• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A rotor blade assembly (100) for a wind turbine (10) and a method for increasing a loading capability of a rotor blade (16) within a maximum bad limit for a wind turbine (10) are diselosed. The rotor blade assembly (100) ineludes a rotor blade (16) having surfaces defining a pressure side (22), a suetion side (24), a leading edge (26), and a trailing edge (28) extending between a tip (32) and a root (34), The rotor blade assemb (100) fbrther inehides an extension (102) conneeted to a surface of the rotor blade (16), the extension (102) having at least one design charaeteristie configured for inereasing a loading capability of the rotor blade (16) within a maximum bad limit for the wind turbine (10). The design eharaeteristic is one of extension length (120), extension width (122), extension curvature, span-wise extension location, chord-wise extension bocation, or extension angle (124) with respect to a chord line (126) of the rotor blade (16).
    公开号:DK201200554A
    申请号:DKP201200554
    申请日:2012-09-07
    公开日:2013-03-10
    发明作者:Herr Stefan；Riddell Scott Gabell；Giguere Philippe；Fritz Peter James；Bergman Jeffrey Erie
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    EXTENSION FOR ROTOR BLADE IN WIND TURBINE FIELD OF THE INVENTION
    The present disclosure relates in general to wind turbine rotor blades, and more particularly to extensions connected to rotor blades for enhancing the loading capabilities of the rotor blades.
    BACKGROUND OF THE INVENTION
    Wind power is considered one of the cleanest, most environmentally friendly energy sources presently available, and wind turbines have received increased attention in this regard. A modem wind turbine typically includes a tower, generator, gearbox, nacelle, and one or more rotor blades. The rotor blades capture kinetic energy of wind using known airfoil principles. The rotor blades transmit the kinetic energy in the form of rotational energy so as to turn a shaft coupling the rotor blades to a gearbox, or if a gearbox is not used directly to the generator. The generator then converts the mechanical energy to electrical energy that may be deployed to a utility grid.
    Frequently, wind turbines are designed and / or operated with excess design margins, such as excess loading margins. For example, the maximum loading of the rotor blades may be less than the maximum loading that other various components of the wind turbine can withstand. This may result from the use of dated design parameters for certain components relative to other components, operation of the wind turbines in lower loading environments than those for which the wind turbine was originally designed, or other design or operational factors.
    Recently, attempts have been made to increase the loading capabilities of rotor blades. For example, flaps have been mounted to the pressure side and / or suction side of a rotor blade. The flaps effectively increase the surface area of the pressure side and / or suction side, thus increasing the lift of the rotor blades.
    However, such attempts to increase loading capabilities do not take into account, and thus take advantage of, the excess design margins for and maximum load limits of the wind turbines. Thus, in lower loading environments or other situations, the full loading potential of the wind turbine is not maximized.
    Accordingly, improved apparatus for increasing the loading capabilities of wind turbine rotor blades would be desired. For example, apparatus that allow for loading of wind turbine rotor blades within and up to a maximum load limit for the wind turbine would be desired.
    LETTER DESCRIPTION OF THE INVENTION
    Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention, [0007] In one embodiment, a rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade assembly further includes an extension connected to a rotor blade surface, the extension having at least one design characteristic configured to increase the loading capacity of the rotor blade within a maximum load limit for the wind turbine. The design characteristic is one of extension length, extension width, extension curvature, span-wise extension location, chord-wise extension location, or extension angle with respect to a chord line of the rotor blade.
    In another embodiment, a method for increasing the loading capacity of a rotor blade within a maximum load limit for a wind turbine is disclosed. The method includes connecting an extension to a rotor blade surface. The extension has at least one design characteristic configured to increase the loading capacity of the rotor blade within the maximum load limit for the wind turbine. The wind turbine is located in a low loading environment relative to the maximum load limit for the wind turbine. The method further includes rotating the rotor blade on the wind turbine.
    The design characteristic is one of extension length, extension width, extension curvature, span-wise extension location, chord-wise extension location, or extension angle with respect to a chord line of the rotor blade.
    These and other features, aspects and advantages of the present invention will be better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.
    LETTER DESCRIPTION OF THE DRAWINGS
    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; FIG. 1 is a perspective view of a wind turbine according to one embodiment of the present disclosure; FIG. 2 is a top view of a rotor blade assembly according to one embodiment of the present disclosure; FIG. 3 is a perspective view of a rotor blade assembly according to one embodiment of the present disclosure; FIG. 4 is a perspective view of a rotor blade assembly according to one embodiment of the present disclosure; FIG. 5 is a perspective view of a rotor blade assembly according to one embodiment of the present disclosure; and, FIG. 6 is a cross-sectional view of a rotor blade assembly according to one embodiment of the present disclosure.
    DETAILED DESCRIPTION OF THE INVENTION
    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 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.
    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.
    Referring to FIG. 2, a rotor blade 16 according to the present disclosure may include exterior surfaces defining a pressure side 22 and a suction side 24 (see FIGS. 3 through 5) extending between a leading edge 26 and a trailing edge 28, and may extend from a blade tip 32 to a blade root 34. The exterior surfaces may be generally aerodynamic surfaces having generally aerodynamic contours, as is generally known in the art.
