CN103485973B - A kind of pneumatic equipment blades with tip vane - Google Patents
A kind of pneumatic equipment blades with tip vane Download PDFInfo
- Publication number
- CN103485973B CN103485973B CN201310316916.3A CN201310316916A CN103485973B CN 103485973 B CN103485973 B CN 103485973B CN 201310316916 A CN201310316916 A CN 201310316916A CN 103485973 B CN103485973 B CN 103485973B
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- Prior art keywords
- empennage
- pneumatic equipment
- equipment blades
- angle
- tip
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- 238000006243 chemical reaction Methods 0.000 claims abstract description 14
- 230000008859 change Effects 0.000 claims description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 108010066278 cabin-4 Proteins 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 230000003750 conditioning effect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
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
-
- 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
- F05B2240/307—Blade tip, e.g. winglets
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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
Abstract
The application proposes a kind of pneumatic equipment blades with tip vane, including: blade tip, tip vane；Wherein, described tip vane, farther include: empennage connection member, the first empennage and the second empennage；First empennage and the second empennage are connected with one end of described empennage connection member simultaneously and constitute dovetail configuration, and the other end fit of described empennage connection member is fixed on described blade tip thus described first empennage and the second empennage have angle with described pneumatic equipment blades shape respectively；And the first empennage is positioned at the side, windward side of described pneumatic equipment blades, the second empennage is positioned at the lee face side of described pneumatic equipment blades, tangentially extending all in flat structure and along described pneumatic equipment blades rotational trajectory of described first empennage and the second empennage.The application effectively improves the aerodynamic characteristic of wind energy conversion system, surface load, reduces tip loss and aerodynamic noise.
Description
Technical field
The application relates to energy technology field, particularly relates to a kind of pneumatic equipment blades with tip vane.
Background technology
Wind energy is as the regenerative resource of a kind of cleaning, in the past ten years due to the energy, environment, gas
Time problem has obtained rapid development.Obviously, the spatter property of wind energy, recyclability and large-scale application thereof
Technology increasingly mature, makes wind-power electricity generation be increasingly becoming in new energy field in addition to nuclear energy, technology is the most ripe,
Most exploit condition and the most promising generation mode.
One typical Wind turbine by rotor, wheel hub, blade, gear-box and power drive system, send out
Motor, PCU Power Conditioning Unit, the control of software and monitoring.Although the maximal efficiency of Wind turbine in theory
It is 59%, the leaf that modern large scale wind power machine designs due to the aerodynamic efficiency that have employed more advanced person
The power system component that sheet, modern control theory and use are more powerful so that the performance of Wind turbine is always
Increasing steadily.
But, during wind energy conversion system actual motion, blade tip is by the wind surface of the blades such as blade body drive or wind-force
Pressure bigger.The blade tip lee face generation turnup to blade can be made for a long time thus cause tip loss, leaf
Point loss can cause blade not produce lift, largely effects on the work efficiency of wind energy conversion system.
Summary of the invention
The main purpose of the application is to provide a kind of pneumatic equipment blades with tip vane, existing to solve
With the presence of the problem of technology, tip vane can be arranged on existing wind field pneumatic equipment blades as blade adapter
Go up or on the blade of coming of new, to reach to improve generating efficiency, reduce the mesh that wind field wind energy conversion system tail disturbs
's.Wherein: including: blade tip, tip vane；Wherein, described tip vane, farther include: tail
Wing connection member, the first empennage and the second empennage；First empennage and the second empennage even with described empennage simultaneously
One end of relay part is connected and constitutes dovetail configuration, and the other end fit of described empennage connection member is fixed on institute
State on blade tip thus described first empennage and the second empennage have angle with described pneumatic equipment blades shape respectively；
And the first empennage is positioned at the side, windward side of described pneumatic equipment blades, the second empennage is positioned at described wind energy conversion system
The lee face side of blade, described first empennage and the second empennage are all in flat structure and along described wind energy conversion system
Blade rotational trajectory tangentially extending.
