• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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    • 专利摘要:
    Modular rotor blades and method. the present disclosure relates to a modular rotor blade (16) for a wind turbine (10) and methods of assembling the same. the rotor blade (16) includes a blade root section (20), a blade tip section (22), at least one leading edge segment (24) having a forward thrust side surface (28) and a forward suction side surface (30), and at least one trailing edge segment (26) having an aft pressure side surface (32) and an aft suction side surface (34). additionally, the leading edge segment (24) and the trailing edge segment (26) are disposed between the blade root section (20) and the blade tip section (22) in a generally general direction in the sense of amplitude. furthermore, the leading edge segment (24) and the trailing edge segment (26) are joined at a lateral pressure joint (36) and a lateral suction joint (38).
    公开号:BR102016015144B1
    申请号:R102016015144-9
    申请日:2016-06-28
    公开日:2021-07-27
    发明作者:Christopher Daniel Caruso；Aaron A. Yarbrough；Daniel Alan Hynum；James Robert Tobin
    申请人:General Electric Company；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    [001] The present invention relates generally to wind turbine rotor blades and more particularly to modular wind turbine rotor blades and the methods of assembly thereof. BACKGROUND OF THE INVENTION
    [002] Wind power is considered one of the cleanest and most environmentally friendly energy sources available today and wind turbines have received more attention in this regard. A modern wind turbine typically includes a tower, a generator, a gearbox, a nacelle, and a rotor that has a rotatable hub with one or more rotor blades. Rotor blades capture kinetic energy from the wind using known airfoil principles. Rotor blades transmit kinetic energy in the form of rotational energy in order to rotate a shaft that couples the rotor blades to a gearbox or, if a gearbox is not used, directly to the generator. The generator then converts mechanical energy into electrical energy that can be distributed to a utility grid.
    [003] Rotor blades generally include a suction side shell and a pressure side shell typically formed using molding processes, which are connected together in connecting lines along the front edges and hindquarters of the blade. Additionally, pressure and suction casings are relatively lightweight and have structural properties (eg, stiffness, strength, and buckling resistance) that are not configured to resist bending moments and other loads exerted on the rotor blade during operation. Therefore, in order to improve the rigidity, strength and buckling resistance of the rotor blade, the body shell is typically reinforced with the use of one or more structural components (eg, opposing spar covers with a shear web configured therebetween) which engage the pressure and internal suction side surfaces of the shell halves. Stringer covers can be constructed from a variety of metals, including but not limited to fiberglass laminated composites and/or carbon fiber laminated composites.
    [004] Such rotor blades, however, are not without problems. For example, typical rotor blade bond lines are generally formed by applying a suitable bonding compound or paste along the bond line with a minimum designed bond width between the shell members. These tie lines are a critical blade design constraint as a significant number of turbine blade field failures occur in the tie line. Separating the lead line along the leading and/or trailing edges of an operating turbine blade can result in catastrophic failure and damage to the wind turbine.
    [005] In addition, the methods used to manufacture the rotor blades and/or their structural components can be difficult to control, prone to defects and/or highly labor-intensive due to the handling of dry screens and the challenges of infusing large laminated structures. In addition, rotor blades continue to increase in size, conventional manufacturing methods continue to increase in complexity as blade halves are typically manufactured using opposing mold halves which must be large enough to accommodate the entire length of the blade. rotor blade. As such, joining the large shovel halves can be highly laborious and more susceptible to defects.
    [006] A known strategy to reduce the costs and complexity associated with preforming, transporting and erecting wind turbines, which have rotor blades of increasing sizes, is to manufacture the rotor blades in blade segments. The blade segments can then be assembled to form the rotor blade. However, known joint designs for connecting blade segments together typically have a variety of disadvantages. For example, many known joint designs do not provide sufficient alignment of the blade segments. As such, a significant amount of time is wasted in aligning the blade segments for assembling the rotor blade. Additionally, many known joint designs include several complex interconnected components, thus increasing the amount of time required to assemble the blade segments. In addition, segmented blades are typically heavier than blades manufactured using conventional methods due to additional gaskets and/or related parts. Additionally, each of the segments is further manufactured using blade halves that are connected together at the front and rear edges, which as mentioned, is a critical design constraint.
