CN103485973A - Wind turbine blade with tip vane - Google Patents
Wind turbine blade with tip vane Download PDFInfo
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- CN103485973A CN103485973A CN201310316916.3A CN201310316916A CN103485973A CN 103485973 A CN103485973 A CN 103485973A CN 201310316916 A CN201310316916 A CN 201310316916A CN 103485973 A CN103485973 A CN 103485973A
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- empennage
- pneumatic equipment
- blades made
- equipment blades
- tip
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- 238000006243 chemical reaction Methods 0.000 claims description 9
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 3
- 230000008859 change Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 108010066278 cabin-4 Proteins 0.000 description 1
- 230000003750 conditioning effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000009257 reactivity Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
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Classifications
-
- 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
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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
- 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 invention provides a wind turbine blade with a tip vane. The wind turbine blade with the tip vane comprises a tip and a tip vane, wherein the tip vane further comprises an empennage connection component, a first empennage and a second empennage; the first empennage and the second empennage are simultaneously connected with one end of the empennage connection component to form a forked tail structure; the other end of the empennage connection component is sheathed and fixedly arranged on the tip; therefore an included angle is respectively formed between the first empennage and the wind turbine blade as well as between the second empennage and the wind turbine blade; the first empennage is positioned on the windward side of the wind turbine blade; the second empennage is positioned on the lee side of the wind turbine blade; and the first empennage and the second empennage are both of the flat structure and tangentially extend along the rotation track of the wind turbine blade. According to the wind turbine blade with the tip vane, which is disclosed by the invention, the aerodynamic characteristics and the surface load of the wind turbine are effectively improved, and the tip loss and the aerodynamic noise are reduced.
Description
Technical field
The application relates to energy technology field, relates in particular to a kind of pneumatic equipment blades made with tip vane.
Background technique
Wind energy is as a kind of clean renewable energy sources, in the past ten years because the energy, environment, Climatic issues have obtained development rapidly.Obviously, the spatter property of wind energy, recyclability and large-scale application technology thereof increasingly mature, become in new energy field except nuclear energy wind-power electricity generation day by day, and technology is the most ripe, tool exploitation condition and the most promising generation mode.
Typical Wind turbine is by control and the monitoring of rotor, wheel hub, blade, gear-box and power transmission system, generator, Power Conditioning Unit, software.Although the maximal efficiency of Wind turbine is 59% in theory, modern large scale wind power machine is due to the blade of the aerodynamic efficiency design that has adopted more advanced persons, modern control theory and the more powerful power system component of use, make the performance of Wind turbine always in steady increase.
Yet, during the wind energy conversion system actual motion, blade tip driven by blade body or the pressure of the wind-receiving face of the blades such as wind-force larger.Thereby can make for a long time blade tip cause tip loss to the lee face generation turnup of blade, tip loss can cause blade not produce lift, greatly affects the working efficiency of wind energy conversion system.
Summary of the invention
The application's main purpose is to provide a kind of pneumatic equipment blades made with tip vane, the problem existed to solve prior art, tip vane can be used as the blade adapter and is arranged on existing wind field pneumatic equipment blades made or on the blade of coming of new, to reach, improves generating efficiency, reduce the purpose that wind field wind energy conversion system tail disturbs.Wherein: comprising: blade tip, tip vane; Wherein, described tip vane further comprises: empennage connected element, the first empennage and the second empennage; The first empennage and the second empennage formation dovetail structure that is connected with an end of described empennage connected element, form an angle with described pneumatic equipment blades made respectively thereby the other end fit of described empennage connected element is fixed on described the first empennage and the second empennage on described blade tip simultaneously; And the first empennage is positioned at windward side one side of described pneumatic equipment blades made, the second empennage is positioned at lee face one side of described pneumatic equipment blades made, and described the first empennage and the second empennage all are flat structure and along the tangential extension of described pneumatic equipment blades made rotating locus.