Further, described first empennage/the second empennage chord line at wingtip and the wing at wing root
The string of a musical instrument has a torsion angle thus forms a torsion structure at described wingtip so that described wind energy conversion system leaf
Tangential along described pneumatic equipment blades rotational trajectory of the wing root of the first empennage/the second empennage described in when sheet rotates
Cutting air, and the wingtip of described first empennage/the second empennage is along described pneumatic equipment blades rotational trajectory
Tangentially intercept air, thus reduce tip loss and blade tip Vortex Shedding structure with reach to alleviate wind energy conversion system it
Between tail interference.
Further, described torsion structure is to be turned round by the trailing edge forward edge of described first empennage/the second empennage
Turn, or, the leading edge of described first empennage/the second empennage reverse to trailing edge.
Further, the angle of described first empennage and pneumatic equipment blades and described second empennage and wind energy conversion system
The angle of blade is unequal.
Further, described first empennage is 45 degree of-135 degree with the angle of described pneumatic equipment blades, institute
The angle stating the second empennage and described pneumatic equipment blades is 45 degree of-135 degree；Described first empennage/the second tail
When the angle of the wing and described pneumatic equipment blades is in 45 degree to 90 degree, described first empennage/the second empennage
Warp is to the side of described pneumatic equipment blades thus wraps described blade tip and empennage connection member；Described
When the angle of one empennage/the second empennage and described pneumatic equipment blades is in 90 degree to 135 degree, described first
Empennage and the second empennage stretch out to the side away from described pneumatic equipment blades.
Further, described first empennage and the second empennage are respectively along described pneumatic equipment blades rotational trajectory
Vertical section on projection between there is an angle of sweep, described first empennage and the leading edge face of the second empennage
Towards the direction of rotation along described pneumatic equipment blades, the trailing edge of described first empennage and the second empennage facing away to
Direction of rotation along described pneumatic equipment blades.
Further, the size of described first empennage is more than the second empennage.
Further, described empennage connection member has a movable connection structure, described empennage connection member
Install by described movable connection structure with the movable of described blade tip and change.
Further, described movable connection structure has size, the shape adapted with described blade tip, institute
State the extension that global shape is described blade tip shape of empennage connection member.
Further, the aerofoil profile of described first empennage and the second empennage is fusiformis structure.
The application compared with prior art remarkable result is as follows:
1) by the blade tip of pneumatic equipment blades is installed tip vane, it is achieved to wind energy conversion system aeroperformance,
Run safety, transient state wind load respond and anti-extreme loads ability.
2) tip vane installed for tip loss in this application, can carry out phase according to different demands
The replacing answered, to be suitable for the different application at high wind speed or low wind speeds.
Accompanying drawing explanation
Accompanying drawing described herein is used for providing further understanding of the present application, constitutes of the application
Point, the schematic description and description of the application is used for explaining the application, is not intended that the application's
Improper restriction.In the accompanying drawings:
Fig. 1 is the wind machine structure block diagram of prior art.
Fig. 2 is the tip vane front view according to the embodiment of the present application.
Fig. 3 be according to the embodiment of the present application tip vane along pneumatic equipment blades rotational trajectory tangential first
Structural representation.
Fig. 4 be according to the embodiment of the present application tip vane along pneumatic equipment blades Plane of rotation vertical first
Structural representation.
Fig. 5 be according to the embodiment of the present application tip vane along pneumatic equipment blades rotational trajectory tangential second
Structural representation.
Fig. 6 be according to the embodiment of the present application tip vane along pneumatic equipment blades Plane of rotation vertical second
Structural representation.
Fig. 7 is according to vertical along pneumatic equipment blades rotational trajectory of tip vane in the embodiment of the present application
Perspective view on tangent plane.
Fig. 8 a is according to the torsion structure schematic diagram of tip vane in the embodiment of the present application.
Fig. 8 b is the schematic perspective view of tip vane in Fig. 8 a.
Fig. 9 a is according to another torsion structure schematic diagram of tip vane in the embodiment of the present application.
Fig. 9 b is the schematic perspective view of tip vane in Fig. 9 a.
