CN102797624A - Root flap for rotor blade in wind turbine - Google Patents
Root flap for rotor blade in wind turbine Download PDFInfo
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- CN102797624A CN102797624A CN2012101674178A CN201210167417A CN102797624A CN 102797624 A CN102797624 A CN 102797624A CN 2012101674178 A CN2012101674178 A CN 2012101674178A CN 201210167417 A CN201210167417 A CN 201210167417A CN 102797624 A CN102797624 A CN 102797624A
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- rotor blade
- pressure side
- suction side
- wing flap
- blade assembly
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- 238000000034 method Methods 0.000 claims abstract description 10
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 238000000926 separation method Methods 0.000 abstract description 2
- 238000005452 bending Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/0608—Rotors characterised by their aerodynamic shape
- F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
- F03D1/0641—Rotors characterised by their aerodynamic shape of the blades of the section profile of the blades, i.e. aerofoil profile
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/065—Rotors characterised by their construction elements
- F03D1/0658—Arrangements for fixing wind-engaging parts to a hub
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/20—Rotors
- F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2250/00—Geometry
- F05B2250/70—Shape
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Wind Motors (AREA)
Abstract
A rotor blade assembly and a method for reducing the separation region of a rotor blade for a wind turbine are disclosed. The rotor blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. The rotor blade assembly further includes a flap extending in the generally span-wise direction from the root towards the tip. The flap includes an inner surface and an outer surface, the inner surface conformingly mounted to at least one of the pressure side, the suction side, or the trailing edge, the outer surface and at least one of the pressure side or the suction side defining a generally continuous aerodynamic surface.
Description
Technical field
The present invention relates to the rotor blade of wind turbine in general, and relates more specifically to be installed in the wing flap on the rotor blade.
Background technique
Wind-force is considered to one of energy of at present obtainable cleaning, environmental protection, and in this, wind turbine receives increasing concern.Modern wind turbine generally includes pylon, generator, gear-box, cabin and one or more rotor blade.Rotor blade utilizes known aerofoil profile principle to catch the kinetic energy of wind.The kinetic energy of ability form is rotated in the rotor blade transmission, so that the axle rotation, this axle is attached to gear-box with rotor blade, if perhaps do not use gear-box, then this axle is attached directly to generator with rotor blade.Then, generator converts mechanical energy to configurable electric energy to utility network.
Generally speaking, in order to catch the kinetic energy of increase, the size of rotor blade increases gradually.Yet the shape of the rotor blade of typical wind turbo machine causes bigger separated region because of the profile of rotor blade.Particularly, the contiguous root of rotor blade and comprise that the profile of the inside of root can cause such separation.In some cases, this inside can comprise rotor blade 40%, 50% or more.Separated region causes significant energy loss through producing resistance.Further, along with the size increase of rotor blade, these losses also are exaggerated.
Therefore, it will be favourable improved rotor blade assembly being provided.For example, expectation provides the rotor blade assembly that reduces or eliminate the separated region of adjacent rotor root of blade.
Summary of the invention
Aspect of the present invention and advantage perhaps become significantly through explanation partly setting forth in the explanation below, perhaps are able to understanding through practice of the present invention.
An embodiment of the invention disclose a kind of rotor blade assembly of wind turbine.This rotor blade assembly comprises rotor blade, rotor blade have definition on the pressure side, the outer surface of suction side, leading edge and trailing edge, and between tip and root along roughly open up to direction extend.This rotor blade assembly also comprise from root along roughly open up to the wing flap that extends towards the tip of direction.Wing flap comprises internal surface and outer surface, and internal surface is installed on the pressure side adaptively, in suction side or the trailing edge at least one, on the pressure side or at least one side and outer surface in the suction side formed roughly continuous aerodynamic surface.