    [007] Therefore, the technique continually seeks new and improved rotor blades and related methods that address the aforementioned issues. Accordingly, the present invention is directed to improved modular wind turbine rotor blades and methods of assembling them. DESCRIPTION OF THE INVENTION
    [008] The embodiments and advantages of the invention will be presented partially in the following description or may become apparent from the description, or may be learned by practicing the invention.
    [009] In another embodiment, the present invention is directed to a modular rotor blade for a wind turbine. The rotor blade includes a blade root section, a blade tip section, at least one leading edge segment that has a leading pressure side surface and a leading suction side surface, and at least one trailing edge segment that it has an aft pressure side surface and an aft suction side surface. Additionally, the leading edge segment and the trailing edge segment are disposed between the blade root section and the blade tip section in a generally broad direction. In addition, the leading edge segment and the trailing edge segment can be joined in a lateral pressure joint and a lateral suction joint.
    [010] In one embodiment, the rotor blade may also include at least one pressure side segment and at least one suction side segment. In another embodiment, the blade root section may include one or more spar caps that extend in one direction, generally in the breadth direction. Similarly, the blade tip section may include one or more corresponding spar caps that extend in one direction, generally in the breadth direction. Therefore, in certain embodiments, the blade root section and the blade tip section can be joined together via their respective spar cap(s). In further embodiments, the blade root section may additionally include one or more shear webs configured between the one or more spar caps.
    [011] In further embodiments, the rotor blade may include a plurality of leading edge segments and/or a plurality of trailing edge segments. In additional embodiments, the rotor blade may also include a structural member secured to the blade root section. Furthermore, in particular embodiments, the structural member can be configured with the trailing edge segment(s).
    [012] In certain embodiments, the leading edge segment(s) and the trailing edge segment(s) may be configured to overlap at the lateral pressure junction and the lateral suction junction. In addition, adjacent leading edge segments as well as adjacent trailing edge segment(s) can be configured to overlap. Therefore, in specific embodiments, the rotor blade may also include an adhesive configured between the overlapping trailing and leading edge segments and/or adjacent overlapping trailing or leading edge segments.
    [013] In yet another embodiment, the leading edge segment(s) and trailing edge segment(s) may be constructed from any suitable material that allows for the desired shape and characteristics of the component. corresponding. More specifically, in certain embodiments, the leading edge segment(s) and/or the trailing edge segment(s) may be constructed, at least in part, from a thermoset polymer, from a thermoplastic polymer or similar.
    [014] In yet another embodiment, the present invention is directed to a modular rotor blade for a wind turbine. The rotor blade includes a preformed blade root section having one or more continuous spar caps extending in a generally broad direction, a preformed blade tip, and at least one blade segment disposed between the blade root section and the blade tip section. In addition, the blade segment includes a chord direction cross section that defines a continuous, single blade surface.
    [015] In one embodiment, the continuous, single blade surface is unbonded. In another embodiment, the blade segment(s) includes a single gasket on a trailing edge thereof. In certain embodiments, the blade segment(s) may be constructed, at least in part, from either a thermoset polymer or a thermoplastic polymer.
    [016] In yet another embodiment, the present invention is directed to a modular rotor blade for a wind turbine. The rotor blade includes a pre-formed blade root section having one or more continuous spar caps that extend in a generally broad direction, a pre-formed blade tip section, and the head. minus one blade segment disposed between the blade root section and the blade tip section. Furthermore, the at least one blade segment includes a chord direction cross section having multiple joints, wherein at least one joint is situated on at least one of a pressure side surface or a suction side surface.
    [017] In one embodiment, the blade segment(s) may be constructed, at least in part, from at least one of a thermoset polymer, a thermoplastic polymer or the like. In another embodiment, the blade segment(s) may include at least one leading edge segment and at least one trailing edge segment joined at a lateral pressure joint and at a lateral suction joint. More specifically, in certain embodiments, the leading edge segment can include a forward pressure side surface and a front suction side surface and the trailing edge segment can include an aft pressure side surface and an aft suction side surface. . In additional embodiments, the leading edge and trailing edge segment(s) may overlap at the lateral pressure junction and the lateral suction junction. Therefore, in certain embodiments, the rotor blade may include an adhesive configured between the overlapping trailing and leading edge segments.
    [018] In further embodiments, the modular rotor blade may include at least one pressure side segment and at least one suction side segment, e.g., leading and trailing edges joined through suitable gaskets.