Involved element and corresponding label in accompanying drawing, as follows:
Detailed description of the invention
For making the purpose of the application, technical scheme and advantage clearer, below in conjunction with accompanying drawing and specifically real
Execute example, the application is described in further detail.
The core idea of the application:
As it is shown in figure 1, the horizontal-shaft wind turbine of prior art, including: blade 1, blade tip 2, wheel hub
3, cabin 4 and pylon 5 form.When blade 1 rotating operation, can be with leaf at the blade tip of blade 1
The rotation of sheet 1 produces a tail flow field.This tail flow field has and presents multi-helical structure
Eddy current.When eddy current flows around blade tip, the upper and lower surface at blade tip section can produce pressure differential so that whirlpool
Stream produces at blade tip and streams, and this means that the circular rector at blade tip reduces, thus causes torque to reduce,
Making blade not produce lift, this loss is referred to as tip loss.Obviously, tip loss will necessarily affect
The performance of wind energy conversion system.
And by description above, tip loss is primarily due to the structure of blade tip and streaming to be caused
, clearly can change the impact streamed by the size and structure changing blade tip itself thus solve leaf
Point loss.But, the direct size changing blade tip itself and structure can largely effect on the gas of pneumatic equipment blades
Dynamic characteristic, the reduction of the performance that this impact is caused is considerably beyond avoiding tip loss to be brought
Income, therefore can not solve tip loss by the size and structure that directly change blade tip itself.Institute
To consider to revise the structure at blade tip by Circumscribed structure, so reduce tip loss.
As shown in figures 2-6, a kind of pneumatic equipment blades 1 with tip vane, including: blade tip 2, leaf
Point winglet；Wherein,
Described tip vane, farther includes: empennage connection member the 223, first empennage 221 and second
With the one of described empennage connection member 223 while of empennage 222, the first empennage 221 and the second empennage 222
End is connected and constitutes dovetail configuration, and the other end fit of described empennage connection member 223 is fixed on described blade tip
On 2 thus described first empennage 221 and the second empennage 222 form one with described pneumatic equipment blades 1 respectively
Angle a, b.
And the first empennage 221 is positioned at the side, windward side 21 of described pneumatic equipment blades 1, the second empennage
222 lee face 22 sides being positioned at described pneumatic equipment blades 1, described first empennage 221 and the second tail
Tangential 24 extensions of the wing 222 rotational trajectory all in flat structure and along described pneumatic equipment blades 1, institute
State the leading edge 224 of the first empennage 221 and the second empennage 222 facing to the rotation along described pneumatic equipment blades 1
Turning direction, the trailing edge 225 of described first empennage 221 and the second empennage 222 is facing away to along described wind energy conversion system
The direction of rotation of blade 1.
Described first empennage 221 is disposed asymmetrically relative to pneumatic equipment blades 1 with the second empennage 222.
This asymmetric setting shows as the setting of angle and size:
1) described first empennage 221 is 45 degree of-135 degree with the angle a of described pneumatic equipment blades 1, institute
The angle b stating the second empennage 222 and described pneumatic equipment blades 1 is 45 degree of-135 degree.But described
The angle a of one empennage 221 and pneumatic equipment blades 1 and described second empennage 222 and pneumatic equipment blades 1
Angle b is the most unequal.Owing to the first empennage 221 is positioned at the side, windward side 21 of pneumatic equipment blades 1,
Its aerodynamic loading born is bigger, in general, and the first empennage 221 and the angle of pneumatic equipment blades 1
A is more than described second empennage 222 and the angle b of pneumatic equipment blades 1.
As shown in Figure 3,4, when being in 45 degree to 90 degree for angle a, angle b, the first empennage 221
With the second empennage 222 warp wind machine blade 1 side, thus wrap described blade tip 2 with empennage even
The fixing end of relay part 223.
As shown in Figure 5,6, when being in 90 degree to 135 degree for angle a, angle b, the first empennage 221
Stretch out to the side away from described pneumatic equipment blades 1 with the second empennage 222.