Another embodiment of the present invention discloses a kind of wind turbine.This wind turbine comprises: a plurality of rotor blades, each in said a plurality of rotor blades all have definition on the pressure side, the outer surface of suction side, leading edge and trailing edge, and between tip and root along roughly open up to direction extend.This wind turbine also comprises wing flap; The said root of at least one from said a plurality of rotor blades of said wing flap along said roughly open up to direction towards said most advanced and sophisticated the extension; Said wing flap comprises internal surface and outer surface; Said internal surface be installed in adaptively in said a plurality of rotor blade at least one said on the pressure side, in said suction side or the said trailing edge at least one, at least one side in the said on the pressure side perhaps said suction side of at least one in said a plurality of rotor blades and said outer surface form roughly continuous aerodynamic surface.
Further, said wing flap have along said exhibition to the cross sectional area that roughly reduces towards said tip of direction.
Further, said wing flap extends and is no more than the maximum chord length of said rotor blade along roughly tangential direction
Further, the said outer surface of said wing flap comprises on the pressure side part and suction side part.
Further, the said outer surface of said wing flap also is included in the planar section that extends between said part on the pressure side and the said suction side part.
Further, said internal surface be installed in adaptively said on the pressure side, on said suction side and the said trailing edge.
Another embodiment of the invention discloses a kind of method of separated region of the rotor blade that is used to reduce wind turbine.This method comprises: wing flap is installed on the rotor blade, and the rotor blade on the rotation wind turbine.Wherein this rotor blade have definition on the pressure side, the outer surface of suction side, leading edge and trailing edge, and between tip and root along roughly open up to direction extend.Wing flap from root along roughly open up to direction extend towards the tip.Wing flap comprises internal surface and outer surface, and internal surface is installed on the pressure side adaptively, in suction side or the trailing edge at least one, on the pressure side or at least one side in the suction side and the roughly continuous aerodynamic surface of outer surface formation.
With reference to following explanation and accompanying claims, of the present invention these with the understanding that will improve of further feature, aspect and advantage.The accompanying drawing that is included in this specification and constitutes the part of this specification shows mode of execution of the present invention, and is used to explain principle of the present invention with this explanation.
Description of drawings
To those skilled in the art, in this specification with reference to accompanying drawing set forth of the present invention fully with disclosing of can realizing, it comprises preferred forms of the present invention, in the accompanying drawings:
Fig. 1 is a kind of side view of wind turbine of conventional configurations;
Fig. 2 is the birds-eye perspective according to the rotor blade assembly of an embodiment of the invention;
Fig. 3 is the face upwarding view of the rotor blade assembly of Fig. 2;
Fig. 4 is the birds-eye perspective of rotor blade assembly according to another implementation of the invention;
Fig. 5 is the face upwarding view of the rotor blade assembly of Fig. 4;
Fig. 6 is the sectional view according to the rotor blade assembly of an embodiment of the invention;
Fig. 7 is the sectional view of rotor blade assembly according to another implementation of the invention;
Fig. 8 is the sectional view of rotor blade assembly according to another implementation of the invention;
Fig. 9 is the sectional view of rotor blade assembly according to another implementation of the invention;
Figure 10 is the sectional view of rotor blade assembly according to another implementation of the invention; And,
Figure 11 is the sectional view of rotor blade assembly according to another implementation of the invention.
Reference numerals list:
Embodiment
To wherein show one or more instance of mode of execution in the drawings at length with reference to mode of execution of the present invention now.It is to be used to explain the present invention that each instance is provided, rather than restriction the present invention.In fact, it will be apparent to one skilled in the art that under the situation that does not deviate from scope of the present invention or spirit and can make various modifications and variation the present invention.For example, can be used in another mode of execution to produce another mode of execution as the part demonstration of a mode of execution or the characteristic of describing.Therefore, this invention is intended to cover interior these modifications and the variation of scope that falls into accompanying claims and their equivalent.
Fig. 1 illustrates the wind turbine 10 of conventional configurations.Wind turbine 10 comprises pylon 12, and cabin 14 is installed on the pylon 12.A plurality of rotor blades 16 are installed on the rotor hub 18, and rotor hub 18 is connected with the main flange of rotation main rotor shaft.The power of wind turbine produces and controlling component is contained in the cabin 14.For the illustrative purpose provides the view of Fig. 1, so that the present invention places the exemplary fields of purposes.Be contemplated that the present invention is not limited to the structure of the wind turbine of any particular type.