    In some embodiments, the rotor blade 16 may include a plurality of individual blade segments aligned in an end-to-end order from blade tip 32 to blade root 34, Each of the individual blade segments may be uniquely configured so that the plurality of blade segments define a complete rotor blade 16 having a designed aerodynamic profile, length, and other desired characteristics. For example, each of the blade segments may have an aerodynamic profile that corresponds to the aerodynamic profile of adjacent blade segments. Thus, the aerodynamic profiles of the blade segments may form a continuous aerodynamic profile of the rotor blade 16. Alternatively, the rotor blade 16 maybe formed as a singular, unitary blade having the designed aerodynamic profile, length, and other desired characteristics.
    The rotor blade 16 may, in exemplary embodiments, be curved. Curving of the rotor blade 16 may entail bending the rotor blade 16 in a generally flapwise direction and / or in a generally edgewise direction. The flapwise direction may generally be constructed as the direction (or the opposite direction) in which the aerodynamic lift acts on the rotor blade 16. The edgewise direction is generally perpendicular to the flapwise direction, Flapwise curvature of the rotor blade 16 is also known as pre-bend, while edgewise curvature is also known as sweep. Thus, a curved rotor blade 16 may be pre-bent and / or swept. Curving may enable the rotor blade 16 to better withstand flapwise and edgewise loads during operation of the wind turbine 10, and may further provide clearance for the rotor blade 16 from the tower 12 during operation of the wind turbine 10, [0022] The rotor blade 16 may further define chord 42 and a span 44. 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 rotor blade 16 along the span 44.
    Additionally, the rotor blade 16 may define an inner board area 52 and an outer board area 54. The inner board area 52 may be a spanwise portion of the rotor blade 16 extending from the root 34. For example, the inner board area 52 may, in some embodiments, include approximately 33%, 40%, 50%, 60%, 67%, or any percentage or range of percentages therebetween, or any other suitable percentage or range of percentages, of the span 44 from the root 34. The outer board area 54 may be a span-wise portion of the rotor blade 16 extending from the tip 32, and may in some embodiments include the remaining portion of the rotor blade 16 between the inner board area 52 and the tip 32. Additionally or alternatively, the outer board area 54 may, in some embodiments, include approximately 33%, 40%, 50%, 60%, 67%, or any percentage or range of percentages therebetween, or any other suitable percentage or range of percentages, of the span 44 from the tip 32.
    As illustrated in FIGS. 2 through 6, the present disclosure may be directed to a rotor blade assembly 100. The rotor blade assembly 100 may include one or more extensions 102 and the rotor blade 16. In general, the extensions 102 may be connected to a surface of the rotor blade 16, and may increase the loading capability, and thus the lift capability, of the rotor blade 16 during operation of the wind turbine 10. In an exemplary embodiment of the present disclosure, an extension 102 may be connected to a surface of the rotor blade 16 adjacent the trailing edge 28 of the rotor blade 16 Alternatively, an extension 102 may be connected to a surface of the rotor blade 16 adjacent the leading edge 26 of the rotor blade 16, or adjacent the tip 32 or the root 34 of the rotor blade 16, or at any other suitable position on the rotor blade 16.
    An exemplary embodiment, as shown in FIG. 2, an extension 102 may be connected to the pressure side 22 of the rotor blade 16. In alternative embodiments, an extension 102 may be connected to the suction side 24.
    [0026] In some embodiments, a rotor blade assembly 100 may include only one extension 102 connected to a rotor blade 16. In other embodiments, a rotor blade assembly 100 may include a plurality of extensions 102 connected to a rotor blade 16, as shown. in FIG. 2. For example, in some embodiments, a plurality of extensions 102 may be mounted in a generally span-wise array along at least a portion of the span 44 of the rotor blade 16. These extensions 102 may abut one another or be spaced apart from one another in the generally span-wise direction.
    An extension 102 according to the present disclosure may, in some embodiments as shown in FIGS. 2 through 4, be an extension plate 104. The extension plate 104 may be partially or entirely curvilinear in the generally chord-wise direction as shown in FIG. 3, or planer in the generally chord-wise direction as shown in FIG. 4, Alternatively, an extension 102 according to the present disclosure may, in some embodiments, as shown in FIG. 5, be an auxiliary airfoil section or sections 106. The auxiliary airfoil section 106 may include a pressure side, suction side, leading edge, and trailing edge, and thus have a generally aerodynamic contour, as shown.
    Extensions 102 according to the present disclosure may be connected to the rotor blade 16 through any suitable apparatus or methods. For example, in some embodiments as shown in FIG. 5, an extension 102 may be spaced from the rotor blade 16 and connected to the rotor blade 16 using suitable connecting apparatus. Such connecting apparatus may be rods 110, frames, or any other apparatus suitable for connecting an extension 102 to the rotor blade 16 while maintaining desired spacing therebetween.
    Alternatively, an extension 102 may be mounted to the rotor blade 16. In some embodiments, mechanical fasteners such as nut / bolt combinations, nails, screws, rivets, or other suitable mechanical fasteners may be utilized to mount an extension to the rotor blade 16. In other embodiments, apparatus such as hinges, in particular piano hinges, may be utilized to mount the extension to the rotor blade 16. In other embodiments, hook-and-loop fasteners or other suitable fasteners may be utilized. Still other embodiments, as shown in FIGS. 3,4, and 6, a bond layer 112 may be disposed between the extension 102 and the rotor blade 16. The bond layer 112 bonds the extension to the rotor blade 16, thus mounting the extension to the rotor blade 16.