    [019] In another embodiment, the blade segment(s) may include at least one forward pressure side segment, at least one forward suction side segment, at least one aft pressure side segment, and at least one side segment of aft suction. In such an embodiment, the blade segment(s) is (are) generally segmented into four quadrants which can be joined together via four joints.
    [020] In still further embodiments, the blade segment(s) may include a generally J-shaped blade segment and at least one of an aft pressure side surface or a aft suction side surface, for example, joined together in multiple joints. In additional embodiments, the blade root section may also include one or more shear webs configured between the one or more continuous spar caps.
    [021] These and other functions, embodiments and advantages of the present invention will become better understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated into and constitute a part of this specification, illustrate embodiments of the invention and, together with a description, serve to explain the principles of the invention. BRIEF DESCRIPTION OF THE DRAWINGS
    [022] A complete and enabling description of the present invention, which includes the best way of it, intended for a person skilled in the art, is presented in the descriptive report, which makes reference to the attached Figures, in which: - Figure 1 illustrates a view in perspective of an embodiment of a wind turbine according to the present invention; Figure 2 illustrates a perspective view of an embodiment of a wind turbine, according to the present invention; Figure 3 illustrates an exploded view of the modular rotor blade of Figure 2; Figure 4 illustrates a cross-sectional view of an embodiment of a leading edge segment of a modular rotor blade according to the present invention; Figure 5 illustrates a cross-sectional view of an embodiment of a trailing edge segment of a modular rotor blade according to the present invention; Figure 6 illustrates a cross-sectional view of the modular rotor blade of Figure 2 according to the present invention taken along line 6-6; Figure 7 illustrates a cross-sectional view of the modular rotor blade of Figure 2 according to the present invention taken along line 7-7; Figure 8 illustrates a cross-sectional view of another embodiment of a modular rotor blade according to the present invention, which particularly illustrates a blade segment having overlapping pressure and suction side joints; Figure 9 illustrates a cross-sectional view of another embodiment of a modular rotor blade according to the present invention, which particularly illustrates a continuous blade segment without joint; Figure 10 illustrates a cross-sectional view of another embodiment of a modular rotor blade according to the present invention, which particularly illustrates a single-joint blade segment; Figure 11 illustrates a cross-sectional view of an embodiment of a modular rotor blade according to the present invention, which particularly illustrates a plurality of blade segments joined together by multiple joints; Figure 12 illustrates a cross-sectional view of another embodiment of a modular rotor blade according to the present invention, which particularly illustrates a plurality of blade segments joined together by multiple joints; Figure 13 illustrates a flowchart of a method for assembling a modular rotor blade in accordance with the present invention. Figures 14 to 17 illustrate several schematic diagrams of an embodiment of a method for assembling a modular rotor blade of a wind turbine according to the present invention, which particularly illustrate the assembly steps that can be completed in the factory; Figure 18 illustrates a perspective view of an embodiment of an accessory assembly used to assemble various rotor blade components of a wind turbine in accordance with the present invention; and Figure 19 illustrates a schematic diagram of an embodiment of a method for assembling a wind turbine rotor blade according to the present invention, which particularly illustrates the assembly steps that can be completed in the field, for example , on a wind turbine site. DESCRIPTION OF ACHIEVEMENTS OF THE INVENTION
    [023] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided as an explanation of the invention and not as a limitation of the invention. In fact, it will be evident to those skilled in the art that various modifications and realizations can be made to the present invention without departing from the scope of the invention. For example, features illustrated or described as part of one embodiment can be used with another embodiment to provide yet another embodiment. Therefore, the present invention is intended to encompass such modifications and embodiments as included within the scope of the appended claims and their equivalents.
    [024] In general, the present invention is directed to a modular rotor blade for a wind turbine and the assembly methods of the same. In certain embodiments, the rotor blade includes a pre-formed blade root section, a pre-formed blade tip section, and one or more blade segments mounted between the blade root section and the blade tip section. in one direction, generally in the sense of amplitude. In certain embodiments, the paddle segments may include one or more leading edge segments, trailing edge segments, pressure side segments, suction side segments, a front pressure side segment, a front suction side segment, a side segment of aft pressure, a side suction aft segment or a continuous paddle segment without joint. Additionally, the blade root section and the blade tip section each include one or more spar caps. Therefore, the blade root section and the blade tip section can be joined together via their respective spar caps.
