Method of Manufacturing a Wind Turbine Rotor Blade

Abstract

The present invention relates to a method of manufacturing a wind turbine rotor blade, to a wind turbine rotor blade obtainable by said method, to a pultrusion process for producing an elongated preform (97) for embedment in a wind turbine rotor blade and to an elongated preform (97) obtainable by said process. The blade manufacturing process involves a pultrusion process to obtain the preform (97), embedding the preform (97) within one or more parts of the blade, infusing a resin into said one or more blade parts containing the preform (97), and assembling the rotor blade including said one or more blade parts.

Claims

1. A method of manufacturing a wind turbine rotor blade, said method comprising the step of manufacturing an elongated preform (97) having a length of at least 1 meter and a constant cross section, wherein the preform (97) is manufactured using a pultrusion process comprising the steps of providing a fibre material such as fibre rovings (90), contacting the fibre material with a heated binding agent to form a pultrusion string (94), wherein the binding agent is present in an amount of 0.1-15 wt % relative to the weight of the fibre material, pulling the pultrusion string (94) through a die (93) having a predetermined cross section, and cutting the pultrusion string (94) to obtain the preform (97), wherein said method of manufacturing a wind turbine rotor blade further comprises the steps of embedding the preform (97) within one or more parts of the blade, infusing a resin into said one or more blade parts containing the preform (97), and assembling the rotor blade including said one or more blade parts.

2. A method according to claim 1, wherein said blade part is a shear web, preferably an I-shaped shear web, or a shell half.

3. A method according to claim 1, wherein the preform (97) has a length of at least 4 meters.

4. A method according to claim 1, wherein the die (93) and the resulting preform (97) have a triangular cross section.

5. A method according to claim 1, wherein the binding agent is a thermoplastic binding agent.

6. A method according to claim 1, wherein the binding agent is present in an amount of 1-6 wt % relative to the weight of the fibre material.

7. A method according to claim 1, wherein the binding agent is different from the resin used for infusing said one or more blade parts.

8. A method according to claim 1, wherein the preform (97) has an elastic modulus (Young's modulus) of between 0.01 and 10 GPa, preferably between 0.01 and 5 GPa.

9. A method according to claim 1, wherein the binding agent comprises a polyester, preferably a bisphenolic polyester.

10. A method according to claim 1, wherein the pultrusion string (94) comprises a first region and a second region, wherein the first region contains a higher amount of binding agent than the second region relative to the weight of the fibre material.

11. A method according to claim 10, wherein in the first region the binding agent is present at in an amount of 5-15 wt %, and wherein in the second region the binding agent is present at in an amount of 0.1-4 wt % relative to the weight of the fibre material.

12. A method according to claim 1, wherein the preform (97) has a lower stiffness prior to the step of infusing a resin into said one or more blade parts as compared to after completion of said step.

13. A wind turbine rotor blade obtainable by the method of claim 1.

14. A pultrusion process for producing an elongated preform (97) for embedment in a wind turbine rotor blade, the preform (97) having a constant cross section and a length of at least 1 meter, the pultrusion process comprising the steps of contacting a fibre material with a heated binding agent to form a pultrusion string (94), wherein the binding agent is present in an amount of 0.1-15 wt % relative to the weight of the fibre material, pulling the pultrusion string (94) through a die (93) having a predetermined cross section, cutting the pultrusion string (94) to obtain the elongated preform (97).

15. An elongated preform (97) obtainable by the method of claim 14, the preform (97) having a constant cross section and a length of at least 1 meter.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0063] The invention is explained in detail below with reference to embodiments shown in the drawings, in which

[0064] FIG. 1 shows a wind turbine,

[0065] FIG. 2 shows a schematic view of a wind turbine blade,

[0066] FIG. 3 shows a schematic view of an airfoil profile through section I-I of FIG. 4,

[0067] FIG. 4 shows a schematic view of the wind turbine blade, seen from above and from the side,

[0068] FIG. 5 is a schematic view of a pultrusion system for manufacturing an elongated preform according to the present invention,

[0069] FIG. 6 is a perspective drawing of a preform according to the present invention,

[0070] FIG. 7 shows different embodiments of possible cross sections of the die and the resulting preform according to the present invention, and

[0071] FIG. 8 illustrates a possible use of the preform in a shear web mould as part of a blade manufacturing process.

DETAILED DESCRIPTION

[0072] FIG. 1 illustrates a conventional modern upwind wind turbine according to the so-called Danish concept with a tower 4, a nacelle 6 and a rotor with a substantially horizontal rotor shaft. 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. The rotor has a radius denoted R.

[0073] FIG. 2 shows a schematic view of a first embodiment of a wind turbine blade 10 according to the invention. The wind turbine blade 10 has the shape of a conventional wind turbine blade 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, and a trailing edge 20 facing the opposite direction of the leading edge 18.

[0074] 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.

[0075] 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.

[0076] 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.

[0077] FIGS. 3 and 4 depict parameters which are used to explain the geometry of the wind turbine blade according to the invention.