    Bond layer 112 may generally be any suitable adhesive or bonding material. In some embodiments, the bond layer 112 may have various characteristics for reducing the strain associated with mounting the extension 102 to the rotor blade 16. The bond layer 112 may thus at least partially absorb strain from the rotor blade 16 and prevent this strain from being transmitted to the extension 102, and may be formed from materials that ax relatively flexible and relatively tough. In exemplary embodiments, the bond layer 112 may generally isolate the strain associated with the rotor blade 16. By generally isolating the strain, the bond layer 112 may generally prevent a relatively substantial portion of the rotor blade 16 strain from being transmitted through the bond layer. 112 to the extension 102.
    In some embodiments, for example, the bond layer 112 may be relatively elastic, and may thus have a relatively low shear modulus. The shear modulus may be determined by suitable environmental conditions or ranges of environmental conditions generally expected for a wind turbine 10. For example, in some embodiments, the shear modulus of the bond layer 112 may be approximately equal to or less than 5 gigapascals. In other embodiments, the bond layer 112 may have a shear modulus approximately less than or equal to 3 gigpascals, 1 gigapascal, 500 megapascals, 300 megapascals, 100 megapascals, 20 megapascals, or 10 megapascals. The relatively low shear modulus of the bond layer 112 may advantageously allow the bond layer 112 to absorb strain from the rotor blade 16 and reduce or prevent the strain being transmitted through the bond layer 112 to the extension 102.
    Further, in some embodiments, the bond layer 112 may have a relatively low durometer. For example, the durometer of the bond layer 112 may be approximately less than or equal to 100, 90, SO, 70, or 60. The relatively low durometer of the bond layer 112 may advantageously allow the bond layer 112 to absorb strain from the rotor blade 16 and reduce or prevent the strain being transmitted through the bond layer 112 to the extension 102.
    In some embodiments, the bond layer 112 may comprise an epoxy, polyurethane, methacrylate such as methyl methacrylate or another suitable methacrylate, or an acrylic. In embodiments where the bond layer 112 is an acrylic, the acrylic may be an acrylic foam, such as a closed cell acrylic foam, or any acrylic solid or non-foam.
    In some embodiments, as shown in FIG. 6, the bond layer 112 may include an inner layer 114 and a plurality of outer layers 116. The inner layer 114 may be disposed between the opposing outer layers 116. The inner layer 114 may comprise, for example, an epoxy, a polyurethane, a methacrylate, or an acrylic. In exemplary embodiments, the inner layer 114 is an acrylic foam. Further, the acrylic foam may be a closed cell acrylic foam.
    The inner layer 114 may define a thickness 118. In some embodiments, such as when the inner layer 114 is an inner acrylic foam layer, the thickness 118 may be in the range between approximately 0.1 millimeters and approximately 10 millimeters. Alternatively, the thickness 118 may be in the range between approximately 0.3 millimeters and approximately 10 millimeters, or in the range between approximately 0.3 millimeters to approximately 3 millimeters, or in the range between approximately 0.5 millimeters and approximately 10 millimeters, or in the range between approximately 0.5 millimeters and approximately 3 millimeters, or in the range between approximately 0.6 millimeters and approximately 3 millimeters, or in the range between approximately 0.6 millimeters and approximately 1 millimeter.
    The outer layers 116 may generally be configured to mount the extension 102 to the rotor blade 16. In exemplary embodiments, the outer layers 116 comprise adhesives and are outer adhesive layers. For example, in some exemplary embodiments, the outer layers 116 may comprise acrylic adhesives. The adhesives are generally disposed on the outer surfaces of the outer layers 116 to adhere to, for example, the extension 102 and / or rotor blade 16. The inner layer may generally be coated to the inner surfaces of the outer layers to form the bond. layer 112.
    Extensions 102 according to the present disclosure have one or more design characteristics which are configured to increase the loading capacity of the rotor blade 16. In other words, such design characteristics increase the lift capacity and thus the loading capacity of the rotor blade. 16 to which extension 102 is connected. Further, the design characteristics are configured to increase the loading capability within an established maximum load limit for the wind turbine 10. The maximum load limit may be established during the design, manufacture, and / or operation of the rotor blade 16 and wind turbine 10, and establishes the maximum total loading capability, typically with a built in factor of safety, for the wind turbine. For example, the maximum load limit may be established, and the total loading capability of the rotor blades 16 without extensions 102 may be less than this maximum load limit. This prevents damage to the wind turbine 10 during operation. Due to the use of dated design parameters or the operation of the wind turbines in lower loading environments than those for which the wind turbine was originally designed, however, there may be a significant load design margin between the maximum load limit and the total loading capability. . The design characteristics of the extensions 102 thus allow for increasing the loading capacity of the rotor blades 16 within the maximum load limit, such that the total loading capacity of the rotor blades 16 approaches or reaches the maximum load limit. This advantageously allows for increased power output from wind turbines that, for example, were designed using outdated design parameters or are utilized in lower loading environments.