    [025] The present invention provides many advantages that are not present in the prior art. For example, the present invention provides a modular rotor blade that has multiple blade segments and/or components that can each be individually preformed prior to blade assembly. Therefore, the blade segments reduce the number of tie lines and shift the tie lines in the opposite direction to the leading and/or trailing edge regions. Also, the number of chamfer joints or the like can be reduced. Additionally, modular rotor blades, as described herein, can increase supply chain options, can reduce assembly cycle time, and/or can reduce shipping cost. Therefore, the rotor blades and methods of the present invention provide an economical alternative to conventional rotor blades. Additionally, the rotor blades of the present invention can be of reduced weight.
    [026] Now, referring to the drawings, Figure 1 illustrates an embodiment of a wind turbine, according to the present invention; as shown, wind turbine 10 includes a tower 12 with a nacelle 14 mounted thereto. A plurality of rotor blades 16 are mounted on a rotor hub 18, which in turn is connected to a main flange that turns a main rotor shaft. The wind turbine power generation and control components are housed within nacelle 14. The view of Figure 1 is provided for illustrative purposes only in order to place the present invention in an exemplary field of use. It should be appreciated that the invention is not limited to any particular type of wind turbine configuration. Furthermore, the present invention is not limited to the use of wind turbines, however, it can be used in any application that has rotor blades.
    [027] Now with reference to Figures 2 and 3, several views of a modular rotor blade 16 manufactured in accordance with the present invention are illustrated. As shown, the rotor blade 16 includes a modular configuration having a preformed blade root section 20, a preformed blade tip section 22 disposed opposite the blade root section 20, and a plurality of blade segments. shovel arranged between them. Blade root section 20 is configured to be mounted or otherwise secured to rotor 18 (Figure 1). Additionally, as shown in Figure 2, rotor blade 16 defines an amplitude 23 which is equal to the total length between blade root section 20 and blade tip section 22. Also, as shown in Figures 2 and 6 , the rotor blade 16 defines a chord 25 which is equal to the total length between the leading edge 40 of the rotor blade 16 and the trailing edge 42 of the rotor blade 16. As is generally understood, the chord 25 may de generally, vary in length with respect to amplitude 23 as rotor blade 16 extends from blade root 20 to blade tip section 22.
    [028] Furthermore, as shown in the illustrated embodiment, the blade segments may include a plurality of leading edge segments 24 and a plurality of trailing edge segments 26 generally disposed between the blade root section 20 and the blade tip section 22 along a longitudinal axis 27 in a generally broad direction. Therefore, the leading and trailing edge segments 24 and 26 generally serve as the outer casing/cover of the rotor blade 16 and can define a substantially aerodynamic profile, such as by defining a symmetrical or shaped cross-section. of curved airfoil. In further embodiments, it is to be understood that the blade segment portion of the blade 16 may include any combination of the segments described herein and is not limited to the embodiment as shown.
    [029] Now with reference to Figure 4, each of the leading edge segments 24 has a front pressure side surface 28 and a front suction side surface 30. Similarly, as shown in Figure 5, each of the front pressure segments trailing edge 26 has an aft pressure side surface 32 and an aft suction side surface 34. In addition, as particularly shown in Figure 6, the leading edge segment(s) 26 and the segment(s) Trailing edge(s) 26 can be joined at a lateral pressure joint 36 and a lateral suction joint 38. Therefore, the front pressure lateral surface 28 of the leading edge segment 24 and the aft pressure lateral surface 32 of the trailing edge segment 26 generally define a pressing side surface of the rotor blade 16. Similarly, the front suction side surface 30 of the leading edge segment 24 and the aft suction side surface 34 of the trailing edge segment 26 generally define a suction side surface of the rotor blade 16.
    [030] In additional embodiments, as shown in Figure 8, the leading edge segment(s) 24 and the trailing edge segment(s) 26 can be configured to overlap at the lateral pressure joint 36 and/or at the suction side joint 38. In addition, as shown in Figure 2, the adjacent leading edge segments 24 as well as the adjacent trailing edge segments 26 can be configured to overlap at a joint 54. More specifically, in certain embodiments, the various segments of the rotor blade 16 can be additionally secured together, for example, via an adhesive 56 configured between the overlapping trailing and leading edge segments 24 and 26 and/or the trailing edge segments or earlier adjacent that overlap 24 and 26.
