Methods for Mitigating Noise during High Wind Speed Conditions of Wind Turbines

Abstract

A method for mitigating noise during high wind speed conditions of a wind turbine includes providing a backward twist to the outboard region of the rotor blade having an angle of less than 6. The method may also include reducing a tip chord taper within at least a portion of the outboard region of the rotor blade. Further, the method may include increasing a local tip chord length of the rotor blade. In addition, the method may include increasing a torsional stiffness of the outboard region of the rotor blade. As such, a combination of one or more of the blade properties described above are configured to reduce noise associated with high wind speed conditions.

Claims

1. A method for mitigating noise generated by a rotor blade of a wind turbine during high wind speed conditions, the method comprising: providing a backward twist to an outboard region of the rotor blade having an angle of less than 6 degrees (); and, reducing a tip chord taper within at least a portion of the outboard region of the rotor blade.

2. The method of claim 1, wherein the backward twist has an angle within a range of from about 0 to about 2.

3. The method of claim 1, wherein the backward twist comprises a slope of from about 0.003 degrees per meter to about 0.0016 degrees per meter.

4. The method of claim 1, wherein the outboard region expands from about 0% to about 10% from a blade tip of the rotor blade in a span-wise direction.

5. The method of claim 1, wherein providing the backward twist to the outboard region of the rotor blade further comprises at least one of backward twisting the outboard region of the rotor blade or providing a blade sleeve over the outboard region of the rotor blade.

6. The method of claim 1, further comprising increasing a torsional stiffness of the outboard region of the rotor blade.

7. The method of claim 5, wherein increasing the torsional stiffness of the outboard region of the rotor blade further comprises at least one of providing an additional layer of fiber material in the outboard region of the rotor blade, decreasing a moment arm of the blade tip of the rotor blade, or adjusting a position or number of shear webs in the rotor blade.

8. The method of claim 1, further comprising increasing a local tip chord length of the rotor blade.

9. The method of claim 8, further comprising increasing the local tip chord length to a range of from about 50 millimeters (mm) to about 400 mm.

10. The method of claim 1, further comprising reducing a tip chord taper of the rotor blade.

11. The method of claim 10, wherein a slope of the tip chord taper ranges from about 0.25 meter/meter span to about 0.75 meter/meter span.

12. A rotor blade assembly of a wind turbine, the rotor blade assembly comprising: an aerodynamic body having an inboard region and an outboard region, the inboard and outboard regions defining a pressure side, a suction side, a leading edge, and a trailing edge, the inboard region comprising a blade root, the outboard region comprising a blade tip, the outboard region comprising a backward twist of less than 6 and a tip chord taper having a slope ranging from about 0.25 meter/meter span to about 0.75 meter/meter span.

13. The rotor blade assembly of claim 12, wherein the backward twist comprises an angle within a range of from about 0 to about 2.

14. The rotor blade assembly of claim 12, wherein the outboard region expands from about 0% to about 10% from a blade tip of the rotor blade in a span-wise direction.

15. The rotor blade assembly of claim 12, further comprising a blade sleeve over the outboard region of the rotor blade, the blade sleeve comprising the backward twist of less than 6.

16. The rotor blade assembly of claim 12, wherein the outboard region further comprises at least one structural feature for increasing torsional stiffness thereof, the structural feature comprising at least one of an additional layer of fiber material or an increased number of shear webs in the rotor blade.

17. The rotor blade assembly of claim 11, wherein the outboard region further comprises an increased local tip chord length in a range of from about 50 millimeters (mm) to about 400 mm.

18. A method for mitigating noise generated by a rotor blade of a wind turbine high wind speed conditions, the method comprising: increasing a torsional stiffness of an outboard region of the rotor blade; providing a backward twist to an outboard region of the rotor blade having an angle of less than 6; increasing a local tip chord length of the rotor blade; and, reducing a tip chord taper within at least a portion of the outboard region of the rotor blade.

19. The method of claim 18, wherein increasing the torsional stiffness of the outboard region the rotor blade further comprises at least one of providing an additional layer of fiber material in the outboard region of the rotor blade, decreasing a moment arm of the blade tip of the rotor blade, or adjusting a position or number of shear webs in the rotor blade.