    A design characteristic may be, for example, extension length 120 or extension width 122. The length 120 may be, for example, in the range between 0% and 30%, 0% and 25%, 0% and 20% , or 0% and 15% of span 44. The width 122 may be, for example, in the range of 0% and 30%, 0% and 25%, 0% and 20%, or 0% and 15% of the local chord. Another design characteristic maybe extension curvature. Extension curvature is the curvature of any curvilinear portion of the extension 102, such as in the generally chord-wise direction. Another design characteristic may be chord-wise extension location. The chord-wise extension location may, in some embodiments, define the chord-wise amount or ratio of the extension that is on or within the rotor blade 16 boundaries versus off or out of the rotor blade 16 boundaries. Another design characteristic may be span-wise extension location. For example, an extension may be located in the inner board area 52 or outer board area 54 of the rotor blade 16. Another design characteristic may be extension angle 124 with respect to chord line 126 of the rotor blade 16. The chord line for the rotor blade 16 may be established using any suitable known technique, and may further be determined at any suitable local chord for the rotor blade 16, The extension angle 124 is the angle between the chord line 126 and a line tangent to a point of contact 128 between the extension 102 and rotor blade 16. The extension angle 124 maybe, for example, in the range between 40 degrees and -40 degrees, 30 degrees and -30 degrees, 20 degrees and -20 degrees, or 10 degrees and -10 degrees In some embodiments, as shown in FIGS. 2 and 3, the rotor blade assembly 100 further includes a gurney flap 130. The gurney flap 130 may extend from the extension 102. In some embodiments, the gurney flap 130 may be connected to the extension 102 using a suitable mechanical fastener, bond layer , or other suitable connecting apparatus. In other embodiments, the gurney flap 130 may be integral with the extension 102, as shown, Guroey flaps 130 according to the present disclosure may have one or more design characteristics configured to increase the loading capacity of the rotor blade 16. In other words, such design characteristics increase the loading capability, and thus, the lift capability of the rotor blade 16 to which the gumey flap 130 is connected. Further, the design characteristics are configured to increase the loading capability within an established maximum load limit for the wind turbine 10. The maximum load limit may be established during the design, manufacture, and / or operation of the rotor blade 16 and wind turbine 10, and establishes the maximum total loading capability, typically with a built in factor of safety, for the wind turbine.
    A design characteristic may be, for example, flap length 132 or flap height 134. The length 132 may be, for example, in the range of 0% and 30%, 0% and 25%, 0% and 20% , or 0% and 15% of span 44. The height 134 may be, for example, in the range of 0% and 15%, 0% and 12%, 0% and 10%, or 0% and 5% of the local chord. Another design characteristic may be chord-wise flap location. The chord-wise flap location may, in some embodiments, define the distance between the gumey flap 130 and the extension 102. Another design characteristic may be the span-wise extension location. For example, a gumey flap 130 may be located in the inner board area 52 or outer board area 54 of the rotor blade 16. Another design characteristic may be flap angle 136 with respect to chord line 126 of the rotor blade 16. The chord line for the rotor blade 16 may be established using any suitable known technique, and may further be determined at any suitable local chord for the rotor blade 16. The flap angle 136 is the angle between the chord line 126 and the flap 130 generally. In some embodiments, the gurney flap 130 may extend generally perpendicularly to the chord line 126 of the rotor blade 16. In other embodiments, the gurney flap 130 may extend at any suitable angle 136 to the chord line 126.
    In some embodiments, the gurney £ 1¾130 may further include a flap adjustment plate 140. The flap adjustment plate 140 may be mounted to the gurney flap 130, and may increase the height 134 of the gurney flap 130. The flap adjustment plate 140 may be permanently mounted to the gurney flap 130, or may be temporarily mounted to the gurney flap 130. For example, the flap adjustment plate 140 may be mounted to the gurney flap during specific time periods, such as periods of relatively lower loading or expected lower loading on the rotor blade 16. These periods may be time-based, month-based, season-based, or otherwise.
    [0044] It should be understood that according to the present disclosure, extensions 102 may be connected to rotor blades 16 during manufacture of the rotor blade 16, or may be retro-fit to existing rotor blades 16, to form rotor blade assemblies 100.
    The present disclosure is further directed to a method for increasing the loading capacity of a rotor blade 16 within a maximum load limit for a wind turbine 10. The method may include connecting an extension 102 to the rotor blade 16, as discussed above. . The rotor blade 16 may be connected to a wind turbine 10, and the wind turbine 10 may be provided in a low loading environment relative to the maximum load limit for the wind turbine. The method may further include rotating the rotor blade 16 on the wind turbine 10, as discussed above.
    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 which 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 dements with insubstantial differences from the literal languages of the daims.
    权利要求:
    Claims (14)
    [1] 2. The rotor blade assembly (100) of claim 1, wherein the extension (102) is an extension plate (104).
    [2] 3. The rotor blade assembly (100) of claim 2, wherein at least a portion of the extension plate (104) in the generally chord-wise direction is planer.
    [3] 4. The rotor blade assembly (100) of claim 2, wherein at least a portion of the extension plate (104) in the generally chord-wise direction is curvilinear.
    [4] 5. The rotor blade assembly (100) of any of claims 1-4, wherein the extension (102) is mounted on a surface of the rotor blade (16).
    [5] 6. The rotor blade assembly (100) of claim 5, further comprising a bond layer (112) disposed between the extension (102) and the rotor blade (16), the bond layer (112) bonding the extension (102) to the rotor blade (16).