With reference to Fig. 2 to Figure 11; Rotor blade 16 according to the present invention can comprise formation on the pressure side 22 with the outer surface of suction side 24; Wherein on the pressure side 22 and suction side 24 between leading edge 26 and trailing edge 28, extend, and rotor blade 16 can extend to root of blade 34 from vane tip 32.As generally known in the art, outer surface can be to have the roughly aerodynamic surface of aerodynamic profile usually.
In some embodiments, rotor blade 16 can comprise a plurality of independent blade sections, and these blade sections are arranged to root of blade 34 from vane tip 32 according to end to end order.In the blade sections each all can be configured to uniquely separately, makes a plurality of blade sections form the complete rotor blade 16 with design pneumatic longitudinal plane profile, length and other desirable characteristics.For example, the pneumatic longitudinal plane profile of each in the blade sections all can be corresponding to the pneumatic longitudinal plane profile of adjacent blades section.Like this, the pneumatic longitudinal plane profile of each blade sections can form the continuous pneumatic longitudinal plane profile of rotor blade 16.Perhaps, rotor blade 16 can form the single integral blade with design pneumatic longitudinal plane profile, length and other desirable characteristics.
In the exemplary embodiment, rotor blade 16 can be crooked.The bending of rotor blade 16 can make rotor blade 16 along the wing roughly to direction and/or along edge roughly to direction bend.The wing to direction can be interpreted as aerodynamic lift usually and act on the direction (perhaps opposite direction) on the rotor blade 16.The edge to direction and the wing to the direction approximate vertical.The wing of rotor blade 16 also is known as prebuckling to bending, and the edge also is known as to bending and scans.Therefore, crooked rotor blade 16 can be prebuckling and/or scan.Bending make rotor blade 16 the run duration of wind turbine 10 can bear better the wing to load and edge to load, and can be that rotor blade 16 provides the gap away from pylon 12 at the run duration of wind turbine 10.
In addition, rotor blade 16 can limit inside region 52 and exterior lateral area 54.Inside region 52 can be that the exhibition of extending from root 34 of rotor blade 16 is to part.For example; In some embodiments, inside region 52 can comprise the span 44 from root 34 about 33%, 40%, 50%, 60%, 67%, or any percentage or percentage between scope, or any other suitable percentage or the scope between the percentage.Exterior lateral area 54 can be rotor blade 16 from most advanced and sophisticated 32 exhibitions of extending to part, and in some embodiments, can comprise the remainder of rotor blade 16 between inside region 52 and tip 32.Additionally or alternatively; In some embodiments, exterior lateral area 54 can comprise the span 44 from most advanced and sophisticated 32 about 33%, 40%, 50%, 60%, 67%, or any percentage or percentage between scope, or any other suitable percentage or the scope between the percentage.
To shown in Figure 11, the present invention can also relate to rotor blade assembly 100 like Fig. 2.Rotor blade assembly 100 can comprise wing flap 110 and rotor blade 16.Wing flap 110 is to be arranged in the inside region 52 of rotor blade assembly 100 and to be installed in the common static wing flap on the rotor blade 16.Wing flap 110 along exhibition to direction extend to most advanced and sophisticated 32 from root 34.Therefore, an end of wing flap 110 is positioned at root 34 places, and the other end is positioned in the inside region 52 between root 34 and most advanced and sophisticated 32.Be described below, wing flap has changed the profile of a part of the contiguous root 34 of rotor blade 16.This change reduces or has eliminated any separated region in this part of rotor blade 16, and has reduced the resistance that is associated with rotor blade 16, and has improved the performance of rotor blade 16.