20. The method of claim 18, wherein the backward twist has an angle within a range of from about 0 to about 2.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0017] A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:

[0018] FIG. 1 illustrates a perspective view of a wind turbine according to the present disclosure;

[0019] FIG. 2 illustrates a perspective view of one embodiment of a rotor blade of a wind turbine according to the present disclosure;

[0020] FIG. 3 illustrates a graph of one embodiment of the back twist of the rotor blade (y-axis) versus the r/R (x-axis) or normalized rotor radius according to the present disclosure;

[0021] FIG. 4 illustrates a graph of one embodiment of the aerodynamic twist (y-axis) versus the geometric twist (x-axis) according to the present disclosure;

[0022] FIG. 5 illustrates a graph of one embodiment of the CL (y-axis) versus the angle of attack (x-axis) according to the present disclosure;

[0023] FIG. 6 illustrates a graph of one embodiment of the tip chord length (C/R) (y-axis) versus the r/R (x-axis) according to the present disclosure;

[0024] FIG. 7 illustrates a graph of one embodiment of the chord reduction slope (y-axis) versus the r/R (x-axis) according to the present disclosure;

[0025] FIG. 8 illustrates partial top views of rotor blade tips according to conventional construction and according to the present disclosure so as to particularly illustrate a tip chord taper of the blade tip of the present disclosure;

[0026] FIG. 9 illustrates a flow diagram of one embodiment of a method for mitigating noise during high wind speed conditions generated by a rotor blade of a wind turbine according to the present disclosure; and,

[0027] FIG. 10 illustrates a perspective view of another embodiment of a rotor blade of a wind turbine according to the present disclosure.

DETAILED DESCRIPTION OF THE INVENTION

[0028] Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.

[0029] Referring now to the drawings, FIG. 1 illustrates a wind turbine 10 of conventional construction. The wind turbine 10 includes a tower 12 with a nacelle 14 mounted thereon. A plurality of rotor blades 16 are mounted to a rotor hub 18, which is in turn connected to a main flange that turns a main rotor shaft. The wind turbine power generation and control components are housed within the nacelle 14. The view of FIG. 1 is provided for illustrative purposes only 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.

[0030] Referring now to FIG. 2, a perspective view of one of the rotor blades 16 of the wind turbine 10 of FIG. 1 is illustrates according to the present disclosure is illustrated. More specifically, as shown, the rotor blade 16 includes one or more features configured to reduce noise associated with high wind speed conditions. As shown, the rotor blade 16 includes an aerodynamic body 20 having an inboard region 23 and an outboard region 25. Further, the inboard and outboard regions 23, 35 define a pressure side 22 and a suction side 24 extending between a leading edge 26 and a trailing edge 28. Further, the inboard region 23 includes a blade root 34, whereas the outboard region 25 includes a blade tip 32.

[0031] Moreover, as shown, the rotor blade 16 defines a pitch axis 40 relative to the rotor hub 18 (FIG. 1) that typically extends perpendicularly to the rotor hub 18 and the blade root 34 through the center of the blade root 34. A pitch angle or blade pitch of the rotor blade 16, i.e., an angle that determines a perspective of the rotor blade 16 with respect to the air flow past the wind turbine 10, may be defined by rotation of the rotor blade 16 about the pitch axis 40. In addition, the rotor blade 16 further defines a chord 42 and a span 44. More specifically, as shown in FIG. 2, the chord 42 may vary throughout the span 44 of the rotor blade 16. Thus, a local chord may be defined for the rotor blade 16 at any point on the blade 16 along the span 44. In certain embodiments, the inboard region 23 may include from about 0% to about 97% of the span 44 of the rotor blade 16, whereas the outboard region 25 may include from about 3% to about 5% of the span 44 of the rotor blade 16.

[0032] Referring now to FIG. 3, the outboard region 25 of the rotor blade 16 of the present disclosure includes a backward twist of less than 6. The backward twist or back twist, as described herein, generally refers to a minimum twist in the rotor blade 16 to the twist at the blade tip 32. Thus, FIG. 3 illustrates a graph of backward twist (y-axis) versus r/R (x-axis), which refers to an approximate normalized distance outward from a center of rotation of the blade 16 along the span 44 thereof according to the present disclosure. Accordingly, curves 50, 52 illustrate back twist ranges of prior art rotor blades. In contrast, curve 54 illustrates the back twist of the rotor blades 16 of the present disclosure, as well as the upper and lower ranges 56, 58. More specifically, as shown, the backward twist of the rotor blade 16 of the present disclosure may include angles within a range of from about 0 to about 2 in the outboard region 25.

[0033] In addition, the back twist slope can vary in combination with the back twist angle. For example, in certain embodiments, the backward twist may have a slope of from about 0.003 degrees per meter to about 0.0016 degrees per meter. In still further embodiments, the back twist slope may be less than 0.003 degrees per meter or greater than 0.0016 degrees per meter.