2) aerodynamic loading and due to the first empennage 221 born is bigger, the most described first empennage
The size of 221 is more than the second empennage 222, and the thickness of the such as first empennage 221, chord length, the span will
More than the second empennage 222.
Also having a movable connection structure in empennage connection member 223, described empennage connection member 223 is led to
Cross the installation movable with described blade tip 2 of described movable connection structure and change.Described movable connection structure
There is size, the shape adapted with described blade tip 2, the global shape of described empennage connection member 223
Extension for described blade tip 2 shape.Wind energy conversion system in varying environment is can be implemented in by movable connection structure
Select to be suitable for the tip vane of current environment.
The cross section of the aerofoil profile of the first empennage 221 and the aerofoil profile of the second empennage 222 (transversal along chord line
Face) in fusiformis structure.
Certainly, it is contemplated that the rationalization of actual application, in another embodiment, described first empennage
The aerofoil profile of aerofoil profile and the second empennage can also be symmetrical arranged, and the application is not limited to this.
As it is shown in fig. 7, be in the embodiment of the present application tip vane along described pneumatic equipment blades rotational trajectory
Perspective view on the vertical section of 23.
Described first empennage 221 and the second empennage 222 are along described pneumatic equipment blades rotational trajectory 23
Projection on vertical section is respectively provided with leading edge sweep α1、α2And/or trailing sweep β1、β2,
Leading edge sweep α1、α2It is leading edge 224 and the spanwise 25 of the first empennage 221/ second empennage 222
Angle, trailing sweep β1、β2It is trailing edge 225 and the wing of the first empennage 221/ second empennage 222
The angle in exhibition direction 25.It should be noted that before described first empennage 221 and the second empennage 222
Edge angle of sweep α1、α2Can be identical, it is also possible to different；Described first empennage 221 and the second empennage 222
Trailing sweep β1、β2Can be identical, it is also possible to different；First empennage 221/ second empennage 222
Leading edge sweep α1、α2With trailing sweep β1、β2Between can be identical, it is also possible to different.
Generally, because the leading edge of described first empennage 221 and the second empennage 222 is facing to along described
The direction of rotation of pneumatic equipment blades 1, the trailing edge of described first empennage 221 and the second empennage 222 facing away to
Along the direction of rotation of described pneumatic equipment blades 1, so the first empennage 221 and leading edge of the second empennage 222
Angle of sweep α1、α2And/or trailing sweep β1、β2Angle arrange the biggest, described first empennage 221
The most sharp-pointed with the shape that the second empennage 222 is constituted, the rotary speed of described pneumatic equipment blades can be made to increase.
As shown in Fig. 8 a, 8b, 9a and 9b, for the twist-tie of another tip vane in the embodiment of the present application
Structure schematic diagram.
Described tip vane has and leading edge sweep α shown in Fig. 51、α2And/or trailing edge sweepback
Angle beta1、β2, do not repeat them here.
Additionally, described first empennage 221/ second empennage 222 is extended to along chord length direction by wing root 226
There occurs time at wingtip 227 that torsion forms torsion structure, this torsion structure can make described first empennage
221/ second empennage 222 forms a windward side 21 at wingtip 227, and this torsion structure is not limited to court
To side (in Fig. 3 phase between the first empennage 221/ second empennage 222 away from pneumatic equipment blades 1
The side of folder), it is also possible to towards (in Fig. 3 angle a, b place, side of pneumatic equipment blades 1
Side).
Specifically, described first empennage 221/ second empennage 222 chord line 228 at wingtip 227
With the chord line 228 at wing root 226, there is a torsion angle thus at described wingtip 227, form one
Torsion structure so that the wing of the first empennage 221/ second empennage 222 described in when described pneumatic equipment blades rotates
Root is along the tangential 24 cutting air of described pneumatic equipment blades rotational trajectory, and described first empennage 221/ the
The wingtip 227 of two empennages 222 intercepts air along tangential the 24 of described pneumatic equipment blades rotational trajectory.