For example, Fig. 2 to Fig. 7 and Fig. 9 show be installed in adaptively rotor blade 16 on the pressure side 22, each mode of execution of the internal surface 112 on suction side 24 and the trailing edge 28.Fig. 6 shows a mode of execution of internal surface 112, and it is installed in suction side 24 and on the pressure side on 22 the relative least part.Fig. 7 shows a mode of execution of internal surface 112, and it is installed in the relative substantial portion of suction side 24 and on the pressure side on 22 the relative least part.Fig. 9 shows another mode of execution of internal surface 112, and it is installed in suction side 24 and on the pressure side on 22 the relative least part.
Further, Fig. 8 show be installed in adaptively on the pressure side 22 with trailing edge 28 on a mode of execution of internal surface 112, wherein internal surface 112 is installed on the pressure side on 22 the relative substantial portion.Figure 10 and Figure 11 show each mode of execution that is installed on the pressure side the internal surface 112 on 22 adaptively, and wherein internal surface 112 is installed on the pressure side on 22 the relative substantial portion.
As stated, in some embodiments, internal surface 112 can be installed on the pressure side 22 and/or the relative substantial portion of suction side 24 on.Can limit this part with respect to local chord length 46.For example, internal surface can be installed on the pressure side 22 and/or suction side 24 on local chord length 46 about 20% and about 60% between, for example between about 20% and about 50%, for example between about 20% and about 40%, for example between about 20% and about 30%.In other embodiments, internal surface 112 can be installed on the pressure side 22 and/or the relative least part of suction side 24 on.Can also limit this part with respect to local chord length 46.For example, internal surface can be installed on the pressure side 22 and/or suction side 24 on local chord length 46 about 0% and about 20% between, for example between about 0% and about 15%, for example between about 0% and about 10%, for example between about 0% and about 5%.
Be understood that; Internal surface 112 can be installed on the pressure side 22 adaptively, in suction side 24 or the trailing edge 28 any one or a plurality of on, and internal surface 112 can also be installed on the pressure side 22, any one or a plurality of relative substantial portion in suction side 24 or the trailing edge 28 or relatively on the least part.Further, it should be understood that above-mentioned relative substantial portion and relative least part are not limited to above-mentioned scope of disclosure, and any suitable scope or percentage are all in scope of the present invention and spirit.
To shown in Figure 11, the outer surface 114 of wing flap 110 one or more in the outer surface of rotor blade 16 formed roughly continuous aerodynamic surface like Fig. 2.For example, outer surface 114 with on the pressure side 22 or suction side 24 at least one formed roughly continuous aerodynamic surface.Roughly continuous aerodynamic surface is to have the roughly surface of continuous pneumatic profile.Therefore, when two surfaces had formed roughly continuous aerodynamic surface, there was less interruption in the intersection on two surfaces in the aerodynamic profile.Like Fig. 2 to Fig. 7 and shown in Figure 9, for example, outer surface 114 has formed roughly continuous aerodynamic surface with suction side 24.Further, in Fig. 2 to Figure 11, outer surface 114 and on the pressure side 22 formed roughly continuous aerodynamic surface.
The outer surface 114 of wing flap 110 can comprise on the pressure side part 122 and/or suction side part 124.On the pressure side part 122 as stated can with rotor blade 16 on the pressure side 22 form roughly aerodynamic surface, and suction side part 124 can form roughly aerodynamic surface with suction side 24 as stated.In some embodiments, shown in figure 11, the outer surface 114 of wing flap 110 can only comprise on the pressure side part 122 and suction side part 124, and on the pressure side part 122 can be met at place, roughly tangential end two of wing flap 110 with suction side part 124.
Yet in other embodiments, outer surface 114 can also comprise other surface.For example, in some embodiments, to shown in Figure 10, outer surface 114 can also comprise planar section 126 like Fig. 2.Planar section 126 can on the pressure side extend between part 122 and the suction side part 124, is perhaps on the pressure side extending between one of part 122 or suction side part 124 and the internal surface 112.
In the exemplary embodiment, planar section 126 along roughly open up to direction extend.Therefore, in some embodiments, planar section 126 can be roughly parallel to the span 44 of rotor blade 16 and extend.Yet, perhaps perhaps requirement as required, planar section 126 can extend with any suitable angle with respect to the span 44.In other alternative mode of execution, planar section 126 can extend with any suitable angle with respect to rotor blade 16.