[0078] FIG. 3 shows a schematic view of an airfoil profile 50 of a typical blade of a wind turbine depicted with the various parameters, which are typically used to define the geometrical shape of an airfoil. The airfoil profile 50 has a pressure side 52 and a suction side 54, which during usei.e. during rotation of the rotornormally face towards the windward (or upwind) side and the leeward (or downwind) side, respectively. The airfoil 50 has a chord 60 with a chord length c extending between a leading edge 56 and a trailing edge 58 of the blade. The airfoil 50 has a thickness t, which is defined as the distance between the pressure side 52 and the suction side 54. The thickness t of the airfoil varies along the chord 60. The deviation from a symmetrical profile is given by a camber line 62, which is a median line through the airfoil profile 50. The median line can be found by drawing inscribed circles from the leading edge 56 to the trailing edge 58. The median line follows the centres of these inscribed circles and the deviation or distance from the chord 60 is called the camber f. The asymmetry can also be defined by use of parameters called the upper camber (or suction side camber) and lower camber (or pressure side camber), which are defined as the distances from the chord 60 and the suction side 54 and pressure side 52, respectively.

[0079] Airfoil profiles are often characterised by the following parameters: the chord length c, the maximum camber f, the position d.sub.f 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 d.sub.t 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 d.sub.p 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.

[0080] FIG. 4 shows other geometric parameters of the blade. The blade has a total blade length L. As shown in FIG. 3, the root end is located at position r=0, and the tip end located at r=L. The shoulder 40 of the blade is located at a position r=L.sub.w, and has a shoulder width W, which equals the chord length at the shoulder 40. The diameter of the root is defined as D. The curvature of the trailing edge of the blade in the transition region may be defined by two parameters, viz. a minimum outer curvature radius r.sub.o and a minimum inner curvature radius r.sub.i, which are defined as the minimum curvature radius of the trailing edge, seen from the outside (or behind the trailing edge), and the minimum curvature radius, seen from the inside (or in front of the trailing edge), respectively. Further, the blade is provided with a prebend, which is defined as y, which corresponds to the out of plane deflection from a pitch axis 22 of the blade.

[0081] FIG. 5 schematically illustrates a pultrusion process according to the present invention. A number of bands or rovings of fibre material 90 are drawn from a shelf 89 into a receiving and heating station 91. A binding agent is fed from a reservoir 92 into the receiving and heating station 91 to provide contact with the fibre material 90, wherein the binding agent is present in an amount of 0.1-15 wt % relative to the weight of the fibre material. The resulting pultrusion string 94 is passed through a shaping die 93 which, for example, has a cross section corresponding to one of those shown in FIG. 7. Alternatively, the binder could be added to the glass material prior to this process by the glass supplier.

[0082] The string may be extracted from the die by means of a pulling station 95. On the other side of the pulling station 95 a knife 96 cuts the string, whereby an elongated preform 97 is obtained. The elongated preform 97 is flexible and soft enough for it to be wound up on a roll or coil 98 for transport and later use.

[0083] FIG. 6 is a perspective drawing of the resulting preform 97, which may have the shape of a triangular prism.

[0084] FIG. 7 illustrates a number of cross sections of the shaping die and of the resulting preform. FIG. 7 a-d each show a triangular cross sections, the triangle being defined by different combinations of straight and curved sides. FIG. 7e is an example of more complex cross section that might be useful for stabilising blade parts or elements thereof between the two extending legs of the preform.

[0085] FIG. 8 illustrates a possible use of the preform in a blade manufacturing process. Here, An I-shaped shear web 65 (only shown in part) is moulded between a lower web mould part 64 and an upper web mould part 66. Fibre layers 67 and a core material 68 are arranged between the lower web mould parts 64, 66. The lower web mould part 64 is provided with a ledge 70, for defining an end section of the first side of the web foot flange and/or may be used for carrying the external web foot flange. Further, a first and a second preform 97a, 97b according to the present invention are arranged within the mould. The preforms may have a shape so as to provide a gradual transition from the web body to a web foot flange. A backing plate 72 is installed and subsequently a vacuum bag 74 is arranged on top of the two web mould parts 64, 66 and the backing plate 72. Resin is then injected and finally hardened or cured in order to form the shear web.

[0086] 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.

LIST OF REFERENCE NUMERALS

[0087] 2 wind turbine [0088] 4 tower [0089] 6 nacelle [0090] 8 hub [0091] 10 blade [0092] 14 blade tip [0093] 16 blade root [0094] 18 leading edge [0095] 20 trailing edge [0096] 22 pitch axis [0097] 30 root region [0098] 32 transition region [0099] 34 airfoil region [0100] 40 shoulder/position of maximum chord [0101] 50 airfoil profile [0102] 52 pressure side [0103] 54 suction side [0104] 56 leading edge [0105] 58 trailing edge [0106] 60 chord [0107] 62 camber line/median line [0108] 64 lower web mould part [0109] 65 shear web [0110] 66 upper web mould part [0111] 67 fibre material [0112] 68 core material [0113] 70 ledge [0114] 72 backing plate [0115] 74 vacuum bag [0116] 88 pultrusion system [0117] 89 shelf [0118] 90 bands of fibre material [0119] 91 receiving and heating station [0120] 92 agent reservoir [0121] 93 shaping die [0122] 94 pultrusion string [0123] 95 pulling station [0124] 96 knife [0125] 97 preform [0126] 98 coil [0127] c chord length [0128] d.sub.t position of maximum thickness [0129] d.sub.f position of maximum camber [0130] d.sub.p position of maximum pressure side camber [0131] f camber [0132] L blade length [0133] r local radius, radial distance from blade root [0134] t thickness [0135] y prepend