    [031] In addition, the lateral pressure joint 26 and/or the lateral suction joint 38 can be situated at any location in the proper chord direction. For example, as shown in Figures 6 and 8, the joints 36 and 38 can be located from about 40% to about 60% of rope from the leading edge 40 of the rotor blade 16. More specifically, in certain embodiments, joints 36 and 38 can be located about 50% of chord from leading edge 40. In still further embodiments, joints 36 and 38 can be located less than 40% of chord or more than 60% of rope from the leading edge 40 of the rotor blade 16. Additionally, in some embodiments, the joints 36 and 38 may be aligned as shown generally in the Figures. Alternatively, joints 36 and 38 can be moved.
    [032] In additional embodiments, as shown in Figures 3 and 7, the rotor blade 16 may also include at least one pressure side segment 44 and/or at least one suction side segment 46. For example, as shown in Figure 7, the rotor blade 16 may include a pressure side segment 44 disposed and joined with a suction side segment 46 at the front and rear edges 40, 42. Such segments can be used in combination with and/or exclusive to the additional segments as required. described in this document.
    [033] To date, the segments described in this document are joined at two joint locations. Although, in additional embodiments, less than two or more than two joint locations may be used. For example, as shown in Figure 9, the rotor blade 16 may also include a jointless continuous blade surface 45. More specifically, as shown, the jointless continuous blade surface 45 does not require connecting the multiple segments. Such segments 45 may be used in combination with and/or exclusive to the additional segments as described herein. Additionally, as shown in Figure 10, rotor blade 16 may also include a blade segment having a single joint blade surface 55. More specifically, as shown, single joint blade surface 55 may include a side surface. of pressure 33, a suction side surface 31 and a single joint 57 at the trailing edge 42. Therefore, the single joint paddle surface 55 requires only one joint rather than multiple joints. Such segments 55 may be used in combination with and/or exclusive to the additional segments as described herein.
    [034] In addition, as shown in Figures 11 and 12, the rotor blade 16 may also include a multi-jointed blade surface 59. More specifically, as shown in Figure 11, the multi-jointed blade surface 59 may include a plurality of segments 41, 43, 47 and 49 joined together by multiple joints 61, 63, 65, 67 spaced around the cross section of the blade segment 59. For example, as shown, segments 41, 43, 47 and 49 may include a forward pressure side segment 43, a front suction side segment 41, an aft pressure side segment 49, and an aft suction side segment 47. In another embodiment, as shown in Figure 12, a segment blade 59 may include a generally J-shaped blade segment 39 and an additional blade segment, e.g., an aft pressure side segment 49 or an aft suction side segment 47, joined together. through junctions 65 and 67. More specifically, as per m Once, the J-shaped paddle segment 39 may extend from the trailing edge 42 around the suction side surface 33 to a pressure side joint 35. Such segments can be used in combination with and/or exclusive to the segments. additional as described in this document.
    [035] Referring now to Figures 2 to 3, the rotor blade 16 may also include one or more longitudinally extending structural components configured to provide improved rigidity, strength and/or buckling resistance to the rotor blade 16. For example , the blade root section 20 may include one or more longitudinally extending spar caps 48, 50 configured to be engaged against the opposing inner surfaces of the blade segments of the rotor blade 16. Similarly, the nose section The blade 22 may include one or more longitudinally extending spar caps 51, 53 configured to be engaged against the opposing inner surfaces of the rotor blade blade 16. In addition, the blade tip section 20 and/or the blade section The blade root 22 may also include one or more shear webs 35 configured between the one or more spar caps 48, 50, 51, 53 of the blade root section 20 or the blade tip section 22, respectively. As such, the shear web(s) 35 is (are) configured to increase stiffness in blade root section 20 and/or blade tip section 22, thus allowing sections 20 and 22 are handled with more control.
    [036] More specifically, in particular embodiments, the blade root section 20 and/or the blade tip section 22 may be preformed with the one or more spar caps 48, 50, 51, 53. Additionally, the spade root spar caps 48, 50 can be configured to line up with the spade tip spar caps 51, 53. The spade caps 48, 53 can be generally designed to control the stresses of bending and/or other loads acting on the rotor blade 16 in a generally broad direction (a direction parallel to the amplitude 23 of the rotor blade 16) during operation of a wind turbine 10. Similarly , the stringer covers 48, 50, 51, 53 can be designed to resist the compression in the direction of the amplitude that occurs during the operation of the wind turbine 10. Additionally, the stringer cover(s) 48, 50, 51 , 53 can be configured to extend from the blade root section 20 to the blade tip section 22 or a portion of it. Therefore, in certain embodiments, the blade root section 20 and the blade tip section 22 can be joined together via their respective spar caps 48, 50, 51, 53.