Described first empennage 221 chord line 228 at wingtip 227 and the chord line at wing root 226
228 have the first torsion included angle X, described second empennage 222 chord line at wingtip with at wing root
Chord line there is the second torsion angle γ.Torsion can be as shown in Figure 8, by described first empennage
The trailing edge forward edge of 221/ second empennage 222 reverses.Torsion can also be as it is shown in figure 9, by described
The leading edge of one empennage 221/ second empennage 222 is reversed to trailing edge.The most any torsion, can be in institute
The wingtip 227 stating the first empennage 221/ second empennage 222 forms the face intercepting air.
The benchmark being initial 0 degree with first empennage 221/ second empennage 222 chord line 228 at wing root
Line (signal as in Fig. 8 a, 9a).As shown in Figure 8 a, the value model of described first torsion included angle X
Enclosing by-10 degree to 0 degree, described second reverses the span of angle γ by 0 degree to 10 degree；Such as figure
Shown in 9a, the span of described first torsion included angle X is by 0 degree to 10 degree, and described second reverses folder
The span of angle γ is spent to 0 degree by-10.
Therefore, comprehensive for, with first empennage 221/ second empennage 222 chord line at wing root 226
The datum line that 228 is initial 0 degree, first empennage 221/ second empennage 222 wing chord at wingtip 227
The span reversing angle that line 228 and the chord line 228 at wing root 226 are formed is by-10 degree
To 10 degree.
The foregoing is only embodiments herein, be not limited to the application, for this area
Technical staff for, the application can have various modifications and variations.All in spirit herein with principle
Within, any modification, equivalent substitution and improvement etc. made, should be included in claims hereof
Within the scope of.
Claims (9)
1. the pneumatic equipment blades with tip vane, it is characterised in that including: blade tip, blade tip are little
The wing；Wherein,
Described tip vane, farther includes: empennage connection member, the first empennage and the second empennage；
First empennage and the second empennage are connected with one end of described empennage connection member simultaneously and constitute dovetail knot
Structure, the other end fit of described empennage connection member be fixed on described blade tip thus described first empennage and
Second empennage has angle with described pneumatic equipment blades shape respectively；
And the first empennage is positioned at the side, windward side of described pneumatic equipment blades, the second empennage is positioned at described wind
The lee face side of power machine blade, described first empennage and the second empennage are all in flat structure and along described wind
Power machine blade rotational trajectory tangentially extending, described first empennage and the second empennage are respectively along described wind-force
There is between projection on the vertical section of machine blade rotational trajectory an angle of sweep, described first empennage and
The leading edge of two empennages is facing to the direction of rotation along described pneumatic equipment blades, described first empennage and the second tail
The trailing edge of the wing is facing away to the direction of rotation along described pneumatic equipment blades.
Pneumatic equipment blades the most according to claim 1, it is characterised in that
Described first empennage/the second empennage chord line at wingtip has one with the chord line at wing root
Reverse angle thus at described wingtip, form a torsion structure so that described pneumatic equipment blades rotates time institute
State the wing root tangential cutting air along described pneumatic equipment blades rotational trajectory of the first empennage/the second empennage, and
The wingtip of described first empennage/the second empennage tangentially intercepts air along described pneumatic equipment blades rotational trajectory,
Thus reduce tip loss and blade tip Vortex Shedding structure to reach the tail interference alleviating between wind energy conversion system.
Pneumatic equipment blades the most according to claim 2, it is characterised in that
Described torsion structure is to be reversed by the trailing edge forward edge of described first empennage/the second empennage, or, by
The leading edge of described first empennage/the second empennage is reversed to trailing edge.
Pneumatic equipment blades the most according to claim 1, it is characterised in that
The angle of described first empennage and pneumatic equipment blades and described second empennage and the angle of pneumatic equipment blades
Unequal.
