WIND TURBINE BLADE

Abstract

A method of manufacturing a wind turbine blade, comprising the steps of: placing one or more shell fibre layers on a mould surface of a blade mould, placing a plurality of separately provided preforms directly on the one or more shell fibre layers in a stacked arrangement, infusing and curing the stacked preform arrangement, the one or more shell fibre layers together via a resin in mould cavity of the blade mould to form a wind turbine blade part with a spar cap integrated in a shell part providing part of the aerodynamic shape of the wind turbine blade.

Claims

1. A method of manufacturing a wind turbine blade extending along a longitudinal direction from a blade root through a root region and an airfoil region to a tip region with the blade tip, the wind turbine blade having a profiled contour including a pressure side, a suction side and a chord line extending between a leading edge and a trailing edge, the wind turbine blade comprising a shell providing the aerodynamic shape of the wind turbine blade and a spar cap forming a load carrying structure of the wind turbine blade, the method comprising the steps of: providing a blade mould for a wind turbine blade part having a mould cavity with a mould surface, placing one or more shell fibre layers and optionally an exterior coat on the blade mould surface, placing a plurality of separately provided preforms directly on the one or more shell fibre layers in a stacked arrangement, wherein each preform comprises a mixture of fibre material and a binding agent, wherein the fibre material of each preform is at least partially joined together by means of the binding agent, infusing the stacked preform arrangement, the one or more shell fibre layers and the optional exterior coat with a resin in mould cavity of the blade mould, and curing the stacked preform arrangement, the one or more shell fibre layers and the optional exterior coat together via the resin to form a wind turbine blade part with a spar cap integrated in a shell part providing part of the aerodynamic shape of the wind turbine blade.

2. A method according to claim 1, wherein the stacked preform arrangement, the one or more shell fibre layers and the optional exterior coat are infused in a vacuum pressure environment, optionally in a vacuum-assisted resin transfer moulding process.

3. A method according to claim 1, wherein the stacked preform arrangement comprises at least 20 preforms, such as at least 50 preforms.

4. A method according to claim 1, wherein the stacked preform arrangement comprises: two or more preforms in the chordwise direction, and/or two or more preforms in the thickness direction, and/or two or more preforms in the spanwise direction.

5. A method according to claim 1, wherein the plurality of preforms are arranged in a staggered manner or offset manner in the stacked preform arrangement.

6. A method according to claim 1, wherein a core insert is placed directly on the exterior shell and adjacent to the stacked preform arrangement in a chordwise direction.

7. A method according to claim 6, wherein an end of the stacked preform arrangement facing the leading edge or the trailing edge of the wind turbine blade is bevelled and an end of the stacked preform arrangement facing the interior of the wind turbine blade defines an acute angle with the bevelled side, the method further comprises: placing a core insert with a bevelled side directly on the exterior shell and subsequently placing a plurality of preforms directly on the exterior shell in a stacked arrangement so that, after infusion, the bevelled side of the core insert and the bevelled side of the stacked preform arrangement form a scarf joint.

8. A method according to claim 6, wherein an end of the stacked preform arrangement facing the leading edge or the trailing edge of the wind turbine blade is bevelled and an end of the stacked preform arrangement facing the exterior of the wind turbine blade defines an acute angle with the bevelled side, the method further comprises: placing a plurality of preforms directly on the exterior shell in a stacked arrangement and subsequently placing a core insert with a bevelled side directly on the exterior shell so that, after infusion, the bevelled side of the core insert and the bevelled side of the stacked preform arrangement form a scarf joint.

9. A wind turbine blade with a profiled contour including a pressure side and a suction side with a thickness direction extending therebetween, and a leading edge and a trailing edge with a chord having a chordwise direction extending therebetween, the wind turbine blade extending in a spanwise direction between a root end and a tip end, the spar cap extending in the spanwise direction, the chordwise direction, and the thickness direction, the wind turbine blade comprising: an exterior shell providing the profiled contour of the wind turbine blade and comprising one or more shell fibre layers, and a spar cap being a sandwich-structured composite including one or more inner fibre layers and a core portion sandwiched between the one or more inner fibre layers and the exterior shell, the core portion comprising a plurality of separately provided preforms arranged in a stacked preform arrangement, wherein each preform comprises a mixture of fibre material and a binding agent, wherein the fibre material is at least partially joined together by means of the binding agent, wherein the plurality of preforms and the exterior shell are joined together by means of a resin.

10. A wind turbine blade according to claim 9, wherein the stacked preform arrangement comprises at least 20 preforms, such as at least 50 preforms.