Further, as shown in the figure, in some embodiments, planar section 126 is approximately perpendicular to the local chord length 46 of rotor blade 16.Therefore, when planar section 126 for example along roughly open up to direction when extending, the planar section 126 in any position can be approximately perpendicular to the local chord length 46 of that position.Yet perhaps, planar section 126 can become with respect to rotor blade 16 vertically perhaps to have any other suitable angle with any suitable angular positioning.
In some embodiments, to shown in Figure 10, wing flap 110 can extend along roughly tangential direction like Fig. 2, but is no more than the maximum chord length 48 of rotor blade 16.In these mode of executions, along roughly open up to direction on along any position of wing flap 110, wing flap 110 extends not more than the maximum chord length 48 of rotor blade 16.Comprise in the mode of execution of planar section 126 that at wing flap 110 planar section 126 can extend not more than the maximum chord length 48 of rotor blade 16.Only comprise in the mode of execution of part on the pressure side 122 and suction side part 124 that at wing flap 110 on the pressure side part 122 and suction side part 124 all extend not more than the maximum chord length 48 of rotor blade 16.Yet, shown in figure 11 in other embodiments, perhaps requirement as required, wing flap 110 can extend beyond the maximum chord length 48 of rotor blade 16 along roughly tangential direction.In these mode of executions, along roughly open up to direction on along any position of wing flap 110, wing flap 110 can extend beyond the maximum chord length 48 of rotor blade 16.
In some embodiments, like Fig. 2 to shown in Figure 5, wing flap 110 can have along exhibition to direction towards most advanced and sophisticated 32 cross sectional areas that roughly reduce.Yet, perhaps, wing flap 110 can have along exhibition to direction towards most advanced and sophisticated 32 cross sectional areas that roughly increase, perhaps can have the cross sectional area of constant.
The present invention can also relate to the method for the separated region of the rotor blade 16 that is used to reduce wind turbine 10.As stated, the method comprising the steps of: wing flap 110 is mounted on the rotor blade 16.This method also comprises: the rotor blade 16 on the rotation wind turbine 10.
This written explanation utilizes instance to come open the present invention, comprises preferred forms, and can make those skilled in the art's embodiment of the present invention, comprises making and using any device or system and carry out the method for combination in any.Patentable scope of the present invention is defined by the claims, and can comprise other instance that those skilled in the art expect.If these other instances comprise the structural element identical with the word language of claim, if perhaps they comprise that the word language with claim does not have the equivalent structure element of essential difference, then they are within the scope of the claims.
Claims (15)
1. rotor blade assembly that is used for wind turbine, said rotor blade assembly comprises:
Rotor blade, said rotor blade have definition on the pressure side, the outer surface of suction side, leading edge and trailing edge, and between tip and root along roughly open up to direction extend; And,
Wing flap; Said wing flap from said root along said roughly open up to direction towards said most advanced and sophisticated the extension; Said wing flap comprises internal surface and outer surface; Said internal surface be installed in adaptively said on the pressure side, in said suction side or the said trailing edge at least one, at least one side in the said on the pressure side perhaps said suction side and said outer surface form roughly continuous aerodynamic surface.
2. rotor blade assembly according to claim 1 is characterized in that, said wing flap have along said exhibition to the cross sectional area that roughly reduces towards said tip of direction.
3. according to each described rotor blade assembly in the claim 1 and 2, it is characterized in that said wing flap extends and be no more than the maximum chord length of said rotor blade along roughly tangential direction.
4. according to each the described rotor blade assembly in the claim 1 to 3, it is characterized in that the said outer surface of said wing flap comprises on the pressure side part and suction side part.
5. rotor blade assembly according to claim 4 is characterized in that, the said outer surface of said wing flap also is included in the planar section that extends between said part on the pressure side and the said suction side part.
6. rotor blade assembly according to claim 5 is characterized in that, said planar section along said roughly open up to direction extend.