Further, thereby described the first empennage/second empennage has a torsion angle at the chord line at wingtip place and chord line at the wing root place forms a torsion structure at described wingtip place, while making described pneumatic equipment blades made rotation, the wing root of described the first empennage/second empennage is along the tangential cutting air of described pneumatic equipment blades made rotating locus, and the wingtip of described the first empennage/second empennage is along the tangential obstruct air of described pneumatic equipment blades made rotating locus, thereby reduce tip loss and blade tip Vortex Shedding structure is disturbed to reach the tail alleviated between wind energy conversion system.
Further, described torsion structure reverses to leading edge for the trailing edge by described the first empennage/second empennage, or, by the leading edge of described the first empennage/second empennage, to trailing edge, reversed.
Further, the angle of the angle of described the first empennage and pneumatic equipment blades made and described the second empennage and pneumatic equipment blades made is unequal.
Further, the angle of described the first empennage and described pneumatic equipment blades made is 45 degree-135 degree, and the angle of described the second empennage and described pneumatic equipment blades made is 45 degree-135 degree; The angle of described the first empennage/second empennage and described pneumatic equipment blades made is when 45 degree to 90 are spent, thereby described the first empennage/second empennage warp wraps described blade tip and empennage connected element to a side of described pneumatic equipment blades made; The angle of described the first empennage/second empennage and described pneumatic equipment blades made is when 90 degree to 135 are spent, and described the first empennage and the second empennage stretch out to the side away from described pneumatic equipment blades made.
Further, described the first empennage and the second empennage have respectively a sweepback angle between the projection on the plumb cut along described pneumatic equipment blades made rotating locus, the leading edge of described the first empennage and the second empennage is facing to the sense of rotation along described pneumatic equipment blades made, and the trailing edge of described the first empennage and the second empennage is carried on the back towards the sense of rotation along described pneumatic equipment blades made.
Further, the size of described the first empennage is greater than the second empennage.
Further, described empennage connected element has a movable connection structure, and described empennage connected element is installed and changed by the activity of described movable connection structure and described blade tip.
Further, described movable connection structure has size, the shape adapted with described blade tip, the extension that the global shape of described empennage connected element is described blade tip shape.
Further, the aerofoil profile of described the first empennage and the second empennage is the fusiformis structure.
The application compared with prior art remarkable result is as follows:
1) by the blade tip to pneumatic equipment blades made, tip vane is installed, is realized wind energy conversion system aeroperformance, security of operation, transient state wind are carried to reactivity and anti-extreme loads ability.
2) tip vane of installing for tip loss in this application, can change accordingly according to different demands, the different application when being adapted at high wind speed or low wind speed.
The accompanying drawing explanation
Accompanying drawing described herein is used to provide the further understanding to the application, forms the application's a part, and the application's schematic description and description, for explaining the application, does not form the improper restriction to the application.In the accompanying drawings:
Fig. 1 is the wind energy conversion system structured flowchart of prior art.
Fig. 2 is the tip vane plan view according to the embodiment of the present application.
Fig. 3 is first structural representation tangential along the pneumatic equipment blades made rotating locus according to the embodiment of the present application tip vane.
Fig. 4 is first structural representation vertical along the pneumatic equipment blades made plane of rotation according to the embodiment of the present application tip vane.
Fig. 5 is second structural representation tangential along the pneumatic equipment blades made rotating locus according to the embodiment of the present application tip vane.
Fig. 6 is second structural representation vertical along the pneumatic equipment blades made plane of rotation according to the embodiment of the present application tip vane.
Fig. 7 is the perspective view on the plumb cut along the pneumatic equipment blades made rotating locus according to tip vane in the embodiment of the present application.
Fig. 8 a is the torsion structure schematic diagram according to 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 another torsion structure schematic diagram according to tip vane in the embodiment of the present application.
Fig. 9 b is the schematic perspective view of tip vane in Fig. 9 a.
Related element and corresponding label in accompanying drawing, as follows:
Embodiment
For the purpose, technological scheme and the advantage that make the application is clearer, below in conjunction with drawings and the specific embodiments, the application is described in further detail.