11. A wind turbine blade according to claim 9, wherein at least two adjacent preforms in a layer of the stacked preform arrangement are joined by a joint, preferably a scarf joint or a butt joint.

12. A wind turbine blade according claim 9, wherein the core portion of the spar cap further comprises a core insert arranged directly on the exterior shell and adjacent to the stacked preform arrangement in a chordwise direction, wherein the core insert is of a different material than the preform arrangement.

13. A wind turbine blade according to claim 9, wherein an end of the stacked preform arrangement facing the leading edge or the trailing edge of the wind turbine blade is bevelled and an end of the stacked preform arrangement facing the interior of the wind turbine blade defines an acute angle with the bevelled side, wherein the bevelled side of the stacked preform arrangement and a bevelled side of the core insert form a scarf joint.

14. A wind turbine blade according to claim 9, wherein an end of the stacked preform arrangement facing the leading edge or the trailing edge of the wind turbine blade is bevelled and an end of the stacked preform arrangement facing the exterior of the wind turbine blade defines an acute angle with the bevelled side, wherein the bevelled side of the stacked preform arrangement and a bevelled side of the core insert form a scarf joint.

15. A wind turbine blade obtainable by a method according to claims 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0069] Embodiments of this disclosure will be described in more detail in the following with regard to the accompanying figures. The figures show one way of implementing the present invention and are not to be construed as being limiting to other possible embodiments falling within the scope of the attached claim set.

[0070] FIG. 1 is a schematic perspective view illustrating an exemplary wind turbine,

[0071] FIG. 2 is a schematic perspective view illustrating an exemplary wind turbine blade,

[0072] FIG. 3 is a schematic perspective view illustrating a step of laying up preforms in a blade shell mould,

[0073] FIGS. 4a-4c are schematic cross-sectional views of three different preforms,

[0074] FIGS. 5a-5d are schematic cross-sectional views of four different stacked preform arrangements,

[0075] FIG. 6 is a schematic cross-sectional view of a fifth stacked preform arrangement, and

[0076] FIGS. 7a-7b are schematic cross-sectional views of a first and a second spar cap configuration, respectively.

DETAILED DESCRIPTION OF THE INVENTION

[0077] FIG. 1 illustrates a conventional modern upwind wind turbine 2 according to the so-called “Danish concept” with a tower 4, a nacelle 6 and a rotor with a substantially horizontal rotor shaft which may include a tilt angle of a few degrees. The rotor includes a hub 8 and three blades 10 extending radially from the hub 8, each having a blade root 16 nearest the hub and a blade tip 14 furthest from the hub 8.

[0078] FIG. 2 shows a schematic view of an exemplary wind turbine blade 10. The wind turbine blade 10 has the shape of a conventional wind turbine blade with a root end 17 and a tip end 15 and comprises a root region 30 closest to the hub, a profiled or an airfoil region 34 furthest away from the hub and a transition region 32 between the root region 30 and the airfoil region 34. The blade 10 comprises a leading edge 18 facing the direction of rotation of the blade 10, when the blade is mounted on the hub 8, and a trailing edge 20 facing the opposite direction of the leading edge 18.

[0079] 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 region 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.

[0080] 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.

[0081] 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.

[0082] The wind turbine blade 10 comprises a blade shell comprising two blade shell parts or half shells, a first blade shell part 24 and a second blade shell part 26, typically made of fibre-reinforced polymer. The wind turbine blade 10 may comprise additional shell parts, such as a third shell part and/or a fourth shell part. The first blade shell part 24 is typically a pressure side or upwind blade shell part. The second blade shell part 26 is typically a suction side or downwind blade shell part. The first blade shell part 24 and the second blade shell part 26 are fastened together with adhesive, such as glue, along bond lines or glue joints extending along the trailing edge 20 and the leading edge 18 of the blade 10. Typically, the root ends of the blade shell parts 24, 26 have a semi-circular or semi-oval outer cross-sectional shape. The blade shell parts 24, 26 define the aerodynamic shape of the wind turbine blade but require a spar cap to have the load carrying structure to support the weight of the wind turbine blade.