    [6] 7. The rotor blade assembly (100) of claim 6, wherein the bond layer (112) has a shear modulus approximately equal to or less than 5 gigapascals.
    [7] 8. The rotor blade assembly (100) of any of claims 6-7, wherein the bond layer (112) comprises at least one of an epoxy, a polyurethane, a methacrylate, and an acrylic.
    [8] 9. The rotor blade assembly (100) of any of claims 6-7, wherein the bond layer (112) comprises an inner acrylic foam layer (114) disposed between opposing outer adhesive layers (116).
    [9] 10. The rotor blade assembly (100) of any of claims 1 -9, further comprising a gurney flap (130) extending from the extension (102).
    [10] 11. The rotor blade assembly (100) of claim 10, wherein the gurney flap (130) extends generally perpendicularly to the chord line (126) of the rotor blade (16).
    [11] 12. The rotor blade assembly (100) of any of claims 10-11, wherein the gurney flap (130) has at least one design characteristic configured for increasing the loading capability of the rotor blade (16) within the maximum load limit for the wind turbine (10), and wherein the design characteristic is one of flap length (132), flap height (134), span-wise flap location, chord-wise flap location, or flap angle (136) with respect to the chord line (126).
    [12] 13. The rotor blade assembly (100) of any of claims 10-11, wherein the gurney flap (130) further comprises a flap adjustment plate (140) mounted thereto, the flap adjustment plate (140) increasing a height (134) of the gurney flap (130).
    [13] 14. A wind turbine (10), comprising: a plurality of rotor blades (16), each of the plurality of rotor blades (16) having surfaces defining a pressure side (22), a suction side (24), a leading edge (26), and a trailing edge (2S) extending between a tip (32) and a root (34); and, an extension (102) connected to a surface of one of the plurality of rotor blades (16), the extension (102) having at least one design characteristic configured for increasing a loading capability of the rotor blade (16) within a maximum load limit for the wind turbine (10), wherein the design characteristic is one of extension length (120), extension width (122), extension curvature, span-wise extension location, chord-wise extension location, or extension angle (124) with respect to a chord line (126) of the rotor blade (16)·
    [14] 15. A method for increasing a loading capability of a rotor blade (16) within a maximum load limit for a wind turbine (10), the method comprising: connecting an extension (102) to a surface of a rotor blade (16), the extension (102) having at least one design characteristic configured for increasing the loading capability of the rotor blade (16) within the maximum load limit for the wind turbine (10), the wind turbine (10) located in a low loading environment relative to the maximum load limit for the wind turbine (10); and, rotating the rotor blade (16) on the wind turbine (10), wherein the design characteristic is one of extension length (120), extension width (122), extension curvature, span-wise extension location, chord-wise extension location, or extension angle (124) with respect to a chord line (126) of the rotor blade (16).
    类似技术:
    公开号 | 公开日 | 专利标题
    US8834127B2|2014-09-16|Extension for rotor blade in wind turbine
    US10584676B2|2020-03-10|Wind turbine rotor blade assembly with surface features
    CA2826409C|2017-03-07|Attachment system for a wind turbine rotor blade accessory
    DK178555B1|2016-06-13|Wind turbine rotor blade
    DK178482B1|2016-04-11|Noise reducer for rotor blade in wind turbine
    US8047784B2|2011-11-01|Lift device for rotor blade in wind turbine
    US9494134B2|2016-11-15|Noise reducing extension plate for rotor blade in wind turbine
    US20120027588A1|2012-02-02|Root flap for rotor blade in wind turbine
    US20120134815A1|2012-05-31|Blade extension for rotor blade in wind turbine
    US8430633B2|2013-04-30|Blade extension for rotor blade in wind turbine
    EP2868916B1|2019-06-19|Chord extenders for a wind turbine rotor blade assembly
    EP2784301B1|2018-01-31|Rotor blade assembly for wind turbine having load reduction features
    US9033661B2|2015-05-19|Rotor blade assembly for wind turbine
    CA2828512A1|2014-04-03|Noise reduction tab and method for wind turbine rotor blade
    WO2019018131A1|2019-01-24|Airflow configuration for a wind turbine rotor blade
    US20130064677A1|2013-03-14|Rotor blade assembly for wind turbine
    同族专利:
    公开号 | 公开日
    DE102012108182A1|2013-03-14|
    US20120141269A1|2012-06-07|
    CN102996328B|2016-09-21|
    US8834127B2|2014-09-16|
    DK178210B1|2015-08-24|
    CN102996328A|2013-03-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    USRE19412E|1935-01-01|Aircraft and control thereof |
