CN103306907B - A kind of heavy thickness aerofoil with blunt tail edge blade of large fan - Google Patents
A kind of heavy thickness aerofoil with blunt tail edge blade of large fan Download PDFInfo
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- CN103306907B CN103306907B CN201310283686.5A CN201310283686A CN103306907B CN 103306907 B CN103306907 B CN 103306907B CN 201310283686 A CN201310283686 A CN 201310283686A CN 103306907 B CN103306907 B CN 103306907B
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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
- Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
- Y02B10/00—Integration of renewable energy sources in buildings
- Y02B10/30—Wind power
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Abstract
The present invention relates to a kind of heavy thickness aerofoil with blunt tail edge blade of large fan, the cross section external frame of its leaf root part is divided into leading edge, trailing edge, suction surface molded line and pressure side molded line, the distance of leading edge and trailing edge is chord length, the maximum ga(u)ge of described cross section is the 50.0%-55.0% of chord length, and the distance of maximum ga(u)ge place and leading edge is the 30%-35% of chord length; The maximum camber of described cross section is the 0.5%-1.5% of chord length, and the distance of maximum camber place and leading edge is the 85%-95% of chord length; The radius of described leading edge is the 25.0%-35.0% of chord length, and the end surface thickness of described trailing edge is the 10%-14% of chord length.This aerofoil profile opens the beginning that domestic relative thickness is greater than the Special Airfoil of Wind Turbine of 40%, and the application of this aerofoil profile not only can increase blade Static stiffness but also can alleviate structure weight, becomes the important technical basis of development Large Efficient low cost wind energy conversion system.
Description
Technical field
The present invention relates to wind power generation field, particularly relate to a kind of heavy thickness aerofoil with blunt tail edge blade of large fan.
Background technique
Along with the energy and environmental problem become increasingly conspicuous, rich reserves, pollution-free and reproducible wind energy are subject to people's attention gradually, and the development of wind-powered electricity generation is particularly swift and violent.No matter for land or offshore wind farm unit, unit capacity is all presenting increasing trend, correspondingly, the length as critical component-blade also increases to about 60 meters (5 megawatt units) and even maximum about 75 meters at present (10 megawatt unit) from about 20 meters several years ago (1 megawatt units) thereupon.But flexible increase after length of blade increases, corresponding construction rigidity reduces greatly, reduces the ability of the various extraneous loading effect of its opposing, too increases the risk that it scans pylon, and the reliability of corresponding unit reduces.In addition, while blade maximizes, own wt enlarges markedly, and causes cost to increase, and also will bring many problems to follow-up operation, installation and maintenance.For this reason, foreign scholar is recently proposed a kind of so-called heavy thickness Airfoil Design technology, more than 40% chord length is increased to by original blade position aerofoil profile maximum ga(u)ge in blade root and leaf, this technology, once proposition, is solve the above-mentioned feasible scheme to the vital structural characteristics problem of large-scale developer blade with regard to being generally believed by industry.Therefore, how to found high, the lightweight new heavy thickness aerofoil profile fan blade of a kind of structural rigidity, one of current important research and development problem of real genus.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of heavy thickness aerofoil with blunt tail edge blade of large fan, makes that its structural rigidity is high, weight lowers, fan comprehensive performance improves, thus overcome the deficiency that existing structure weight is heavy, wind energy utilization is low.
For solving the problems of the technologies described above, the invention provides a kind of heavy thickness aerofoil with blunt tail edge blade of large fan, the cross section external frame of its leaf root part is divided into leading edge, trailing edge, suction surface molded line and pressure side molded line, the distance of leading edge and trailing edge is chord length, the maximum ga(u)ge of described cross section is the 50.0%-55.0% of chord length, and the distance of maximum ga(u)ge place and leading edge is the 30%-35% of chord length; The maximum camber of described cross section is the 0.5%-1.5% of chord length, and the distance of maximum camber place and leading edge is the 85%-95% of chord length; The radius of described leading edge is the 25.0%-35.0% of chord length, and the end surface thickness of described trailing edge is the 10%-14% of chord length.
As a modification of the present invention, the present invention also realizes by following proposal:
A kind of heavy thickness aerofoil with blunt tail edge blade of large fan, wherein, described maximum ga(u)ge is 52.36% of chord length, the distance of maximum ga(u)ge place and leading edge is 32.5% of chord length, maximum camber is 0.69% of chord length, the distance of maximum camber place and leading edge is 88.9% of chord length, and leading-edge radius is 29.7% of chord length, and trailing edge end surface thickness is 12.64% of chord length.
A heavy thickness aerofoil with blunt tail edge blade for large fan, wherein, described pressure side molded line and suction surface molded line are Bezier curve.