The application's core idea:
As shown in Figure 1, the horizontal-shaft wind turbine of prior art comprises: blade 1, blade tip 2, wheel hub 3, cabin 4 and pylon 5 form.When blade 1 rotating operation, at the blade tip place of blade 1, can produce a tail flow field with the rotation of blade 1.There is the eddy current that presents multi-helical structure in this tail flow field.When blade tip flows, in the upper and lower surface of blade tip section, can produce pressure difference when eddy current, make eddy current produce and stream at the blade tip place, this just means that the circular rector at blade tip reduces, thereby cause torque to reduce, make blade not produce lift, this loss is called tip loss.Obviously, tip loss will inevitably affect the performance of wind energy conversion system.
And the description by front is known, tip loss is mainly because the structure of blade tip and streaming causes, thereby is obviously to change the impact solution tip loss streamed by size and the structure that changes blade tip itself.But, directly change the size of blade tip itself and the aerodynamic characteristic that structure can affect pneumatic equipment blades made greatly, the reduction of the performance that this impact causes, considerably beyond the income of avoiding tip loss to bring, therefore can not solve tip loss by size and the structure of direct change blade tip itself.So consider to revise by Circumscribed structure the structure at blade tip place, reduce like this tip loss.
As shown in Fig. 2-6, a kind of pneumatic equipment blades made with tip vane 1, comprising: blade tip 2, tip vane; Wherein,
Described tip vane, further comprise: empennage connected element 223, the first empennage 221 and the second empennage 222, the first empennage 221 and the second empennage 222 are connected with an end of described empennage connected element 223 and form the dovetail structure simultaneously, thus the other end fit of described empennage connected element 223 be fixed on described blade tip 2 described the first empennage 221 and the second empennage 222 respectively with described pneumatic equipment blades made 1 formation one angle a, b.
And the first empennage 221 is positioned at windward side 21 1 sides of described pneumatic equipment blades made 1, the second empennage 222 is positioned at lee face 22 1 sides of described pneumatic equipment blades made 1, described the first empennage 221 and the second empennage 222 all are flat structure and extend along tangential 24 of the rotating locus of described pneumatic equipment blades made 1, the leading edge 224 of described the first empennage 221 and the second empennage 222 is facing to the sense of rotation along described pneumatic equipment blades made 1, and trailing edge 225 back ofs the body of described the first empennage 221 and the second empennage 222 are towards the sense of rotation along described pneumatic equipment blades made 1.
Described the first empennage 221 and the second empennage 222 are asymmetric setting with respect to pneumatic equipment blades made 1.This asymmetric setting shows as the setting of angle and size:
1) described the first empennage 221 is 45 degree-135 degree with the angle a of described pneumatic equipment blades made 1, and described the second empennage 222 is 45 degree-135 degree with the angle b of described pneumatic equipment blades made 1.But the angle b of the angle a of described the first empennage 221 and pneumatic equipment blades made 1 and described the second empennage 222 and pneumatic equipment blades made 1 is also unequal.Because the first empennage 221 is positioned at windward side 21 1 sides of pneumatic equipment blades made 1, its aerodynamic loading born is larger, and in general, the angle a of the first empennage 221 and pneumatic equipment blades made 1 is greater than the angle b of described the second empennage 222 and pneumatic equipment blades made 1.
As shown in Figure 3,4, while spending in 45 degree to 90 for angle a, angle b, the first empennage 221 and the second empennage 222 warps are to pneumatic equipment blades made 1 one sides, thereby wrap the fixed end of described blade tip 2 and empennage connected element 223.
As shown in Figure 5,6, while spending in 90 degree to 135 for angle a, angle b, the first empennage 221 and the second empennage 222 stretch out to the side away from described pneumatic equipment blades made 1.
2) and the aerodynamic loading born due to the first empennage 221 larger, therefore the size of described the first empennage 221 is greater than the second empennage 222, for example the thickness of the first empennage 221, chord length, the span all are greater than the second empennage 222.