    US2899128A|1959-08-11|Vaghi |
    US175355A|1876-03-28|Waltee king |
    US573562A|1896-12-22|Propeller |
    US1861065A|1930-08-18|1932-05-31|Poot Philippe|Screw-propeller for flying machines and other aerodynamics apparatus|
    US2071012A|1932-11-22|1937-02-16|Adams Herbert Luther|Noiseless device|
    US2238749A|1939-01-30|1941-04-15|Clarence B Swift|Fan blade|
    US2225312A|1939-10-05|1940-12-17|Bell Telephone Labor Inc|Acoustic device|
    US2312219A|1941-04-21|1943-02-23|Sensenich Brothers|Aircraft propeller|
    US2469167A|1946-06-11|1949-05-03|American Steel & Wire Co|Vibration damper|
    IT1036993B|1974-07-02|1979-10-30|Rotron Inc|DEVICE FOR THE MOVEMENT OF A FLUID|
    US4204629A|1977-07-20|1980-05-27|Rolls-Royce Limited|Brush seal and a method of manufacture|
    US4618313A|1980-02-06|1986-10-21|Cofimco S.R.L.|Axial propeller with increased effective displacement of air whose blades are not twisted|
    GB8626408D0|1986-11-05|1987-12-16|Secr Defence|Damping treatment for pipes & bodies|
    US4720244A|1987-05-21|1988-01-19|Hudson Products Corporation|Fan blade for an axial flow fan and method of forming same|
    US5088665A|1989-10-31|1992-02-18|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Serrated trailing edges for improving lift and drag characteristics of lifting surfaces|
    US5320491A|1992-07-09|1994-06-14|Northern Power Systems, Inc.|Wind turbine rotor aileron|
    EP0615903B1|1993-03-13|1999-09-15|GKN Westland Helicopters Limited|Rotary blades|
    US5328329A|1993-07-06|1994-07-12|Hudson Products Corporation|Fan blade width extender|
    NL9301910A|1993-11-04|1995-06-01|Stork Prod Eng|Wind turbine.|
    US5522266A|1993-11-30|1996-06-04|Medex, Inc.|Low cost pressure transducer particularly for medical applications|
    CA2141529A1|1994-10-25|1996-04-26|Frances Gould|Street sweeper brush assembly|
    US6352601B1|1994-12-27|2002-03-05|The B. F. Goodrich Company|Self-adhering ice protector|
    DE19647102A1|1996-11-14|1998-05-20|Philippe Arribi|Flow body|
    JP2000120524A|1998-10-16|2000-04-25|Mitsubishi Heavy Ind Ltd|Windmill blade|
    NZ511846A|1998-12-09|2003-07-25|Aloys Wobben|Reduction in the noise produced by a rotor blade of a wind turbine|
    GB2358130A|2000-01-17|2001-07-18|Llewellyn Jones John Adrian|One-piece toothbrush|
    DE10020177A1|2000-04-25|2001-11-08|Daimler Chrysler Ag|Device for reducing noise on aircraft wings|
    BR0003706A|2000-05-30|2002-02-13|Tecsis Tecnologia E Sist S Ava|Axle fan for low noise and high efficiency|
    DK174318B1|2000-06-19|2002-12-02|Lm Glasfiber As|Wind turbine rotor blade includes flap comprising laminate with layers of materials having differing thermal expansion coefficients|
    US6733240B2|2001-07-18|2004-05-11|General Electric Company|Serrated fan blade|
    EP3219981B1|2001-07-19|2021-09-01|Vestas Wind Systems A/S|Wind turbine blade|
    DE10157849A1|2001-11-24|2003-06-12|Airbus Gmbh|Arrangement for reducing the aerodynamic noise on a slat of a commercial aircraft|
    US7059833B2|2001-11-26|2006-06-13|Bonus Energy A/S|Method for improvement of the efficiency of a wind turbine rotor|
    US6872048B2|2001-11-26|2005-03-29|Lennox Industries, Inc.|Fan with reduced noise generation|
    EP1338793A3|2002-02-22|2010-09-01|Mitsubishi Heavy Industries, Ltd.|Serrated wind turbine blade trailing edge|
    JP2003254225A|2002-03-05|2003-09-10|Ebara Corp|Device for reducing airflow noise of windmill|
    DK1613860T3|2003-03-31|2016-02-01|Univ Denmark Tech Dtu|Managing energy, performance and / or stability of a wind turbine with horizontal axis of use of variable vane geometry management|
    DE102004008618A1|2004-02-21|2005-09-08|Geka Brush Gmbh|Brush for applying cosmetic or nourishing products|
    US7328770B2|2005-06-16|2008-02-12|Owens Jeffrey A|Strap silencer|
    US7637721B2|2005-07-29|2009-12-29|General Electric Company|Methods and apparatus for producing wind energy with reduced wind turbine noise|
    MX2008002475A|2005-08-22|2008-09-10|Viryd Technologies Inc|Fluid energy converter.|
    US7458777B2|2005-09-22|2008-12-02|General Electric Company|Wind turbine rotor assembly and blade having acoustic flap|
    ES2318925B1|2005-09-22|2010-02-11|GAMESA INNOVATION & TECHNOLOGY, S.L.|AEROGENERATOR WITH A BLADE ROTOR THAT REDUCES NOISE.|
    DK176352B1|2005-12-20|2007-09-10|Lm Glasfiber As|Profile series for blade for wind turbines|
    NL1031223C1|2006-02-23|2007-08-24|Stichting Nationaal Lucht En R|Wind turbine blade, has brush at back edge of blade, where brush includes synthetic bristles that rest parallel to top or bottom of blade|
