. In some embodiments the midpoint of all rovings substantially coincides with the midpoint of moulding cavity as seen in a longitudinal direction. Thus, preferably the thickness of the fibre arrangement is thickest at the center, and tapering towards each end of the preform of the embedding element.
An upper mould plate is placed on top of the first moveable core member and the second moveable core member to form a cavity between the upper and lower mould plates and the first and second moveable core members. Thus, the moulding cavity may be delimited by the first and second moveable core members and the upper and lower mould plates. In particular is preferred that the upper mould plate converges towards the lower mould plate at the two respective ends of the mould, such that a wedge-shaped structure is provided at either side of the mould. In some embodiments, the step of placing an upper mould plate on top of the first moveable core member and the second moveable core member further compresses the fibre material.
One or both of the core members are pushed towards the cavity, i.e. inwards, for compacting the fibre material. Pushing one or both of the core members towards the cavity will reduced the size of the cavity. Thus, the final shape of the moulding cavity is advantageously provided when one or both of the core members have reached a predetermined engagement position. In a preferred embodiment, the pushing step comprises pushing both of the core members towards the cavity for compacting the fibre material until both of the core members reach a final predetermined position.
The fibre material and the binding agent are then heated to form the embedding element or a preform thereof. A preform of the embedding element is particularly preferred a part which can be cut in half at its center along a transverse plane for providing two identically shaped embedding elements. In a preferred embodiment, one or both of the moveable core members comprises a heating element, such as a heat exchanger fluid recirculation system, for heating the fibre material and the binding agent. In other embodiments, heating can be present in the mould plates, or hot air can be passed through grooves in the core members or the mould plates. Preferably, the heating temperature is 100-150° C.
After heating for a sufficient time, the embedding element or the preform thereof is cooled down, preferably to around 40° C. or lower. Then, one or both of the core members can be retracted, and advantageously the upper mould plate is removed, for releasing the embedding element or the preform thereof. Is particularly preferred that a preform of the embedding element is manufactured by the method of the present invention, in particular a symmetrical preform. Such preform is advantageously cut in half in the transverse direction along its centreline to provide two identically shaped embedding elements with a shape as described above.
Thus, in a preferred embodiment, the step of cutting the preform comprises cutting the preform into half along a plane normal to the longitudinal axis of the preform to provide two embedding elements.
According to another aspect, the present invention relates to an embedding element for embedment in a shell structure of a wind turbine rotor blade, the embedding element being obtainable by the method of the present invention described above.
In a preferred embodiment, the embedding element has a first end portion and a second end portion, wherein the embedding element comprises a wedge-shaped part which tapers in the direction towards the second end portion.
In a preferred embodiment, the embedding element has an elastic modulus (Young's modulus) of between 0.01 and 110 GPa, preferably between 0.01 and 45 GPa.
According to another embodiment, the embedding element has an elastic modulus (Young's modulus) of 0.01-110 GPa, preferably 0.01-70 GPa, such as between 0.01-45 GPa or between 0.01-10 GPa. Embedding elements with such elasticity were found to be particularly well suited for a blade manufacturing process according to the present invention.
In a preferred embodiment, between its two end portions the embedding element is provided with a first longitudinal lateral face extending concavely in a cross-sectional view perpendicular to the longitudinal axis of the embedding element and provided with a second longitudinal lateral face facing opposite the first lateral face and extending concavely in a cross-sectional view perpendicular to the longitudinal axis of the embedding element.
According to another embodiment, the embedding element essentially consists of the fibre material and the binding agent. This means that the embedding element contains not more than 15 wt %, preferably not more than 5 wt %, of material other than fibre material and binding agent relative to the total weight of the embedding element. According to another embodiment, the embedding element consists of the fibre material and the binding agent.
According to another embodiment, the fibre material comprises glass fibres, carbon fibres or a combination. In another embodiment, the fibre material essentially consists of glass fibres. This means that the fibre material contains not more than 15 wt %, preferably not more than 5 wt %, of material other than glass fibres relative to the total weight of the fibre material. According to another embodiment, the fibre material consists of glass fibres.
According to a preferred embodiment, between its two end portions the embedding element is provided with a first longitudinal lateral face extending concavely in a cross-sectional view perpendicular to the longitudinal axis of the embedding element. In a particularly preferred embodiment, between its two end portions the embedding element is provided with a second longitudinal lateral face facing opposite the first lateral face and extending concavely in a cross-sectional view perpendicular to the longitudinal axis of the embedding element. Thus, the embedding element may comprise two longitudinally extending lateral faces on either side, both of which have a concave cross section for improved contact to adjacent cylindrical bushings.
In one aspect, the present invention relates to the use of the above-described embedding elements for manufacturing a wind turbine blade.
