CN203515955U - Thickened high-aerodynamic-performance wind turbine blade - Google Patents
Thickened high-aerodynamic-performance wind turbine blade Download PDFInfo
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- CN203515955U CN203515955U CN201320535471.3U CN201320535471U CN203515955U CN 203515955 U CN203515955 U CN 203515955U CN 201320535471 U CN201320535471 U CN 201320535471U CN 203515955 U CN203515955 U CN 203515955U
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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
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Abstract
The utility model discloses a thickened high-aerodynamic-performance wind turbine blade and belongs to the technical field of wind energy utilization. A three-dimensional structure on the surface of the wing-type part of the blade is generated by wing-type curves of ten wing-type faces in a continuous and smooth transition mode, and each wing-type-face wing-type curve is composed of a leeside curve and a windward side curve. It is defined that the origin of a coordinate system is the leading edge point of the first wing-type-face wing-type curve, the blade stretching direction is the positive direction of the Z-axis, the direction of a wing wheel shaft is the Y-axis direction, and the other direction perpendicular to the Z-axis and the Y-axis at the same time is the X-axis direction. The ten wing-type faces are parallel to the XOY plane and are sequentially arrayed in the positive direction of the Z-axis; each wing-type face rotates by a certain angle within a plane, where the corresponding leading edge point is located, perpendicular to the Z-axis with the corresponding leading edge point as the center. Due to the adoption of the thickening design of the leading edge points and trailing edge points of the blade, on the premise that high aerodynamic performance of the blade is guaranteed and the blade has high bending resistance and fatigue damage resistance performance, the blade has the characteristics of being low in starting wind speed and working noise.
Description
Technical field
The utility model relates to a kind of pneumatic equipment blades made, is specifically related to a kind of thickening type pneumatic equipment blades made, belongs to Wind Power Utilization technical field.
Background technique
Wind energy conversion system is to draw wind energy by wind wheel blade, and then mechanical energy is converted into the device of electric energy.Wind wheel is the power unit of wind-driven generator key, is determining to draw wind energy efficiency.Wind wheel is comprised of blade, wheel hub and axle, and generator is realized and being connected with the axle of wind wheel by main shaft, and effect is that the mechanical energy of wind wheel output is converted into electric energy output.As can be seen here, the blade of wind wheel is determining the wind energy utilization of wind energy conversion system.And pneumatic equipment blades made is comprised of vane airfoil profile and blade root two-part, vane airfoil profile part-structure is determining that the aeroperformance of wind wheel is good and bad, and leaf root part is mainly undertaken being connected of vane airfoil profile part and wheel hub, plays that blade supports and the effect of location.
The structure of tradition wind-driven generator blade wing section derives from aviation aerofoil profile, causes traditional wind mill airfoil blade in use to have following key technology defect:
1, when operating in low reynolds number, blade inlet edge is more responsive to the variation of roughness, and it is serious that ratio of lift coefficient to drag coefficient worsens phenomenon, has greatly affected the stationarity of its power stage.
2, in wider tip-speed ratio scope internal power index variation, easily producing fluctuation, and stall phenomenon easily occurs, also there is larger wave properties in power peak.
3, wind energy conversion system startup wind speed is had relatively high expectations, and is not suitable for the utilization of low velocity wind energy resource.
4, wind energy utilization is low, causes the whole wind-resources effective rate of utilization of wind-power generating system low.
5, aerodynamic noise in service is large, affects surrounding environment.
6, for pursuing high aeroperformance, it is thin that vane airfoil profile designed, and especially at trailing edge point place, easily ruptures, and easily makes blade generation fatigue damage, causes wind energy conversion system equipment accident multiple.
The existence of above problem, is seriously restricting effective utilization of wind energy and the development process of wind energy conversion system industry.
Model utility content
In view of this, the utility model provides a kind of thickening type high aeroperformance pneumatic equipment blades made, vane airfoil profile front and rear edges point place is thickeied, can make pneumatic equipment blades made on the basis of high aeroperformance, possess that the wind speed of startup is low, power coefficient is high and power out-put characteristic characteristic stably having, the blade of thickening has high bending resistance and antifatigue damage performance simultaneously.