[0083] In the following, embodiments of a method for manufacturing such a wind turbine blade is disclosed. A blade mould 91 for a wind turbine blade part is provided as shown in FIG. 3. The blade mould 91 extends between a tip end 94 and a root end 93 and has a mould cavity 92 with a mould surface (not shown). An exterior gel coat is provided on the mould surface and is covered by several shell glass fibre layers 95 which will form the exterior shell of the wind turbine blade. The load-bearing capability will be provided by a spar cap which comprises a core portion. The core portion is formed by lowering a plurality of separately provided preforms 60 directly on the shell fibre layers 95 in several stacked layers from a bottom layer through a number of intermediate layers to a top layer to a stacked preform arrangement. The core portion of the spar cap 50 further comprises core inserts 70, 71 of balsa wood which are arranged adjacent to both sides of the plurality of preforms 60. Then, the core inserts 70, 71 and the preform arrangement 51 forming the core portion of the spar cap 50 are covered by one or more inner glass fibre layers and infused and cured to arrive at the spar cap 50 integrated with the exterior shell fibre layers as shown in FIGS. 7a-7b. These steps are disclosed in greater detail below.

[0084] FIGS. 4a-4c show different shaped preforms 60a, 60b, 60c having a top face 65, a bottom face 66 opposite of the top face 65, a first side face 67, and a second side face 68 opposite of the first side face 67. Each preform 60 comprises a mixture of carbon fibres (not shown) and a wax-like binding agent (not shown) comprising a bisphenolic polyester present in an amount 0.5-5 wt % relative to the weight of the carbon fibres. The carbon fibres of each preform 60 are joined together by means of the binding agent. The preforms 60 thus act like a “soft” solid with a stiffness between uncured fibre sheets and pultrusions, i.e. increased shape retention relative to uncured carbon fibre sheets while also allowing plastic deformation without breaking in contrast to pultrusions. The preforms 60 are arranged in the same orientation in the figures, i.e. the chordwise direction is along the left-right direction across the paper and the thickness direction T is in the up-down direction as shown in FIG. 4a. For instance, a first preform 60a is a preform plank with a rectangular cross-section as shown in FIG. 4a. A second preform 60b has a truncated pyramid cross-section while a third preform 60c has an upside-down truncated pyramid cross-section, so that a bottom face 66 of the second preform 60b has a greater chordwise extent than a bottom face 66 of the third preform 60b. The thickness T.sub.preform of the preforms may be in about 5 mm while the width W.sub.preform of the preforms may be in the range of 160 mm-800 mm. The preforms 60a, 60b, 60c can be stacked in a preform arrangement that has desirable properties as will be described in the following. The shape of the preforms is chosen depending on the desired shape of the stacked preform arrangement.

[0085] FIGS. 5-6 show five different stacked preform arrangements 51a, 51b, 51c, 51d, 51e. Generally, the preform arrangements 51a, 51b, 51c, 51d, 51e have a top side 52 for facing the interior of the wind turbine blade 10, a bottom side 53 for facing the exterior of the wind turbine blade 10, a leading edge end 54 for facing the leading edge 18 of the wind turbine blade 10, and a trailing edge end 55 for facing the trailing edge 20 of the wind turbine blade 10. The preform arrangements 51a, 51b, 51c, 51d, 51e comprise a plurality of preforms 60 arranged in a plurality of layers 56, 57, 58 stacked on top of each other in the thickness direction T including a bottom layer 56, a top layer 58, and a number of intermediate layers 57. For instance, the first, second, third, and fourth preform arrangements 51a, 51b, 51c, 51d all comprise two intermediate layers 57 while the fifth preform arrangement comprises five intermediate layers 57. Each layer 56, 57, 58 comprises a number of preforms 60 arranged side-by-side and joined at chordwise joints 61. The first four preform arrangements 51a, 51b, 51c, 51d are shown in their curved shape post-infusion in which the top side 52 and bottom side 53 are curved and conform to the shape of the mould surface of the blade mould, while the top side and bottom side 52, 53 are substantially straight prior to infusion and curing. The fifth preform arrangement 51e is shown in the pre-infusion state with a straight bottom side 53.

[0086] The cross-section of the first and second preform arrangements 51a, 51b is shaped as a truncated pyramid wherein the leading edge end 54 and the trailing edge end 55 are straight and tapering, the top side 52 and the bottom side 53 are curved, and the top side 52 has a greater extent in the chordwise direction C relative to the bottom side 53.

[0087] The cross-section of the third and fourth preform arrangements 51c, 51d is shaped as an irregular concave hexagon wherein the trailing edge end 55 and the leading edge end 54 are shaped as > and < respectively to reduce stress concentrations, and the top side 52 and bottom side 53 are curved in the chordwise direction C and have substantially the same extent in the chordwise direction C.