7. according to each described rotor blade assembly in the claim 5 and 6, it is characterized in that said planar section is approximately perpendicular to the local chord length of said rotor blade.
8. according to each described rotor blade assembly in the claim 5 to 7, it is characterized in that said planar section extends not more than the maximum chord length of said rotor blade.
9. according to each described rotor blade assembly in the claim 1 to 8, it is characterized in that, said internal surface be installed in adaptively said on the pressure side with said trailing edge on.
10. according to each described rotor blade assembly in the claim 1 to 8, it is characterized in that said internal surface is installed on said suction side and the said trailing edge adaptively.
11. according to each described rotor blade assembly in the claim 1 to 8, it is characterized in that, said internal surface be installed in adaptively said on the pressure side, on said suction side and the said trailing edge.
12., it is characterized in that said outer surface and the roughly continuous aerodynamic surface of said formation on the pressure side according to each described rotor blade assembly in the claim 1 to 11.
13., it is characterized in that said outer surface and said suction side form roughly continuous aerodynamic surface according to each described rotor blade assembly in the claim 1 to 12.
14. a wind turbine, it comprises:
A plurality of rotor blades, each in said a plurality of rotor blades all have definition on the pressure side, the outer surface of suction side, leading edge and trailing edge, and between tip and root along roughly open up to direction extend; And,
Wing flap; The said root of at least one from said a plurality of rotor blades of said wing flap along said roughly open up to direction towards said most advanced and sophisticated the extension; Said wing flap comprises internal surface and outer surface; Said internal surface be installed in adaptively in said a plurality of rotor blade at least one said on the pressure side, in said suction side or the said trailing edge at least one, at least one side in the said on the pressure side perhaps said suction side of at least one in said a plurality of rotor blades and said outer surface form roughly continuous aerodynamic surface.
15. the method for the separated region of a rotor blade that is used to reduce wind turbine, said method comprises:
Wing flap is installed on the rotor blade; Said rotor blade have definition on the pressure side, the outer surface of suction side, leading edge and trailing edge; And between tip and root along roughly open up to direction extend; Said wing flap from said root along said roughly open up to direction towards said most advanced and sophisticated the extension; Said wing flap comprises internal surface and outer surface, said internal surface be installed in adaptively said on the pressure side, in said suction side or the said trailing edge at least one, at least one side in the said on the pressure side perhaps said suction side and said outer surface form roughly continuous aerodynamic surface; And,
Rotate the said rotor blade on the said wind turbine.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/112148 | 2011-05-20 | ||
| US13/112,148 US20120027588A1 (en) | 2011-05-20 | 2011-05-20 | Root flap for rotor blade in wind turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102797624A true CN102797624A (en) | 2012-11-28 |
Family
ID=45526921
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012101674178A Pending CN102797624A (en) | 2011-05-20 | 2012-05-18 | Root flap for rotor blade in wind turbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20120027588A1 (en) |
| CN (1) | CN102797624A (en) |
| DE (1) | DE102012104317A1 (en) |
| DK (1) | DK178360B1 (en) |
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| CN103711655A (en) * | 2013-12-26 | 2014-04-09 | 中国科学院工程热物理研究所 | Large-thickness blunt-trailing-edge wind turbine blade |