Also have a movable connection structure on empennage connected element 223, described empennage connected element 223 is installed and is changed by described movable connection structure and 2 activities of described blade tip.Described movable connection structure has size, the shape adapted with described blade tip 2, the extension that the global shape of described empennage connected element 223 is described blade tip 2 shapes.Can realize the tip vane of the applicable current environment of wind energy conversion system selection in varying environment by movable connection structure.
The cross section of the aerofoil profile of the aerofoil profile of the first empennage 221 and the second empennage 222 (along the cross section of chord line) is the fusiformis structure.
Certainly, consider the rationalization of practical application, in another embodiment, the aerofoil profile of the aerofoil profile of described the first empennage and the second empennage also can be symmetrical arranged, and the application is not limited to this.
As shown in Figure 7, be the perspective view of tip vane in the embodiment of the present application on the plumb cut along described pneumatic equipment blades made rotating locus 23.
Described the first empennage 221 and the second projection of empennage 222 on the plumb cut along described pneumatic equipment blades made rotating locus 23 have respectively a leading edge sweep α
1, α
2and/or trailing sweep β
1, β
2, leading edge sweep α
1, α
2be the angle of leading edge 224 with the spanwise 25 of the first empennage 221/ second empennage 222, trailing sweep β
1, β
2be the trailing edge 225 of the first empennage 221/ second empennage 222 and the angle of spanwise 25.It should be noted that the leading edge sweep α of described the first empennage 221 and the second empennage 222
1, α
2can be identical, also can be different; The trailing sweep β of described the first empennage 221 and the second empennage 222
1, β
2can be identical, also can be different; The leading edge sweep α of the first empennage 221/ second empennage 222
1, α
2with trailing sweep β
1, β
2between can be identical, also can be different.
In general, because the leading edge of described the first empennage 221 and the second empennage 222 is facing to the sense of rotation along described pneumatic equipment blades made 1, the trailing edge back of the body of described the first empennage 221 and the second empennage 222 is towards the sense of rotation along described pneumatic equipment blades made 1, so the leading edge sweep α of the first empennage 221 and the second empennage 222
1, α
2and/or trailing sweep β
1, β
2the angle setting larger, the shape that described the first empennage 221 and the second empennage 222 form is more sharp-pointed, can make the rotational speed of described pneumatic equipment blades made increase.
As shown in Fig. 8 a, 8b, 9a and 9b, it is the torsion structure schematic diagram of another tip vane in the embodiment of the present application.
Described tip vane has and the leading edge sweep α shown in Fig. 5
1, α
2and/or trailing sweep β
1, β
2, do not repeat them here.
In addition, described the first empennage 221/ second empennage 222 has been occurred when the chord length direction extends to wingtip 227 place by wing root 226 places to reverse and has formed torsion structure, this torsion structure can make described the first empennage 221/ second empennage 222 form a windward side 21 at wingtip 227 places, this torsion structure is not limited to towards the side away from pneumatic equipment blades made 1 (side folded between the first empennage 221/ second empennage 222 in Fig. 3), also can be towards a side (side at angle a, b place in Fig. 3) of pneumatic equipment blades made 1.
Specifically, thereby described the first empennage 221/ second empennage 222 has a torsion angle at the chord line 228 at wingtip 227 places and chord line 228 at wing root 226 places forms a torsion structure at described wingtip 227 places, while making described pneumatic equipment blades made rotation, the wing root of described the first empennage 221/ second empennage 222 cuts air along tangential 24 of described pneumatic equipment blades made rotating locus, and the wingtip 227 of described the first empennage 221/ second empennage 222 intercepts air along tangential 24 of described pneumatic equipment blades made rotating locus.
Described the first empennage 221 has the first torsion included angle X at the chord line 228 at wingtip 227 places with the chord line 228 at wing root 226 places, and described the second empennage 222 has the second torsion angle γ at the chord line at wingtip place and the chord line at the wing root place.Torsion can be as shown in Figure 8, by the trailing edge of described the first empennage 221/ second empennage 222, to leading edge, is reversed.Reversing can be also as shown in Figure 9, by the leading edge of described the first empennage 221/ second empennage 222, to trailing edge, is reversed.No matter any torsion, can form the face that intercepts air at the wingtip 227 of described the first empennage 221/ second empennage 222.