[0088] In this particular embodiment, the first and third preform arrangements 51a, 51c comprise between four to six preforms positioned side-by-side in each layer 58, 57, 56 and joined at chordwise joints 61. In other embodiments, the number of preforms in each layer may be more or less. The preforms include differently shaped preforms, in particular rectangular preforms as shown in FIG. 4a and rectangular preforms with a tapering first side face 67 or a tapering second side face 68. The preforms may have been provided with these different shapes or rectangular preforms may be machined after stacking to achieve the desired shape. The preforms 60 are arranged in a staggered or offset manner so that the chordwise joints 61 of adjacent layers are offset and do not coincide.

[0089] The second and fourth preform arrangements 51b, 51d comprise a single preform 60 in each layer 58, 57, 56 extending along the full chordwise width of the preform arrangement 51b, 51d. The fifth preform arrangement 51e has an optimised cross-sectional shape to provide desired mechanical properties for a specific wind turbine blade 10 as illustrated in FIG. 6. Such an optimised shape can be provided using this method. In this particular embodiment, the shape provided by arranging various shaped preforms 60 in seven layers including five intermediate layers 57 and a top layer 58 and a bottom layer 56. Each layer 56, 57, 58 comprises between one to three preforms 60.

[0090] In order to save costs, the core portion of the spar cap 50 comprises both core inserts 70, 71 and the preform arrangement 51. When using a preform arrangement 51 shaped as the preform arrangements of FIG. 5a or 5b, the preform arrangement 51 is placed directly on shell fibre layers 95 and inserted between a first core insert 70 and a second core insert 71. The sides of the core inserts facing the preform arrangement 51 have a corresponding tapering shape so that the preform arrangement 51 form a scarf joint to the core inserts 70, 71 as shown in FIG. 7a.

[0091] Due to the increased drapability of preforms relative to traditional pultrusions, it is possible to use a preform arrangement 51 shaped as the preform arrangements of FIG. 5c or 5d with the more rigid core inserts 70, 71 having correspondingly shaped sides without risking pockets filled with resin in the cured spar cap as shown in FIG. 7b.

[0092] Once the preform arrangement 51 and core inserts 70, 71 are placed on the shell fibre layers 95 with a satisfactorily configured joint, they are covered by several layers of inner glass fibre sheets 96. The preform arrangement 51, the shell fibre layers 95, the inner fibre layers 96, and the exterior gelcoat (not shown) are then infused with a resin in the mould cavity under vacuum pressure of less than one atmosphere in a vacuum-assisted resin transfer moulding process. During the moulding process, the preforms 60 of the preform arrangement 51 are deformed to conform to the shape of the mould surface 92 due to the vacuum pressure and thus, any pockets that would end up being filled with resin in the cured spar cap 50 are eliminated. The preform arrangement 51, the shell fibre layers 95, the inner fibre layers 96, and the exterior gelcoat (not shown) are then cured together via the resin to form one of the first or second blade shell parts 24, 26 as best seen in FIG. 2 with the integrated spar cap 50. The process is then repeated for the other one of the first blade shell part 24 or second blade shell part 26. The two blade shell parts 24, 26 are then joined along the leading edge 18 and the trailing edge 20 to form the wind turbine blade 10.

LIST OF REFERENCES

[0093] 2 wind turbine

[0094] 4 tower

[0095] 6 nacelle

[0096] 8 hub

[0097] 10 blade

[0098] 14 blade tip

[0099] 15 tip end

[0100] 16 blade root

[0101] 17 root end

[0102] 18 leading edge

[0103] 20 trailing edge

[0104] 24 pressure side

[0105] 26 suction side

[0106] 30 root region

[0107] 32 transition region

[0108] 34 airfoil region

[0109] 40 shoulder

[0110] 50 spar cap

[0111] 51 preform arrangement

[0112] 51a first preform arrangement

[0113] 51b second preform arrangement

[0114] 51c third preform arrangement

[0115] 51d fourth preform arrangement

[0116] 51e fifth preform arrangement

[0117] 52 top side

[0118] 53 bottom side

[0119] 54 leading edge end

[0120] 55 trailing edge end

[0121] 56 bottom layer

[0122] 57 intermediate layer

[0123] 58 top layer

[0124] 60 preform

[0125] 60a first preform

[0126] 60b second preform

[0127] 60c third preform

[0128] 61 chordwise joint

[0129] 65 top face

[0130] 66 bottom face

[0131] 67 first side face

[0132] 68 second side face

[0133] 70 first core insert

[0134] 71 second core insert

[0135] 91 blade mould

[0136] 92 mould surface

[0137] 93 root end

[0138] 94 tip end

[0139] 95 shell fibre layer

[0140] 96 inner fibre layer

[0141] C chordwise direction

[0142] L longitudinal direction

[0143] T thickness direction

[0144] T.sub.preform preform thickness

[0145] W.sub.preform preform width