According to another aspect, the present invention relates to a wind turbine rotor blade including a shell structure of a fibre-reinforced composite material comprising fibres embedded in a polymer matrix, the blade comprising
In a preferred embodiment, a concave lateral face of each embedding element engages a convex lateral face of an adjacent fastening member.
In another aspect, the present invention relates to a method of manufacturing a wind turbine rotor blade including a shell structure of a fibre-reinforced composite material comprising fibres embedded in a polymer matrix, said method comprising the steps of
Preferably, the fastening members are bushings. The bushings usually have a circular cross section. Usually, the bushings are cylindrical. Typically, each bushing comprises an internal thread. In a preferred embodiment, a concave lateral face of each embedding element engages a convex lateral face of an adjacent fastening member.
The embedment of the fastening members, such as bushings, and embedding elements typically comprises the steps of securing the fastening members and/or embedding elements to the root flange of a mould part. The flange is usually a metal plate with apertures corresponding to the flange provided on the turbine hub. Fibre glass mats may be placed in between the elements to create small spacings which are subsequently infused with resin.
The resin for subsequent infusion of the shell structure may be a thermosetting resin, such as epoxy, vinyl ester or polyester, or a thermoplastic resin, such as nylon, PVC, ABS, polypropylene or polyethylene. However, the resin may comprise an in-situ polymerisable thermoplastic material. The in-situ polymerisable thermoplastic material may advantageously be selected from the group consisting of pre-polymers of: polybutylene terephthalate (PBT), polyamide-6 (pre-polymer is caprolactam), polyamide-12 (pre-polymer is laurolactam) alloys of polyamide-6 and polyamide-12; polyurethanes (TPU), polymethylmethacrylate (PMMA), polyethylene terephthalate (PET), polycarbonate (PC), polyetheretherketone (PEEK), polyetherketone (PEK), polyethersulfone (PES), polyphenylenesulphide (PPS), polyethylenenaphthalate (PEN) and polybutylenenaphthalate (PBN), cyclic poly(1,4-butylene terephthalate) (CBT) and/or combinations thereof.
In one embodiment, a concave lateral face of each embedding element engages a convex lateral face of an adjacent fastening member, preferably a bushing. Even more preferred, two opposite concave lateral faces on either side of each embedding element each engage a corresponding convex lateral face of an adjacent fastening member, such as a bushing.
In another embodiment, the resin infusion step comprises vacuum assisted resin transfer moulding. It was found that particularly in vacuum assisted transfer of resin into the shell structure, the present invention results in significant improvement as compared to known methods. The problem of unwanted wrinkle formation in the shell structure is in particular seen in vacuum assisted moulding, said problem being ameliorated by the embedding elements of the present invention. According to a preferred embodiment, the infusion resin dissolves the binding agent, preferably the thermoplastic binding agent, of the embedding element.
In another aspect, the present invention relates to a moulding system for manufacturing an embedding element for embedment in a shell structure of a wind turbine rotor blade, the embedding element having a first end portion and a second end portion, wherein the embedding element comprises a wedge-shaped part which tapers in the direction towards the second end portion, the moulding system comprising a lower mould plate comprising a first lateral side, an opposing second lateral side, and a top surface extending between the first and second lateral sides, a first movable core member and a second movable core member, an upper mould plate arrangeable on top of the first moveable core member and the second moveable core member to form a cavity between the upper and lower mould plates and the first and second moveable core members, and at least one heating device for heating fibre material and binding agent present in said cavity.
It will be understood that any of the above-described features may be combined in any embodiment of the inventive blade as described. In particular, any feature or embodiment described with respect to the method of manufacturing the embedding element may also apply to the embedding element, the wind turbine rotor blade, the method of manufacturing the wind turbine rotor blade and/or to the moulding system of the present invention, and vice versa.
As used herein, the term “longitudinal” is used to describe the direction along the main axis of an element, such as along the length axis of, for example, the embedding element. The term “transverse” refers to the direction that is perpendicular to the longitudinal axis.
As used herein, the term “elongate” refers to a component having a length which is greater than both its width and thickness, for example twice as great.
The term polymerisable thermoplastic material means that the material may be polymerised once at the manufacturing site.
As used herein, the term “wt %” means weight percent. The term “relative to the weight of the fibre material” means a percentage that is calculated by dividing the weight of an agent, such as a binding agent, by the weight of the fibre material. As an example, a value of 1 wt % relative to the weight of the fibre material corresponds to 10 g of binding agent per kilogram of fibre material.
The skilled reader will understand that the elastic modulus, also known as Young's modulus, defines the relationship between stress (force per unit area) and strain (proportional deformation) in a material. Thus, the elastic modulus is a measure of the stiffness of a material. The elastic modulus can be determined by the cantilever beam test, as is well known in the art.
