CN103423083B - A kind of thickening type high aerodynamic performance wind turbine blade - Google Patents
A kind of thickening type high aerodynamic performance wind turbine blade Download PDFInfo
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- CN103423083B CN103423083B CN201310385320.9A CN201310385320A CN103423083B CN 103423083 B CN103423083 B CN 103423083B CN 201310385320 A CN201310385320 A CN 201310385320A CN 103423083 B CN103423083 B CN 103423083B
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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 discloses a kind of thickening type high aerodynamic performance wind turbine blade, belong to technical field of wind energy utilization.The three-dimensional structure on blade aerofoil portion surface is generated by ten airfoil Curve of wing continuous and derivable transition; Each airfoil Curve of wing is made up 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, and blade and blade exhibition direction is the postive direction of Z axis, and 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; Ten airfoils are parallel to X0Y plane respectively and arrange along the postive direction of Z axis successively, and described ten airfoils are crossing respective leading edge point and rotate a certain angle centered by its leading edge point perpendicular in the plane of Z axis.The design that the present invention adopts vane airfoil profile front and rear edges point place to thicken, blade has high bending resistance and antifatigue damage performance under the prerequisite ensureing high aeroperformance, possesses the characteristic that threshold wind velocity is low, operational noise is low simultaneously.
Description
Technical field
The present invention relates to a kind of pneumatic equipment blades made, be specifically related to a kind of thickening type pneumatic equipment blades made, belong to technical field of wind energy utilization.
Background technique
Wind energy conversion system draws wind energy by wind wheel blade, and then be the device of electric energy by changes mechanical energy.Wind wheel is the power unit of wind-driven generator key, decides and draws wind energy efficiency.Wind wheel is made up of blade, wheel hub and axle, and generator realizes being connected with the axle of wind wheel by main shaft, and effect is that the changes mechanical energy that wind wheel exports is electric energy and is exported.As can be seen here, the blade of wind wheel decides the wind energy utilization of wind energy conversion system.And pneumatic equipment blades made is made up of vane airfoil profile and blade root two-part, the aeroperformance that blade aerofoil portion structures shape wind wheel is good and bad, and leaf root part mainly undertakes the connection of blade aerofoil portion and wheel hub, plays the effect of blade support and location.
The architectural source of conventional wind machine vane airfoil profile, in aviation aerofoil profile, causes conventional wind wing blades in use to there is following key technology defect:
1, when operating in low reynolds number, the change of blade inlet edge to roughness is more responsive, and ratio of lift coefficient to drag coefficient corruptions is serious, greatly have impact on the stationarity of its power stage.
2, easily producing fluctuation in wider tip-speed ratio scope internal power index variation, and easily stall event occurs, also there is larger wave properties in power peak.
3, wind energy conversion system threshold wind velocity requires higher, is not suitable for the utilization of low velocity wind energy resource.
4, wind energy utilization is low, causes the overall wind-resources effective rate of utilization of wind-power generating system low.
5, in running, aerodynamic noise is large, affects surrounding environment.
6, for pursuing high aeroperformance, vane airfoil profile designed thin, especially easily ruptured at trailing edge point place, easily made blade generation fatigue damage, caused wind energy conversion system equipment accident multiple.
The existence of above problem, seriously governs effective utilization of wind energy and the development process of wind energy conversion system industry.
Summary of the invention
In view of this, the invention provides a kind of thickening type high aerodynamic performance wind turbine blade, vane airfoil profile front and rear edges point place is thickeied, pneumatic equipment blades made can be made to possess on the basis with high aeroperformance, and threshold wind velocity is low, power coefficient is high and the stable characteristic of power out-put characteristic, and the blade simultaneously thickeied has high bending resistance and antifatigue damage performance.