Pneumatic equipment blades the most according to claim 4, it is characterised in that
Described first empennage is 45 degree of-135 degree with the angle of described pneumatic equipment blades, described second empennage
It is 45 degree of-135 degree with the angle of described pneumatic equipment blades；
When the angle of described first empennage/the second empennage and described pneumatic equipment blades is in 45 degree to 90 degree,
Described first empennage/the second empennage warp to the side of described pneumatic equipment blades thus wraps described blade tip
With empennage connection member；Described first empennage/the second empennage is in 90 with the angle of described pneumatic equipment blades
When degree is to 135 degree, described first empennage and the second empennage stretch out to the side away from described pneumatic equipment blades.
Pneumatic equipment blades the most according to claim 1, it is characterised in that
The size of described first empennage is more than the second empennage.
Pneumatic equipment blades the most according to claim 1, it is characterised in that
Described empennage connection member has a movable connection structure, and described empennage connection member is by described work
The structure that is dynamically connected is installed with the movable of described blade tip and change.
Pneumatic equipment blades the most according to claim 7, it is characterised in that
Described movable connection structure has size, the shape adapted with described blade tip, and described empennage connects
The global shape of parts is the extension of described blade tip shape.
Pneumatic equipment blades the most according to claim 1, it is characterised in that
The aerofoil profile of described first empennage and the second empennage is fusiformis structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310316916.3A CN103485973B (en) | 2013-07-25 | 2013-07-25 | A kind of pneumatic equipment blades with tip vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310316916.3A CN103485973B (en) | 2013-07-25 | 2013-07-25 | A kind of pneumatic equipment blades with tip vane |
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| Publication Number | Publication Date |
|---|---|
| CN103485973A CN103485973A (en) | 2014-01-01 |
| CN103485973B true CN103485973B (en) | 2016-08-10 |
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| CN201310316916.3A Expired - Fee Related CN103485973B (en) | 2013-07-25 | 2013-07-25 | A kind of pneumatic equipment blades with tip vane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2555965A (en) * | 2013-05-22 | 2018-05-16 | 4Navitas Green Energy Solutions Ltd | Wind turbine blade winglet |
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| KR20170129135A (en) * | 2015-03-16 | 2017-11-24 | 엔티엔 가부시키가이샤 | Wing cars and natural energy generating devices equipped with them |
| JP6632805B2 (en) * | 2015-03-19 | 2020-01-22 | Ntn株式会社 | Impeller and renewable energy generator |
| CN104863791A (en) * | 2015-05-20 | 2015-08-26 | 上海交通大学 | Novel wind turbine blade |
| CN104963807B (en) * | 2015-07-16 | 2017-08-22 | 青岛安华新元风能股份有限公司 | Blade of wind-driven generator |
| CN106089572A (en) * | 2016-08-11 | 2016-11-09 | 中国华电科工集团有限公司 | A kind of two section type winglet reducing Axis Wind Turbine With A Tip Vane eddy current |
| CN112459962B (en) * | 2020-11-23 | 2021-11-02 | 重庆交通大学绿色航空技术研究院 | Wind power blade with tip end plate |
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| US5151610A (en) * | 1990-11-29 | 1992-09-29 | St Germain Jean | Wind machine with electric generators and secondary rotors located on rotating vertical blades |
| DE60226318T2 (en) * | 2001-04-23 | 2009-07-09 | Technical University Of Denmark | WIND TURBINE WITH SECONDARY ROTORS |
| CN1563707A (en) * | 2004-03-18 | 2005-01-12 | 上海交通大学 | Horizontal shaft wind mill with small sharp wing |
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| Title |
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| 不同叶尖小翼风力机在不同地区输出功率的分析与比较;代元军等;《太阳能学报》;20120331;第33卷(第3期);第425页-第426页，表1，图1 * |
| 风力机加V型小翼后的性能变化;贾瑞博;《可再生能源》;20110228;第29卷(第1期);第98-99页，图1-3 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2555965A (en) * | 2013-05-22 | 2018-05-16 | 4Navitas Green Energy Solutions Ltd | Wind turbine blade winglet |
| GB2555965B (en) * | 2013-05-22 | 2018-09-05 | 4Navitas Green Energy Solutions Ltd | Wind turbine blade winglet |
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| Publication number | Publication date |
|---|---|
| CN103485973A (en) | 2014-01-01 |
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