The invention is explained in detail below with reference to embodiments shown in the drawings, in which
The airfoil region 34 (also called the profiled region) has an ideal or almost ideal blade shape with respect to generating lift, whereas the root region 30 due to structural considerations has a substantially circular or elliptical cross-section, which for instance makes it easier and safer to mount the blade 10 to the hub. The diameter (or the chord) of the root region 30 may be constant along the entire root area 30. The transition region 32 has a transitional profile gradually changing from the circular or elliptical shape of the root region 30 to the airfoil profile of the airfoil region 34. The chord length of the transition region 32 typically increases with increasing distance r from the hub. The airfoil region 34 has an airfoil profile with a chord extending between the leading edge 18 and the trailing edge 20 of the blade 10. The width of the chord decreases with increasing distance r from the hub.
A shoulder 40 of the blade 10 is defined as the position, where the blade 10 has its largest chord length. The shoulder 40 is typically provided at the boundary between the transition region 32 and the airfoil region 34.
It should be noted that the chords of different sections of the blade normally do not lie in a common plane, since the blade may be twisted and/or curved (i.e. pre-bent), thus providing the chord plane with a correspondingly twisted and/or curved course, this being most often the case in order to compensate for the local velocity of the blade being dependent on the radius from the hub.
Airfoil profiles are often characterised by the following parameters: the chord length c, the maximum camber f, the position df of the maximum camber f, the maximum airfoil thickness t, which is the largest diameter of the inscribed circles along the median camber line 62, the position de of the maximum thickness t, and a nose radius (not shown). These parameters are typically defined as ratios to the chord length c. Thus, a local relative blade thickness t/c is given as the ratio between the local maximum thickness t and the local chord length c. Further, the position dp of the maximum pressure side camber may be used as a design parameter, and of course also the position of the maximum suction side camber.
As seen in
As seen in
As seen in
A more detailed view of the embedding element 76 is shown in
Furthermore, the first part 84 of the embedding element 76 may extend from the first end 71 of the bushing 68 and beyond the second end 72 thereof. The second part 85 of the embedding element 76 is a wedge-shaped tapering extension of the first element part 84, which tapers in the direction towards the second end portion 79. The first part 84 may have an extent substantially corresponding to that of the bushings 68.
As best seen in the cross sectional view of
A fibre material 99 in the form of a plurality of fibre rovings and a binding agent are arranged on the top surface 96 of the lower mould plate 93 in between the first movable core member 97 and the second movable core member 98. The steps of the method of the present invention are illustrated in the cross-sectional views of
As seen in
The embedding element is subsequently cooled down, preferably to room temperature, whereupon the core member(s) can be retracted for releasing the embedding element or the preform thereof;
A perspective view of the resulting preform 90, after its removal from the mould, is shown in
The invention is not limited to the embodiments described herein, and may be modified or adapted without departing from the scope of the present invention.
2 wind turbine
4 tower
6 nacelle
8 hub
10 blade
14 blade tip
16 blade root
18 leading edge
20 trailing edge
22 pitch axis
30 root region
32 transition region
34 airfoil region
40 shoulder/position of maximum chord
50 airfoil profile
52 pressure side
54 suction side
56 leading edge
58 trailing edge
60 chord
62 camber line/median line
64 outer part of shell
66 inner part of shell
68 bushing
70 central bore
71 first end of bushing
72 second end of bushing
74 lateral face of bushing
76 embedding element
77 first end portion of embedding element
78 wedge-shaped extension of bushing
79 second end portion of embedding element
80 first end of extension of bushing
82 second end of extension of bushing
84 first part of embedding element
85 second part of embedding element
86 longitudinal lateral face of embedding element
87 longitudinal lateral face of embedding element
90 preform
91 cutting plane
92 moulding system
93 lower mould plate
94 first lateral side of lower mould plate
95 second lateral side of lower mould plate
96 top surface of lower mould plate
97 first movable core member
98 second movable core member
99 fibre material/fibre rovings
100 upper mould plate
101 side plate
102 cavity
103 lateral surface of first movable core member
104 lateral surface of second movable core member
105 front plate
106 back plate
107 middle segment of core member
108 first outer segment of core member
109 second outer segment of core member
c chord length
dt position of maximum thickness
df position of maximum camber
dp position of maximum pressure side camber
f camber
L blade length
r local radius, radial distance from blade root
t thickness
Δy prebend
| Number | Date | Country | Kind |
|---|---|---|---|
| 22151997.8 | Jan 2022 | EP | regional |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/EP2023/050847 | 1/16/2023 | WO |