    [037] In additional embodiments, as shown in Figures 2, 3, 16, and 18, the rotor blade 16 may also include an additional structural member 52 attached to the blade root section 20 and extending in a direction of generally, in the sense of amplitude. More specifically, structural member 52 may extend any suitable distance between blade root section 20 and blade tip section 22. Therefore, structural member 52 is configured to provide additional structural support for rotor blade 16 as well as an optional mounting frame for the various blade segments as described in this document. For example, in certain embodiments, the structural member 52 can be secured to the blade root section 20 and can extend a distance in the predetermined amplitude direction so that leading and/or trailing edge segments 24 and 26 can be mounted thereon. same.
    [038] Now referring to Figures 13 to 19, several assembly embodiments of the modular rotor blade 16, as described in this document, are illustrated. For example, as shown in Figure 13, a flowchart of one embodiment of a method 100 for assembling a modular rotor blade 16 in accordance with the present invention is illustrated. As shown at 102, method 100 includes providing a preformed blade root section 20 and a preformed blade tip section 22 of the rotor blade. Additionally, as mentioned and generally shown in the Figures, the blade root section 20 and/or the blade tip section 22 may each include one or more spar caps 48, 50, 51, 53 extending into a direction, generally speaking, in the sense of amplitude. In such embodiments, the blade root section 20 and spar caps 48, 50 can be fabricated (e.g., infused) in a single run or mold so as to produce an integral and uniform part. Similarly, the blade tip section 22 and the one or more spar caps 51, 53 can be in a single run so as to produce an integral and uniform part. In alternative embodiments, the spade tip section 22 may not include spar caps 51, 53.
    [039] As shown at 104, method 100 may also include providing at least one preformed paddle segment (e.g., segments 24, 26, 41, 43, 44, 45, 46, 47, or 49, as described herein) of rotor blade 16. Additionally, as shown at 106, method 100 may also include mounting one or more blade segments around spar caps 48, 50 of blade root section 20. More specifically, in certain embodiments, the blade segment(s) may have a chord direction cross section that has multiple joints, with at least one of the multiple joints located on both the pressure side surface and the side surface of suction of a shovel segment. Therefore, in certain embodiments, method 100 may include assembling the leading and trailing edge segments 24 and 26 between the blade root section 20 and the blade tip section 22 and joining the segments through the pressure and pressure side joints. suction 36 and 38. In addition, method 100 may include mounting at least one pressure side segment 44 and at least one suction side segment 46 between blade root section 20 and blade tip section 22 in one direction. , generally speaking, in the sense of amplitude. In still further embodiments, where the blade segment is a single joint blade segment 55 (Figure 10), method 100 may include separating the pressure and suction side surfaces 31 and 33 at the single joint 57, assembling the segment. of continuous spade 55 over the one or more spar caps 48, 50 and securing the continuous spade segment 55 between the blade root section 20 and the spade tip section 22 through an adhesive on the single joint 55.
    [040] In particular embodiments, as shown in Figures 14, 15, 16 and 18, an accessory apparatus 70 can be used to mount the rotor blade 16. More specifically, the accessory apparatus 70 can be used to arrange and/ or orienting the rotor blade blade segments 16 so that the segments can be properly mounted between blade root section 20 and blade tip section 22. More specifically, as shown, accessory apparatus 70 may include a main fitting assembly 58 that is configured to support and orient the blade root section 20, for example, with the leading edge side facing downwards or vice versa. Additionally, in some embodiments, the main fitting 58 may also include a blade root plate 64 configured to align a root end portion 68 of the blade root section 20 to the main fitting 58 assembly. main fitting assembly 58 may also include a root support structure 66 configured to support the root end portion 68 of the blade root section 20. In certain embodiments, as shown in Figure 18, the root support structure 66 may additionally include a support block 72 configured to provide additional support and/or protection to the root end portion 68 of the blade root section 20.
    [041] In addition, as shown in Figures 14, 15, 16 and 18, the accessory apparatus may include a leading edge accessory assembly 60 that is configured to support and/or orient the segment(s) of leading edge 24 with respect to blade root section 20. As such, leading edge fitting assembly 60 can be installed on main fitting assembly 58, for example, below blade root section 20 when the root section blade 20 is installed in the main attachment assembly 58. As such, the leading edge attachment assembly 60 allows the leading edge segment(s) 24 to be easily mounted between the blade section. blade root 20 and blade tip section 22 while the leading edge segment(s) 24 is (are) held in position through the leading edge fitting 60.