In order to solve the problems of the technologies described above, the utility model is achieved in that the high aeroperformance pneumatic equipment blades made of a kind of thickening type, vane airfoil profile and blade root two-part, consist of, the three-dimensional structure of vane airfoil profile part surface is generated by ten continuous smooth transition of airfoil Curve of wing; Described each airfoil Curve of wing is comprised of lee face curve and windward side curve respectively; The initial point of definition system of coordinates is the leading edge point of the first airfoil Curve of wing, the postive direction that blade and blade exhibition direction is Z axis, and the direction of rotor shaft is Y direction, another is X-axis direction perpendicular to the direction of Z axis and Y-axis simultaneously; The 0 ° of angle of rotation that simultaneously defines described ten airfoil Curve of wings is positioned on X forward axle, and Y forward axle is 90 ° of angle of rotation; , the leading edge point coordinate of described ten airfoil Curve of wings is followed successively by (0,0,0), (0 by affiliated spatial position, 0,70), (0,0,140), (0,0,210), (0,0,280), (0,0,350), (0,0,420), (0,0,490), (0,0,560), (0,0,595); Described ten airfoils are parallel to respectively X0Y plane and along the postive direction of Z axis, arrange successively, described ten airfoils cross leading edge point separately and perpendicular to the plane of Z axis in the angle of rotating centered by its leading edge point be followed successively by: 28.95 °, 20.10 °, 14.00 °, 10.07 °, 7.69 °, 6.26 °, 5.19 °, 3.87 °, 1.71 °, 0.12 °; Vane airfoil profile front and rear edges point place thickeies, and vane thickness is increased;
Blade root is comprised of holding part and changeover portion, and holding part is rectangular configuration, is processed with the bolt hole of Y direction on it, and bolt hole is used for being fixedly connected with wind turbine hub, the first airfoil of the changeover portion section of being connected and fixed and vane airfoil profile part;
The coordinate figure that described ten airfoil lee face curves and windward side curve are corresponding is as follows:
The coordinate figure that the first airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the second airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 3rd airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 4th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 5th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 6th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 7th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 8th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 9th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the tenth airfoil lee face curve and windward side curve are corresponding meets respectively:
The concrete production of blade realized technique, can define and be connected the processing mold that smooth transition generates blade profile structure with three dimensional space relative position relation by above-mentioned ten feature airfoil curve practical structures, and then by realize the physical treatment of blade such as techniques such as mold injections.
Beneficial effect:
1) low startup wind speed.The actual test of this vanes, can startup work under 2.9m/s incoming flow wind speed, and more traditional airfoil fan is greater than the startup wind speed of 3m/s, has obvious advantage, is more suitable for the utilization of low-quality wind energy in low wind speed area or city.
2) high power coefficient.The actual test of this vanes, at 4～10m/s(10m/s, be design rated wind speed) in incoming flow wind speed range, the blade that power coefficient all designs apparently higher than American classic aerofoil profile NACA4415, and in 7～10m/s incoming flow wind speed range, power coefficient all reaches 40%(in Table 1), in Miniature Wind Turbine Blades, belong to high power coefficient blade.
3) good output stationarity and stalling characteristics.The actual test of this vanes is design rated wind speed at 4～10m/s(10m/s) in incoming flow wind speed range, power out-put characteristic is steady, is obviously better than traditional airfoil fan, and does not find the generation of stall phenomenon.
4) good aerodynamic noise.The actual test of this vanes, starts noise and is starkly lower than traditional airfoil fan.
5) adopt thick Airfoil Design blade, blade has high bending resistance and antifatigue damage performance.
Accompanying drawing explanation
Fig. 1 is form structure schematic diagram of the present utility model;
Fig. 2 is perspective view of the present utility model;
Fig. 3 is the distribution maps of of the present utility model ten airfoil Curve of wings on blade;
Fig. 4 is the profile diagram of ten feature airfoil Curve of wings.
Wherein: 1-the first airfoil, 2-the second airfoil, 3-the 3rd airfoil, 4-the 4th airfoil, 5-the 5th airfoil, 6-the 6th airfoil, 7-the 7th airfoil, 8-the 8th airfoil, 9-the 9th airfoil, 10-the tenth airfoil, 11-blade root, 12-vane airfoil profile.
Embodiment
Below in conjunction with the accompanying drawing embodiment that develops simultaneously, the utility model is described in detail.