[0034] Referring now to FIGS. 4 and 5, various graphs are provided to illustrate the aspect of aerodynamic twisting as well as geometric twisting. More specifically, FIG. 4 illustrates a graph of one embodiment of the aerodynamic twist (y-axis) and the geometric twist (x-axis) according to the present disclosure. As shown, the graph highlights that the same design lift coefficient/axial induction distribution can be achieved in multiple ways when changing the airfoil geometry along the span besides changing the geometric twist. FIG. 5 illustrates a graph of one embodiment of the lift coefficient (CL) (y-axis) versus the angle of attack AoA (x-axis) according to the present disclosure. As such, the present disclosure allows for trading some geometric twist into aerodynamic twist (reduced camber respectively increased zero lift angle), which can further improve the negative stall margin. For example, in one embodiment, 2 of aerodynamic twisting is relatively easy to achieve, which may change some of the proposed twist boundaries accordingly.

[0035] More specifically, as shown in FIG. 4, the lift distribution can be adjusted as a function of the aerodynamic twist and/or the geometric twist. For example, curve a) illustrates the lift distribution by purely by changing the geometric twist. Curve b) illustrates the lift distribution by combining aerodynamic twist into geometric twist. Further, curve c) illustrates the lift distribution by dominantly changing the aerodynamic twist and having little geometric twist. In addition, FIG. 5 illustrates aerodynamic twisting by shifting the airfoil polar down and to the right. Thus, as shown, the negative stall margin can be increased by shifting the polar to the right.

[0036] In further embodiments, as shown in FIG. 6, the outboard region 25 of the rotor blade 16 may also include a tip chord length designed to manage noise associated with high wind speed conditions and tip vortex noise. More specifically, FIG. 6 illustrates a graph of C/R (which is the chord C expressed as a percentage of a distance outward from the center of rotation r/R) (y-axis) versus r/R (x-axis) according to the present disclosure. Accordingly, curves 60, 62 illustrate ranges of prior art rotor blades. In contrast, curve 64 illustrates the tip chord length of the rotor blades 16 of the present disclosure, as well as the upper and lower ranges 66, 68. More specifically, as shown, the normalized chord length ratio 54 may range from about 1.60% at about 0.90 r/R to about 0.25% C/R at r/R. In certain embodiments, for example, the tip chord length 54 may be about 50 millimeters (mm), more preferably about 70 mm in the outboard region 25. In further embodiments, the tip chord length 54 may also be about 250 mm to as much as 400 mm.

[0037] Referring now to FIGS. 7-8, the outboard region 25 of the rotor blade 16 may also include a reduced tip chord taper 74 to mitigate tip vortex noise. More specifically, FIG. 7 illustrates a graph of chord reduction slope (y-axis) versus r/R (x-axis) according to the present disclosure. Accordingly, curves 70, 72 illustrate ranges of prior art rotor blades. In contrast, curve 74 illustrates the tip chord taper of the rotor blades 16 of the present disclosure, as well as the upper and lower ranges 76, 78. More specifically, as shown in FIG. 8, a prior art rotor blade 116 and a rotor blade 16 of the present disclosure are illustrated, each depicting the tip chord taper 174, 74, respectively. To reduce high wind speed conditions, it is important to manipulate the tip flow interaction of conventional rotor blades 116, thus a reduced tip chord taper 74 is required. For example, in one embodiment, the tip chord taper 74 may range from about 0.25 meter/meter span to about 0.75 meter/meter span in the outboard region 25 of the blade 16, e.g. over the outer two percent of the rotor blade 16 non-dimensional blade length (r/R).

[0038] Referring now to FIG. 9, a flow diagram of one embodiment of a method 100 for mitigating noise associated with high wind speed conditions generated by the rotor blade 16 of the wind turbine 10 is illustrated. As shown at 102, the method 100 includes providing a backward twist to the outboard region 25 of the rotor blade 16 having an angle of less than 6. For example, in one embodiment, the step of providing the backward twist to the outboard region 25 of the rotor blade 16 may include backward twisting the outboard region 25 of the rotor blade 16. Alternatively, as shown in FIG. 10, the step of providing the backward twist to the outboard region 25 of the rotor blade 16 may include providing a blade sleeve 101 over the outboard region 25 of the rotor blade 16.

[0039] As shown at 104, the method 100 may also include reducing a tip chord taper within at least a portion of the outboard region 25 of the rotor blade 16. As shown at 106, the method 100 may also include increasing a local tip chord length of the rotor blade 16. As shown at 108, the method 100 may include increasing a torsional stiffness of the outboard region 25 of the rotor blade 16. In such embodiments, as shown, the step 108 of increasing the torsional stiffness of the outboard region 25 of the rotor blade 16 may include providing an additional layer of fiber material in the outboard region of the rotor blade (110), decreasing a moment arm of the blade tip of the rotor blade 16 (112), and/or adjusting a position or number of shear webs in the rotor blade 16 (114). As such, it should be understood that the method 100 of the present disclosure may include any one of or combination of the steps illustrated in FIG. 10 in addition to any of the additional steps and/or embodiments described herein.

[0040] This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including 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 do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.