In order to solve the problems of the technologies described above, the present invention is achieved in that a kind of thickening type high aerodynamic performance wind turbine blade, be made up of vane airfoil profile and blade root two-part, the three-dimensional structure on blade aerofoil portion surface is generated by ten airfoil Curve of wing continuous and derivable transition; Described each airfoil Curve of wing is made up 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, and blade and blade exhibition direction is the postive direction of Z axis, and 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 simultaneously defining 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 X0Y plane respectively and arrange along the postive direction of Z axis successively, and described ten airfoils are crossing respective leading edge point and be followed successively by perpendicular to the angle rotated centered by its leading edge point in the plane of Z axis: 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 made up of holding part and changeover portion, and holding part is rectangular configuration, it is processed with the bolt hole of Y direction, 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 blade aerofoil portion;
Described ten airfoil lee face curves and coordinate value corresponding to windward side curve as follows:
First airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
Second airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
3rd airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
4th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
5th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
6th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
7th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
8th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
9th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
Tenth airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
Blade is specifically produced and is realized technique, be connected with the definition of three dimensional space relative position relation the processing mold that smooth transition generates blade profile structure by above-mentioned ten feature airfoil curve practical structures, and then realized the physical treatment of blade by techniques such as such as mold injections.
Beneficial effect:
1) low threshold wind velocity.The actual test of this vanes, can start work, be greater than the threshold wind velocity of 3m/s, have obvious advantage compared with traditional airfoil blade under 2.9m/s incoming flow wind speed, 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, be design rated wind speed at 4 ~ 10m/s(10m/s) in incoming flow wind speed range, power coefficient is all apparently higher than the blade that American classic aerofoil profile NACA4415 designs, 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) excellent 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 event.
4) excellent aerodynamic noise.The actual test of this vanes, starts noise and is starkly lower than traditional airfoil blade.
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 invention;
Fig. 2 is perspective view of the present invention;
Fig. 3 is the distribution maps of of the present invention ten airfoil Curve of wings on blade;
Fig. 4 is the profile diagram of ten feature airfoil Curve of wings.
Wherein: 1-first airfoil, 2-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
To develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
As accompanying drawing 1, shown in 2 and 3, thickening type high aerodynamic performance wind turbine blade of the present invention is made up of vane airfoil profile 12 and blade root 11 two-part, vane overall length 700mm, blade aerofoil portion is generated by ten airfoil Curve of wing continuous and derivable transition, as shown in Figure 4, chord length corresponding to ten airfoils is followed successively by: the first airfoil 1 is 193.2mm, second airfoil 2 is 174.5mm, 3rd airfoil 3 is 155.9mm, 4th airfoil 4 is 137.2mm, 5th airfoil 5 is 118.5mm, 6th airfoil 6 is 99.9mm, 7th airfoil 7 is 81.2mm, 8th airfoil 8 is 62.5mm, 9th airfoil 9 is 43.8mm, tenth airfoil 10 is 34.5mm, ,
Ten airfoil Curve of wings are made up 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, blade and blade exhibition direction is the postive direction of Z axis, the direction of rotor shaft is Y direction, and another is simultaneously X-axis direction perpendicular to the direction of Z axis and Y-axis; The 0 ° of angle of rotation simultaneously defining 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 X0Y plane respectively and arrange along the postive direction of Z axis successively, and described ten airfoils are crossing respective leading edge point and be followed successively by perpendicular to the angle rotated centered by its leading edge point in the plane of Z axis:: 28.95 °, 20.10 °, 14.00 °, 10.07 °, 7.69 °, 6.26 °, 5.19 °, 3.87 °, 1.71 °, 0.12 °; Vane airfoil profile surface is generated after the transition of ten airfoil Curve of wing continuous and derivable;
Blade root 11 is made up of holding part and changeover portion, and holding part is rectangular configuration, it is processed with the bolt hole of three Y directions, 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 12;
Coordinate value corresponding to ten airfoil Curve of wings is as following table:
First airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
Second airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
3rd airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
4th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
5th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
6th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
7th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
8th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
9th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
Tenth airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
Ten Curve of wings are disposed in order by position in accompanying drawing 3, and after rotating by above-mentioned corresponding torsional angle, then with 10 airfoil external frame curves for benchmark, smooth transition generates blade-section between each airfoil, can draw or process blade aerofoil portion structure.Blade according to ten Curve of wings of accompanying drawing 4 with the scale amplifying of 1:1 for after actual size, ten the feature airfoil three-dimensional dimensions manufacturing machining blade mould can be obtained.