As accompanying drawing 1, shown in 2 and 3, the high aeroperformance pneumatic equipment blades made of thickening type of the present utility model is comprised of vane airfoil profile 12 and blade root 11 two-part, blade overall length 700mm, vane airfoil profile part is generated by ten continuous smooth transition of airfoil Curve of wing, as shown in Figure 4, ten corresponding chord lengths of airfoil are followed successively by: the first airfoil 1 is 193.2mm, the second airfoil 2 is 174.5mm, the 3rd airfoil 3 is 155.9mm, the 4th airfoil 4 is 137.2mm, the 5th airfoil 5 is 118.5mm, the 6th airfoil 6 is 99.9mm, the 7th airfoil 7 is 81.2mm, the 8th airfoil 8 is 62.5mm, the 9th airfoil 9 is 43.8mm, the tenth airfoil 10 is 34.5mm, ,
Ten airfoil Curve of wings are comprised of lee face curve and windward side curve respectively, as shown in the system of coordinates in accompanying drawing 1, the initial point of definition system of coordinates is the leading edge point of the first airfoil Curve of wing, the postive direction that blade and blade exhibition direction is Z axis, the direction of rotor shaft is Y direction, and another is X-axis direction perpendicular to the direction of Z axis and Y-axis simultaneously; The 0 ° of angle of rotation that simultaneously defines described ten airfoil Curve of wings is positioned on X forward axle, and Y forward axle is 90 ° of angle of rotation; The leading edge point coordinate of described ten airfoil Curve of wings is followed successively by (0,0,0), (0,0 by affiliated spatial position, 70), (0,0,140), (0,0,210), (0,0,280), (0,0,350), (0,0,420), (0,0,490), (0,0,560), (0,0,595); Described ten airfoils are parallel to respectively X0Y plane and along the postive direction of Z axis, arrange successively, described ten airfoils cross leading edge point separately and perpendicular to the plane of Z axis in the angle of rotating centered by its leading edge point be followed successively by:: 28.95 °, 20.10 °, 14.00 °, 10.07 °, 7.69 °, 6.26 °, 5.19 °, 3.87 °, 1.71 °, 0.12 °; After ten continuous smooth transition of airfoil Curve of wing, generate vane airfoil profile surface;
Coordinate figure corresponding to ten airfoil Curve of wings is as following table:
The coordinate figure that the first airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the second airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 3rd airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 4th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 5th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 6th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 7th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 8th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 9th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the tenth airfoil lee face curve and windward side curve are corresponding meets respectively:
Ten Curve of wings are disposed in order by position in accompanying drawing 3, and by after above-mentioned corresponding torsional angle rotation, then to take 10 airfoil external frame curves be benchmark, and smooth transition generates blade-section between each airfoil, can draw or process vane airfoil profile part-structure.According to ten Curve of wings of accompanying drawing 4, the ratio with 1:1 is enlarged into after actual size blade, can obtain ten feature airfoil three-dimensional dimensions manufacturing machining blade mould.
Wind wheel forms by three blades of diameter 1.4m, blade material is wooden, surface scribbles the firm material of glass, the impeller comparative trial that the NACA4415 airfoil fan that utilizes blowing type B1/K2 low speed wind tunnel to carry out impeller that the utility model blade makes and American classic is made, signals collecting is completed by EDA9033G Intelligent three-phase acquisition module, and collection signal comprises the signals such as the active power, wattless power, power factor, voltage, electric current, frequency of wind energy conversion system.
The utility model application airfoil fan and NACA4415 airfoil fan adopt identical processing technology to complete, and possess the thick poor degree of identical material and surface, and two kinds of aerofoil profile wind wheels maximum power output under difference test wind speed is as shown in table 1,
The aerofoil profile that can obviously be found the utility model blade by table 1 data is the advantage at pneumatic output facet with respect to traditional NACA4415 aerofoil profile.