The reference line (as the signal in Fig. 8 a, 9a) that the chord line 228 of the first empennage 221/ second empennage 222 at the wing root place of take is initial 0 degree.As shown in Figure 8 a, the described first span of reversing included angle X is spent to 0 degree by-10, and described second reverses the span of angle γ by 0 degree to 10 degree; As shown in Fig. 9 a, the described first span of reversing included angle X is by 0 degree to 10 degree, and the described second span of reversing angle γ is spent to 0 degree by-10.
Therefore, comprehensive, the reference line that first empennage 221/ second empennage 222 of take is initial 0 degree at the chord line 228 at wing root 226 places, the first empennage 221/ second empennage 222 in the span of the chord line 228 at wingtip 227 places and the formed torsion angle of chord line 228 at wing root 226 places by-10 degree to 10 degree.
The foregoing is only the application's embodiment, be not limited to the application, for a person skilled in the art, the application can have various modifications and variations.All within the application's spirit and principle, any modification of doing, be equal to replacement, improvement etc., within all should being included in the application's claim scope.
Claims (10)
1. the pneumatic equipment blades made with tip vane, is characterized in that, comprising: blade tip, tip vane; Wherein,
Described tip vane further comprises: empennage connected element, the first empennage and the second empennage;
The first empennage and the second empennage formation dovetail structure that is connected with an end of described empennage connected element, form an angle with described pneumatic equipment blades made respectively thereby the other end fit of described empennage connected element is fixed on described the first empennage and the second empennage on described blade tip simultaneously;
And the first empennage is positioned at windward side one side of described pneumatic equipment blades made, the second empennage is positioned at lee face one side of described pneumatic equipment blades made, and described the first empennage and the second empennage all are flat structure and along the tangential extension of described pneumatic equipment blades made rotating locus.
2. pneumatic equipment blades made according to claim 1, is characterized in that,
Thereby described the first empennage/second empennage has a torsion angle at the chord line at wingtip place and chord line at the wing root place forms a torsion structure at described wingtip place, while making described pneumatic equipment blades made rotation, the wing root of described the first empennage/second empennage is along the tangential cutting air of described pneumatic equipment blades made rotating locus, and the wingtip of described the first empennage/second empennage is along the tangential obstruct air of described pneumatic equipment blades made rotating locus, thereby reduce tip loss and blade tip Vortex Shedding structure is disturbed to reach the tail alleviated between wind energy conversion system.
3. pneumatic equipment blades made according to claim 2, is characterized in that,
Described torsion structure reverses to leading edge for the trailing edge by described the first empennage/second empennage, or, by the leading edge of described the first empennage/second empennage, to trailing edge, reversed.
4. pneumatic equipment blades made according to claim 1, is characterized in that,
The angle of the angle of described the first empennage and pneumatic equipment blades made and described the second empennage and pneumatic equipment blades made is unequal.
5. pneumatic equipment blades made according to claim 4, is characterized in that,
The angle of described the first empennage and described pneumatic equipment blades made is 45 degree-135 degree, and the angle of described the second empennage and described pneumatic equipment blades made is 45 degree-135 degree;
The angle of described the first empennage/second empennage and described pneumatic equipment blades made is when 45 degree to 90 are spent, thereby described the first empennage/second empennage warp wraps described blade tip and empennage connected element to a side of described pneumatic equipment blades made; The angle of described the first empennage/second empennage and described pneumatic equipment blades made is when 90 degree to 135 are spent, and described the first empennage and the second empennage stretch out to the side away from described pneumatic equipment blades made.