    [042] Similarly, as shown in Figures 14, 15, 16 and 18, the accessory apparatus 70 may also include a trailing edge accessory assembly 62 that is configured to support and/or orient the segment(s). trailing edge segment(s) 26 relative to blade root section 20. As such, trailing edge segment(s) 26 can be loaded into trailing edge fitting assembly 62 and accessory mount 62 can be installed in the main accessory mount 58, for example, above the blade root section 20 when the blade root section 20 is installed in the main accessory mount 58. For example, as shown in Figure 16 , the trailing edge fitting assembly 62 containing the trailing edge segment(s) 26 can be installed to the main fitting assembly 58 above the shovel root section 20 via a crane. As such, the trailing edge segment(s) can be mounted between the blade root section 20 and the blade tip section 22 as the edge segment(s) Rear 26 is (are) held in position by the trailing edge fitting assembly 62. Therefore, each of fitting assemblies 58, 60 and 62 can be used to support and arrange the various blade components/segments in a direction generally in the amplitude direction so that the components can be easily aligned and secured together to form the rotor blade 16.
    [043] More specifically, in certain embodiments, the leading edge segment(s) 24 may be loaded onto and supported by the leading edge fitting assembly 60. Additionally, in embodiments In particular, the leading edge segments 24 can be joined together, for example, through an adhesive, while being supported on the leading edge fitting assembly 60. In addition, as shown in Figure 15, the leading edge fitting assembly 60 can be carried in the main fitting assembly 58, for example, in a lower portion of the main fitting assembly 58. Therefore, as shown in Figure 16, the leading edge fitting assembly 60 can be lifted into the root section of blade 20 so as to properly locate leading edge segment(s) 24 with respect to blade root section 20. In addition, trailing edge segment(s) 26 may be loaded (s) in rear edge accessory assembly 62. Add Finally, in certain embodiments, one or more adjacent trailing edge segments 26 may be joined together, for example, via an adhesive, while being supported by the trailing edge fitting assembly 62. As such, the trailing edge fitting assembly tail 62 can be lowered on the main attachment 58 assembly, for example, with the use of a crane, so that one or more of the trailing edge segment(s) 26 can be properly oriented ) in relation to the leading edge segment(s) 24.
    [044] In further embodiments, method 100 may also include attaching an additional structural member 52 to the blade root section 20 so that the structural member 52 extends in a generally broad direction. Therefore, as shown in Figure 17, the blade segments (eg, leading and trailing edge segments 24 and 26) can be mounted on structural member 52. For example, in one embodiment, trailing edge segments 26 can be mounted on the structural member 52 of the blade root section 20 and the leading edge segments 24 can be mounted on the trailing edge segments 26, for example, by overlapping the trailing edge segments 26 at the joints 36 and 38. In alternative embodiments , any of the blade segments as described herein may similarly be mounted to the structural member 52 of the blade root section 20 in a direction in the span direction.
    [045] Therefore, as shown at 108 of Figure 13, method 100 may also include joining the blade tip section 20 to one or both of spar caps 51, 53 and/or to one of the spade segments of to form the modular rotor blade 16 as shown in Figure 19 (a) and (b). In addition, method 100 may also include mounting one or more shear webs 35 between the one or more spar caps 48, 50, 51, 53 of the blade root section 20 or the blade tip section 22 above, by example, from the step of assembling the at least one blade segment between the blade root section 20 and the blade tip section 22. As such, the shear web(s) is (are) configured ) to increase stiffness in the blade root section 20 and/or blade tip section 22.
    [046] Consequently, once the blade root section 20 is joined to the blade tip section 22 (and the remaining internal connections of the rotor blade 16 are complete), the remaining close segments (e.g., the side segments pressure and suction valves 44 and 46) can be fitted over the tip-to-root connection to complete the rotor blade 16, for example, as shown in Figure 19(C).