    US7740206B2|2006-04-13|2010-06-22|The Board Of Trustees Of The Leland Stanford Junior University|Translating active Gurney flap to alleviate aircraft wake vortex hazard|
    DE102006017897B4|2006-04-13|2008-03-13|Repower Systems Ag|Rotor blade of a wind turbine|
    BE1017134A5|2006-05-11|2008-03-04|Delaere Marc|BRUSH FOR A SCRUB, SWEEP AND / OR BONE MACHINE AND SPRAY DEVICE FOR CLEANING MULTIPLE SURFACES SIZED BY GROOPS AND / OR JOINING EACH OTHER.|
    ES2294927B1|2006-05-31|2009-02-16|Gamesa Eolica, S.A.|AIRLINER SHOVEL WITH DIVERGING OUTPUT EDGE.|
    US20080001363A1|2006-06-28|2008-01-03|General Electric Company|Brush sealing system and method for rotary machines|
    EP1892442A1|2006-08-18|2008-02-27|Siemens Aktiengesellschaft|Brush seal for a turbomachine|
    WO2008108881A2|2006-09-08|2008-09-12|Steven Sullivan|Method and apparatus for mitigating trailing vortex wakes of lifting or thrust generating bodies|
    DE102006043462A1|2006-09-15|2008-03-27|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Aerodynamic component e.g. rotor blade, for use in wind turbine, has pair of surface units on high pressure side engaged between two surface units on low pressure side in main extension direction of trailing edge|
    US7959412B2|2006-09-29|2011-06-14|General Electric Company|Wind turbine rotor blade with acoustic lining|
    US7811063B2|2006-11-03|2010-10-12|General Electric Company|Damping element for a wind turbine rotor blade|
    EP1927454A1|2006-11-29|2008-06-04|Trisa Holding AG|Toothbrush with partially coated surface|
    US20080166241A1|2007-01-04|2008-07-10|Stefan Herr|Wind turbine blade brush|
    US7918653B2|2007-02-07|2011-04-05|General Electric Company|Rotor blade trailing edge assemby and method of use|
    US7413408B1|2007-02-22|2008-08-19|Samuel B Tafoya|Vibration-reducing and noise-reducing spoiler for helicopter rotors, aircraft wings, propellers, and turbine blades|
    EP2129908B1|2007-03-20|2010-12-01|Vestas Wind Systems A/S|Wind turbine blades with vortex generators|
    WO2008113349A2|2007-03-20|2008-09-25|Vestas Wind Systems A/S|Slow rotating wind turbine rotor with slender blades|
    US7828523B2|2007-03-27|2010-11-09|General Electric Company|Rotor blade for a wind turbine having a variable dimension|
    WO2008131800A1|2007-04-30|2008-11-06|Vestas Wind Systems A/S|A wind turbine blade|
    ES2345583B1|2007-05-31|2011-07-28|GAMESA INNOVATION & TECHNOLOGY, S.L.|AEROGENERATOR SHOVEL WITH ANTI-NOISE DEVICES.|
    ES2324002B1|2007-06-22|2010-05-13|GAMESA INNOVATION & TECHNOLOGY, S.L.|AIRLINER SHOVEL WITH DEFLECTABLE ALERONS.|
    US7927078B2|2007-07-12|2011-04-19|General Electric Company|Wind turbine blade tip vortex breakers|
    NL2000821C2|2007-08-17|2009-02-18|Stichting Energie|Wind turbine and rotor blade.|
    US20090074585A1|2007-09-19|2009-03-19|General Electric Company|Wind turbine blades with trailing edge serrations|
    US20090097976A1|2007-10-15|2009-04-16|General Electric Company|Active damping of wind turbine blades|
    EP2053240B1|2007-10-22|2011-03-30|Actiflow B.V.|Wind turbine with boundary layer control|
    US8047804B2|2007-12-27|2011-11-01|General Electric Company|Wind tower and method of assembling the same|
    US20090196756A1|2008-02-05|2009-08-06|General Electric Company|Wind turbine blades and method for forming same|
    US8418967B2|2008-02-21|2013-04-16|Cornerstone Research Group, Inc.|Passive adaptive structures|
    US8192161B2|2008-05-16|2012-06-05|Frontier Wind, Llc.|Wind turbine with deployable air deflectors|
    GB2462308A|2008-08-01|2010-02-03|Vestas Wind Sys As|Extension portion for wind turbine blade|
    MX2010011336A|2008-08-06|2010-11-30|Mitsubishi Heavy Ind Ltd|Windmill blade and wind power generator using same.|
    US9239039B2|2008-10-27|2016-01-19|General Electric Company|Active circulation control of aerodynamic structures|
    EP2138714A1|2008-12-12|2009-12-30|Lm Glasfiber A/S|Wind turbine blade having a flow guiding device with optimised height|
    US20100143151A1|2009-02-06|2010-06-10|General Electric Company|Permeable acoustic flap for wind turbine blades|
    EP2253838A1|2009-05-18|2010-11-24|Lm Glasfiber A/S|A method of operating a wind turbine|
    EP2253836A1|2009-05-18|2010-11-24|Lm Glasfiber A/S|Wind turbine blade|
    CA2763898A1|2009-06-03|2010-12-09|Flodesign Wind Turbine Corp.|Wind turbine blades with mixer lobes|
    EP2270312A1|2009-07-01|2011-01-05|PEM-Energy Oy|Aero- or hydrodynamic construction|
    US8011887B2|2010-07-21|2011-09-06|General Electric Company|Rotor blade assembly|
    US8083488B2|2010-08-23|2011-12-27|General Electric Company|Blade extension for rotor blade in wind turbine|
    US7976276B2|2010-11-04|2011-07-12|General Electric Company|Noise reducer for rotor blade in wind turbine|