6. pneumatic equipment blades made according to claim 1, is characterized in that,
Described the first empennage and the second empennage have respectively a sweepback angle between the projection on the plumb cut along described pneumatic equipment blades made rotating locus, the leading edge of described the first empennage and the second empennage is facing to the sense of rotation along described pneumatic equipment blades made, and the trailing edge of described the first empennage and the second empennage is carried on the back towards the sense of rotation along described pneumatic equipment blades made.
7. pneumatic equipment blades made according to claim 1, is characterized in that,
The size of described the first empennage is greater than the second empennage.
8. pneumatic equipment blades made according to claim 1, is characterized in that,
Described empennage connected element has a movable connection structure, and described empennage connected element is installed and changed by the activity of described movable connection structure and described blade tip.
9. pneumatic equipment blades made according to claim 8, is characterized in that,
Described movable connection structure has size, the shape adapted with described blade tip, the extension that the global shape of described empennage connected element is described blade tip shape.
10. pneumatic equipment blades made according to claim 1, is characterized in that,
The aerofoil profile of described the first empennage and the second empennage is the 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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| CN103485973B 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 (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104863791A (en) * | 2015-05-20 | 2015-08-26 | 上海交通大学 | Novel wind turbine blade |
| CN104963807A (en) * | 2015-07-16 | 2015-10-07 | 青岛安华新元风能股份有限公司 | Wind driven generator blade |
| WO2016148016A1 (en) * | 2015-03-16 | 2016-09-22 | Ntn株式会社 | Impeller and natural energy power generation device provided with same |
| JP2016176373A (en) * | 2015-03-19 | 2016-10-06 | Ntn株式会社 | Blade wheel and natural energy 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 |
| CN108980107A (en) * | 2018-08-09 | 2018-12-11 | 浙江大学 | A kind of bionical fan vane |
| CN112459962A (en) * | 2020-11-23 | 2021-03-09 | 重庆交通大学绿色航空技术研究院 | Wind power blade with specially-made blade tip end plate |
| CN108980107B (en) * | 2018-08-09 | 2024-04-12 | 浙江大学 | Bionic fan blade |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB201309184D0 (en) * | 2013-05-22 | 2013-07-03 | 4Navitas Green Energy Solutions Ltd | Vertical axis wind turbine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4003676A (en) * | 1973-10-23 | 1977-01-18 | Sweeney Thomas E | Windmill blade and processes related thereto |
| US5151610A (en) * | 1990-11-29 | 1992-09-29 | St Germain Jean | Wind machine with electric generators and secondary rotors located on rotating vertical blades |
| JP2004084590A (en) * | 2002-08-28 | 2004-03-18 | Mitsubishi Heavy Ind Ltd | Wind mill with winglet |
| CN1563707A (en) * | 2004-03-18 | 2005-01-12 | 上海交通大学 | Horizontal shaft wind mill with small sharp wing |
| DE60226318T2 (en) * | 2001-04-23 | 2009-07-09 | Technical University Of Denmark | WIND TURBINE WITH SECONDARY ROTORS |
| JP2010209863A (en) * | 2009-03-12 | 2010-09-24 | Tokyo Electric Power Co Inc:The | Blade structure and wind power generator |
-
2013
- 2013-07-25 CN CN201310316916.3A patent/CN103485973B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4003676A (en) * | 1973-10-23 | 1977-01-18 | Sweeney Thomas E | Windmill blade and processes related thereto |
| 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 |
| JP2004084590A (en) * | 2002-08-28 | 2004-03-18 | Mitsubishi Heavy Ind Ltd | Wind mill with winglet |
| CN1563707A (en) * | 2004-03-18 | 2005-01-12 | 上海交通大学 | Horizontal shaft wind mill with small sharp wing |
| JP2010209863A (en) * | 2009-03-12 | 2010-09-24 | Tokyo Electric Power Co Inc:The | Blade structure and wind power generator |
Non-Patent Citations (2)
| Title |
|---|
| 代元军等: "不同叶尖小翼风力机在不同地区输出功率的分析与比较", 《太阳能学报》 * |
| 贾瑞博: "风力机加V型小翼后的性能变化", 《可再生能源》 * |
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