In sum, these are only preferred embodiment of the present utility model, be not intended to limit protection domain of the present utility model.All within spirit of the present utility model and principle, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (1)
1. the high aeroperformance pneumatic equipment blades made of thickening type, by vane airfoil profile and blade root two-part, formed, the three-dimensional structure that it is characterized in that described vane airfoil profile part surface is generated by ten continuous smooth transition of airfoil Curve of wing, and described each airfoil Curve of wing is comprised of lee face curve and windward side curve respectively; The initial point of definition system of coordinates is the leading edge point of the first airfoil Curve of wing, the postive direction that blade and blade exhibition direction is Z axis, and the direction of rotor shaft is Y direction, another is X-axis direction perpendicular to the direction of Z axis and Y-axis simultaneously; The 0 ° of angle of rotation that simultaneously defines described ten airfoil Curve of wings is positioned on X forward axle, and Y forward axle is 90 ° of angle of rotation; The leading edge point coordinate of described ten airfoil Curve of wings is followed successively by (0,0,0), (0,0 by affiliated spatial position, 70), (0,0,140), (0,0,210), (0,0,280), (0,0,350), (0,0,420), (0,0,490), (0,0,560), (0,0,595); Described ten airfoils are arranged along blade and blade exhibition direction successively, described ten airfoils are parallel to respectively X0Y plane and along the postive direction of Z axis, arrange successively, described ten airfoils cross leading edge point separately and perpendicular to the plane of Z axis in the angle of rotating centered by its leading edge point be followed successively by: 28.95 °, 20.10 °, 14.00 °, 10.07 °, 7.69 °, 6.26 °, 5.19 °, 3.87 °, 1.71 °, 0.12 °;
Described blade root is comprised of holding part and changeover portion, and holding part is rectangular configuration, is processed with the bolt hole of Y direction on it, the first airfoil of the changeover portion section of being connected and fixed and vane airfoil profile part;
The coordinate figure that described ten airfoil lee face curves and windward side curve are corresponding is as follows:
The coordinate figure that the first airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the second airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 3rd airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 4th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 5th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 6th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 7th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 8th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the 9th airfoil lee face curve and windward side curve are corresponding meets respectively:
The coordinate figure that the tenth airfoil lee face curve and windward side curve are corresponding meets respectively:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320535471.3U CN203515955U (en) | 2013-08-30 | 2013-08-30 | Thickened high-aerodynamic-performance wind turbine blade |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201320535471.3U CN203515955U (en) | 2013-08-30 | 2013-08-30 | Thickened high-aerodynamic-performance wind turbine blade |
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| CN203515955U true CN203515955U (en) | 2014-04-02 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103423083A (en) * | 2013-08-30 | 2013-12-04 | 内蒙古工业大学 | Thickened wind turbine blade with high pneumatic performance |
| CN104018998A (en) * | 2014-06-17 | 2014-09-03 | 西北工业大学 | 21%-thickness main airfoil for megawatt wind turbine blade |
| CN106401866A (en) * | 2016-08-22 | 2017-02-15 | 内蒙古工业大学 | Blade point shaped wind turbine blade |
-
2013
- 2013-08-30 CN CN201320535471.3U patent/CN203515955U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103423083A (en) * | 2013-08-30 | 2013-12-04 | 内蒙古工业大学 | Thickened wind turbine blade with high pneumatic performance |
| CN103423083B (en) * | 2013-08-30 | 2015-09-30 | 内蒙古工业大学 | A kind of thickening type high aerodynamic performance wind turbine blade |
| CN104018998A (en) * | 2014-06-17 | 2014-09-03 | 西北工业大学 | 21%-thickness main airfoil for megawatt wind turbine blade |
| CN104018998B (en) * | 2014-06-17 | 2017-02-08 | 西北工业大学 | 21%-thickness main airfoil for megawatt wind turbine blade |
| CN106401866A (en) * | 2016-08-22 | 2017-02-15 | 内蒙古工业大学 | Blade point shaped wind turbine blade |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C53 | Correction of patent for invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Wang Jianwen Inventor after: Ma Jianlong Inventor after: Liu Xiongfei Inventor after: Wei Haijiao Inventor after: Dong Bo Inventor before: Wang Jianwen Inventor before: Ma Jianlong Inventor before: Liu Xiongfei |
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| COR | Change of bibliographic data |
Free format text: CORRECT: INVENTOR; FROM: WANG JIANWEN MA JIANLONG LIU XIONGFEI TO: WANG JIANWEN MA JIANLONG LIU XIONGFEI WEI HAIJIAO DONG BO |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20140402 Effective date of abandoning: 20150930 |
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| RGAV | Abandon patent right to avoid regrant |