| CN105658954A (en) * | 2014-09-22 | 2016-06-08 | 最优叶片有限公司 | Wind turbine rotor blade |
| CN107110112A (en) * | 2014-10-10 | 2017-08-29 | 维斯塔斯风力系统有限公司 | wind turbine blade with trailing edge flap |
| CN110892149A (en) * | 2017-07-20 | 2020-03-17 | 通用电气公司 | Airflow configuration for wind turbine rotor blades |
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| US9677538B2 (en) * | 2012-02-09 | 2017-06-13 | General Electric Company | Wind turbine rotor blade assembly with root extension panel and method of assembly |
| PL2834517T3 (en) | 2012-03-13 | 2020-11-02 | Wobben Properties Gmbh | Twisted blade root |
| US20140093380A1 (en) * | 2012-10-03 | 2014-04-03 | General Electric Company | Noise reduction tab and method for wind turbine rotor blade |
| EP2851557A1 (en) * | 2013-09-24 | 2015-03-25 | LM WP Patent Holding A/S | A wind turbine blade with root end aerodynamic flaps |
| DK178313B1 (en) * | 2014-12-09 | 2015-11-30 | Envision Energy Denmark Aps | Wind turbine blade with air leakage protection |
| US10180125B2 (en) | 2015-04-20 | 2019-01-15 | General Electric Company | Airflow configuration for a wind turbine rotor blade |
| JP6719901B2 (en) * | 2015-12-28 | 2020-07-08 | あおい精機株式会社 | Sample processing device |
| WO2018015254A1 (en) * | 2016-07-19 | 2018-01-25 | Lm Wind Power International Technology Ii Aps | Wind turbine blade with flatback root segment and related method |
| DE102016123412A1 (en) * | 2016-12-05 | 2018-06-07 | Wobben Properties Gmbh | Rotor blade for a wind turbine and wind turbine |
| DE102017129708B4 (en) | 2017-12-13 | 2022-05-12 | cp.max Rotortechnik GmbH & Co. KG | Trailing edge flap for a rotor blade |
| EP4008894A1 (en) * | 2020-12-02 | 2022-06-08 | Siemens Gamesa Renewable Energy A/S | Rotor blade for a wind turbine |
| US20240167450A1 (en) * | 2021-03-10 | 2024-05-23 | Vestas Wind Systems A/S | A wind turbine blade |
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| DE102006022279B4 (en) * | 2006-05-11 | 2016-05-12 | Aloys Wobben | Rotor blade for a wind energy plant |
| ES2330500B1 (en) * | 2008-05-30 | 2010-09-13 | GAMESA INNOVATION & TECHNOLOGY, S.L. UNIPERSONAL | AEROGENERATOR SHOVEL WITH HYPERSUSTENTING ELEMENTS. |
| GB2462307A (en) * | 2008-08-01 | 2010-02-03 | Vestas Wind Sys As | Extension portion for wind turbine blade |
| GB2462308A (en) * | 2008-08-01 | 2010-02-03 | Vestas Wind Sys As | Extension portion for wind turbine blade |
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2011
- 2011-05-20 US US13/112,148 patent/US20120027588A1/en not_active Abandoned
-
2012
- 2012-05-16 DK DK201270257A patent/DK178360B1/en not_active IP Right Cessation
- 2012-05-18 CN CN2012101674178A patent/CN102797624A/en active Pending
- 2012-05-18 DE DE102012104317A patent/DE102012104317A1/en not_active Withdrawn
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103711655A (en) * | 2013-12-26 | 2014-04-09 | 中国科学院工程热物理研究所 | Large-thickness blunt-trailing-edge wind turbine blade |
| CN103711655B (en) * | 2013-12-26 | 2016-04-06 | 中国科学院工程热物理研究所 | The blunt trailing edge pneumatic equipment blades made of a kind of heavy thickness |
| CN105658954A (en) * | 2014-09-22 | 2016-06-08 | 最优叶片有限公司 | Wind turbine rotor blade |
| CN105658954B (en) * | 2014-09-22 | 2019-06-14 | 最优叶片有限公司 | Wind power plant rotor blade |
| CN107110112A (en) * | 2014-10-10 | 2017-08-29 | 维斯塔斯风力系统有限公司 | wind turbine blade with trailing edge flap |
| US10830203B2 (en) | 2014-10-10 | 2020-11-10 | Vestas Wind Systems A/S | Wind turbine blade having a trailing edge flap |
| CN110892149A (en) * | 2017-07-20 | 2020-03-17 | 通用电气公司 | Airflow configuration for wind turbine rotor blades |
Also Published As
| Publication number | Publication date |
|---|---|
| DK178360B1 (en) | 2016-01-11 |
| DE102012104317A1 (en) | 2012-11-22 |
| US20120027588A1 (en) | 2012-02-02 |
| DK201270257A (en) | 2012-11-21 |
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Application publication date: 20121128 |