    [047] This written description uses examples to reveal the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, which includes making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that are not different from the literal language of the claims or if they include equivalent structural elements with insubstantial differences from the literal language of the claims. PARTS LIST 10 Wind Turbine 12 Tower 14 Nacelle 16 Rotor Blade 18 Rotor 20 Blade Root Section 22 Blade Tip Section 23 Amplitude 24 Front Edge Segment 25 Rope 26 Rear Edge Segment 27 Longitudinal Geometric Axis 28 Side Surface of Front Pressure 30 Lateral Suction Surface Front 31 Lateral Pressure Surface 32 Lateral Pressure Surface from Aft 33 Lateral Suction Surface 34 Lateral Suction Surface Aft 35 Shear Weave 36 Lateral Pressure Join 38 Lateral Suction Join 39 J-Shaped Shovel 40 Front Edge 41 Front Pressure Side Segment 42 Rear Edge 43 Front Suction Side Segment 44 Pressure Side Segment 45 Continuous Airfoil Surface Without Joint 46 Suction Side Segment 47 Aft Pressure Side Segment 48 Cover Pressure Side Root Stringer 49 Aft Suction Side Segment 50 Suction Side Root Stringer Cap 51 Stringer Cover d and Pressure Side End 52 Structural Component 53 Suction Side End Spar Cap 54 Junction 55 Single Joint Shovel Segment 56 Adhesive 57 Single Joint 58 Main Attachment Assembly 59 Multiple Joint Blade Segment 60 Front Edge Accessory Assembly 61 Gasket 62 Rear Edge Accessory Assembly 63 Gasket 64 Spade Root Plate 65 Gasket 66 Root Support Frame 67 Gasket 68 Root End Portion 70 Accessory Apparatus 72 Support Block 100 Method 102 Method Step 104 Step Method 106 Method Step 108 Method Step
    权利要求:
    Claims (6)
    [0001]
    1. MODULAR ROTOR BLADE (16) for a wind turbine (10), characterized in that the rotor blade (16) comprises: a blade root section (20), the blade root section (20) comprises one or more spar caps (48, 50) extending in a direction in the span direction, wherein the blade root section (20) is manufactured integrally with the spar caps (48, 50) in a single run or mold; a blade tip section (22); a plurality of leading edge segments (24) comprising a forward pressure side surface (28) and a front suction side surface (30); and, a plurality of trailing edge segments (26) comprising an aft pressure side surface (32) and an aft suction side surface (34) wherein the leading edge segment (24) and the aft edge segment. trailing edge (26) are disposed between the blade root section (20) and the blade tip section (22) in a direction in the amplitude direction, and wherein the at least one leading edge segment (24) and the at least one trailing edge segment (26) are joined at a lateral pressure joint (36) and a lateral suction joint (38).
    [0002]
    ROTOR BLADE (16) according to claim 1, characterized in that it additionally comprises at least one lateral pressure segment (44) and at least one lateral suction segment (46).
    [0003]
    3. ROTOR BLADE (16) according to claim 1, characterized in that the blade root section (20) further comprises one or more shear webs (35) configured between the one or more spar caps (48, 50 ).
    [0004]
    4. ROTOR BLADE (16) according to any one of claims 1 to 3, characterized in that the blade tip section (22) comprises one or more spar caps (51, 53) extending in a direction towards of amplitude, wherein the blade root section (20) and the blade tip section (22) are joined together by their respective spar caps (48, 50, 51, 53).
    [0005]
    5. ROTOR BLADE (16) according to any one of claims 1 to 4, characterized in that at least one leading edge segment (24) and the at least one trailing edge segment (26) overlap at the lateral junction of pressure (36) and at the suction side junction (38).
    [0006]
    ROTOR BLADE (16) according to any one of claims 1 to 5, characterized in that at least one leading edge segment (24) and the at least one trailing edge segment (26) are constructed, at least in part of at least one of a thermosetting polymer or a thermoplastic polymer.
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    同族专利:
    公开号 | 公开日
    CN106286115B|2021-05-25|
    CN106286115A|2017-01-04|
    US20160377050A1|2016-12-29|
    EP3112671A1|2017-01-04|
    BR102016015144A2|2017-01-03|
    BR102016015144A8|2018-02-27|
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    法律状态:
    2017-01-03| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2018-02-27| B03H| Publication of an application: rectification [chapter 3.8 patent gazette]|
    2020-02-18| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-06-08| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-07-27| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 28/06/2016, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/753,137|US20160377050A1|2015-06-29|2015-06-29|Modular wind turbine rotor blades and methods of assembling same|
    US14/753,137|2015-06-29|
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