    US7976283B2|2010-11-10|2011-07-12|General Electric Company|Noise reducer for rotor blade in wind turbine|
    US8523515B2|2010-11-15|2013-09-03|General Electric Company|Noise reducer for rotor blade in wind turbine|
    US8267657B2|2010-12-16|2012-09-18|General Electric Company|Noise reducer for rotor blade in wind turbine|
    US8414261B2|2011-05-31|2013-04-09|General Electric Company|Noise reducer for rotor blade in wind turbine|US8602732B2|2011-10-06|2013-12-10|General Electric Company|Wind turbine rotor blade with passively modified trailing edge component|
    EP2834517B1|2012-03-13|2020-05-06|Wobben Properties GmbH|Twisted blade root|
    GB201209697D0|2012-05-31|2012-07-18|Airbus Uk Ltd|Method of coupling aerofoil surface structures and an aerofoil assembly|
    US9458821B2|2012-09-11|2016-10-04|General Electric Company|Attachment system for a wind turbine rotor blade accessory|
    US20140072441A1|2012-09-12|2014-03-13|Michael J. Asheim|Load and noise mitigation system for wind turbine blades|
    US9399919B2|2012-12-31|2016-07-26|General Electric Company|Extension tip sleeve for wind turbine blade|
    US9989033B2|2013-03-15|2018-06-05|George J. Syrovy|Horizontal axis wind or water turbine with forked or multi-blade upper segments|
    US9377005B2|2013-03-15|2016-06-28|General Electric Company|Airfoil modifiers for wind turbine rotor blades|
    US9677537B2|2013-03-28|2017-06-13|General Electric Company|Acoustic shield for noise reduction in wind turbines|
    US9556849B2|2013-05-02|2017-01-31|General Electric Company|Attachment system and method for wind turbine vortex generators|
    US20150098821A1|2013-10-08|2015-04-09|Edward A. Mayda|Reverse flow load mitigation device for a wind turbine blade|
    US9638164B2|2013-10-31|2017-05-02|General Electric Company|Chord extenders for a wind turbine rotor blade assembly|
    US9494134B2|2013-11-20|2016-11-15|General Electric Company|Noise reducing extension plate for rotor blade in wind turbine|
    US9890764B2|2014-03-26|2018-02-13|General Electric Company|Trailing edge cap for a rotor blade and method of manufacturing same|
    US9476406B2|2014-04-14|2016-10-25|Siemens Aktiengesellschaft|Vortex generators aligned with trailing edge features on wind turbine blade|
    CN104314770A|2014-09-26|2015-01-28|东方电气集团东方汽轮机有限公司|Wind turbine blade with trailing edge flat plate|
    GB201417924D0|2014-10-10|2014-11-26|Vestas Wind Sys As|Wind turbine blade having a trailing edge flap|
    US10151325B2|2015-04-08|2018-12-11|General Electric Company|Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same|
    US10180125B2|2015-04-20|2019-01-15|General Electric Company|Airflow configuration for a wind turbine rotor blade|
    CN104989591A|2015-06-30|2015-10-21|上海理工大学|Blade with adjustable flapping wings|
    US10094358B2|2015-07-21|2018-10-09|Winnova Energy LLC|Wind turbine blade with double airfoil profile|
    EP3329117B1|2015-09-03|2021-02-17|Siemens Gamesa Renewable Energy A/S|Wind turbine blade with trailing edge tab|
    GB201520725D0|2015-11-24|2016-01-06|Vestas Wind Sys As|improvements relating to wind turbine blades|
    DK3219980T3|2016-03-16|2019-04-08|Siemens Ag|Rear-edge air duct of a wind turbine rotor wing|
    DE202016103595U1|2016-07-05|2017-10-06|Peter Lutz|Rotor blade and rotor for wind turbines in the megawatt range|
    US10208733B2|2016-07-19|2019-02-19|Michael L Barrows|Tandem tip-joined rotor blade and hub coupling for passive pitch angle control|
    CN109790818B|2016-09-09|2020-07-28|维斯塔斯风力系统有限公司|Device for mounting to a wind turbine blade and method of mounting the device|
    US10487796B2|2016-10-13|2019-11-26|General Electric Company|Attachment methods for surface features of wind turbine rotor blades|
    US10612517B2|2017-03-09|2020-04-07|General Electric Company|Flexible extension for wind turbine rotor blades|
    US10794358B2|2017-03-17|2020-10-06|Primo Energy, Inc.|High torque wind turbine blade, turbine, and associated systems and methods|
    DE102017117843A1|2017-08-07|2019-02-07|Wobben Properties Gmbh|Rotor blade of a rotor of a wind turbine, wind turbine and method for improving the efficiency of a rotor of a wind turbine|
    US10767623B2|2018-04-13|2020-09-08|General Electric Company|Serrated noise reducer for a wind turbine rotor blade|
    US10746157B2|2018-08-31|2020-08-18|General Electric Company|Noise reducer for a wind turbine rotor blade having a cambered serration|
    WO2021028573A1|2019-08-14|2021-02-18|Power Curve Aps|Wind turbine blade with a gurney flap|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    US13/228,650|US8834127B2|2011-09-09|2011-09-09|Extension for rotor blade in wind turbine|
    US201113228650|2011-09-09|
    [返回顶部]