Wind wheel forms by the Three-blade of diameter 1.4m, blade material is wooden, surface scribbles the firm material of glass, the impeller comparative trial that the NACA4415 airfoil fan of utilize blowing type B1/K2 low speed wind tunnel to carry out impeller that blade of the present invention makes and American classic is made, signals collecting is completed by EDA9033G Intelligent three-phase acquisition module, and collection signal comprises the signal such as active power, wattless power, power factor, voltage, electric current, frequency of wind energy conversion system.
The present patent 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,
Obviously can find that the aerofoil profile of blade of the present invention is relative to the advantage of traditional NACA4415 aerofoil profile at pneumatic output facet by table 1 data.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (1)
1. a thickening type high aerodynamic performance wind turbine blade, be made up of vane airfoil profile and blade root two-part, it is characterized in that the three-dimensional structure on described blade aerofoil portion surface is generated by ten airfoil Curve of wing continuous and derivable transition, each described airfoil Curve of wing is made up 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, and blade and blade exhibition direction is the postive direction of Z axis, and 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 simultaneously defining 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 successively along blade and blade exhibition direction arrangement, described ten airfoils are parallel to X0Y plane respectively and arrange along the postive direction of Z axis successively, and described ten airfoils are crossing respective leading edge point and be followed successively by perpendicular to the angle rotated centered by its leading edge point in the plane of Z axis: 28.95 °, 20.10 °, 14.00 °, 10.07 °, 7.69 °, 6.26 °, 5.19 °, 3.87 °, 1.71 °, 0.12 °;
Described blade root is made up of holding part and changeover portion, and holding part is rectangular configuration, it is processed with the bolt hole of Y direction, the first airfoil of the changeover portion section of being connected and fixed and blade aerofoil portion;
Described ten airfoil lee face curves and coordinate value corresponding to windward side curve as follows:
First airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
Second airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
3rd airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
4th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
5th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
6th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
7th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
8th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
9th airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
Tenth airfoil lee face curve and coordinate value corresponding to windward side curve meet respectively:
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| CN201310385320.9A CN103423083B (en) | 2013-08-30 | 2013-08-30 | A kind of thickening type high aerodynamic performance wind turbine blade |
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| CN201310385320.9A CN103423083B (en) | 2013-08-30 | 2013-08-30 | A kind of thickening type high aerodynamic performance wind turbine blade |
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| CN103423083B true CN103423083B (en) | 2015-09-30 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101230836A (en) * | 2007-01-09 | 2008-07-30 | 通用电气公司 | Wind turbine airfoil family |
| CN102052266A (en) * | 2010-12-29 | 2011-05-11 | 南京航空航天大学 | After-load blunt trailing edge wing profile designed based on sharp trailing edge wing profile |
| CN202209250U (en) * | 2011-09-02 | 2012-05-02 | 吉林大学 | Protrusion type horizontal axis wind turbine blade |
| CN203515955U (en) * | 2013-08-30 | 2014-04-02 | 内蒙古工业大学 | Thickened high-aerodynamic-performance wind turbine blade |
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- 2013-08-30 CN CN201310385320.9A patent/CN103423083B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101230836A (en) * | 2007-01-09 | 2008-07-30 | 通用电气公司 | Wind turbine airfoil family |
| CN102052266A (en) * | 2010-12-29 | 2011-05-11 | 南京航空航天大学 | After-load blunt trailing edge wing profile designed based on sharp trailing edge wing profile |
| CN202209250U (en) * | 2011-09-02 | 2012-05-02 | 吉林大学 | Protrusion type horizontal axis wind turbine blade |
| CN203515955U (en) * | 2013-08-30 | 2014-04-02 | 内蒙古工业大学 | Thickened high-aerodynamic-performance wind turbine blade |
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