After adopting such design, the present invention at least has the following advantages:
1, the application of vane airfoil profile that this programme provides effectively can solve large scale wind power machine blade because the trailing edge place thickness of maximum chord length is too thin and easily occur the problem of flexing.
2, the application of new aerofoil obviously improves blade structure efficiency, not only effectively improves blade Static stiffness more than 20%, and makes blade deadweight also reduce to reach about 5%.
Accompanying drawing explanation
Above-mentioned is only the general introduction of technical solution of the present invention, and in order to better understand technological means of the present invention, below in conjunction with accompanying drawing and embodiment, the present invention is described in further detail.
Fig. 1 is the blade root cross-sectional structure schematic diagram of the heavy thickness aerofoil with blunt tail edge blade of a kind of large fan of the present invention.
Fig. 2 is the partial enlarged drawing of trailing edge in Fig. 1.
Fig. 3 is the cross section external frame plotted curve of the heavy thickness aerofoil with blunt tail edge blade of a kind of large fan of the present invention.
Fig. 4 is the lift coefficient figure of the heavy thickness aerofoil with blunt tail edge blade of a kind of large fan of the present invention.
Fig. 5 is the ratio of lift coefficient to drag coefficient figure of the heavy thickness aerofoil with blunt tail edge blade of a kind of large fan of the present invention.
Embodiment
With reference to Fig. 1, Fig. 2, the invention provides the vane airfoil profile (called after UP50) that relative thickness is 50%, the blade root cross section of the heavy thickness aerofoil with blunt tail edge blade of large fan provided by the present invention is made up of leading edge 1, trailing edge 2, suction surface molded line 3 and pressure side molded line 4, wherein leading edge 1 is circular arc, leading edge 1 is connected with suction surface molded line 3, pressure side molded line 4 respectively, the continual curvature at tie point place, suction surface molded line 3 end 11 and pressure side molded line 4 end 13 are connected to form trailing edge 2.
First, the title of each several part in Fig. 1 is defined as follows:
1, mean camber line 10: the incircle doing a series of suction surface molded line 3 and pressure side molded line 4 in aerofoil profile, the line of these incenters is called the mean camber line 10 of aerofoil profile.
2, chord length: the line of mean camber line 10 rear and front end point is called wing chord, the length of wing chord is called for short chord length.
3, camber C: the maximum normal distance between mean camber line 10 and wing chord is called the maximum camber of aerofoil profile, be called for short camber, it is called relative maximum camber with the ratio of chord length.
4, leading-edge radius: be called leading-edge radius by the apothem of the leading edge 1 of aerofoil profile, it is called relative leading-edge radius with the ratio of chord length.
5, maximum ga(u)ge D: inscribe diameter of a circle maximum in aerofoil profile incircle is called the maximum ga(u)ge of aerofoil profile, and it is called relative maximum ga(u)ge with the ratio of chord length.
6, maximum ga(u)ge position: be called maximum ga(u)ge position by leading edge point to the distance of maximum ga(u)ge along wing chord, itself and the ratio of chord length are called relative maximum ga(u)ge position.
7, maximum camber position: be called maximum camber position by leading edge point to the distance of maximum camber chordwise, it and the ratio of chord length are called relative maximum camber position.
8, trailing edge end face 12: the line segment that the end 11 of suction surface molded line 3 and end 13 line of pressure side molded line 4 are formed is trailing edge end face 12, and its thickness and the ratio of chord length become relative trailing edge end surface thickness.
With reference to shown in Fig. 3, what pressure side molded line 4 of the present invention and suction surface molded line 3 adopted is Bezier(shellfish is hereby) curve, the relative thickness of this programme design is that the geometric data of the aerofoil profile (UP50) of 50% is as follows:
The scope of UP50 each several part parameter value:
Through experimental verification repeatedly, most preferred embodiment data of the present invention are as follows:
The Design of Aerodynamic Configuration of large scale wind power machine blade can be carried out according to the geometry of above-mentioned aerofoil profile and pneumatic performance data.
The aerodynamic data figure of UP50 aerofoil profile is shown in reference to Fig. 4, Fig. 5, and wherein, abscissa is the angle in leading edge and trailing edge line and direction of the wind comes from, and y coordinate is respectively lift coefficient and ratio of lift coefficient to drag coefficient, and the aeroperformance of UP50 is comparatively excellent as seen from the figure.The heavy thickness aerofoil with blunt tail edge primary placements of large scale wind power machine blade of the present invention is at close root of blade and blade medium position, this position is that blade mainly carries position, the aerofoil profile of this position of large scale wind power machine blade needs heavy thickness, high power coefficient, low roughness receptance, high reynolds number stability, this programme is by the performance to the mode comprehensive assessment aerofoil profile of above-mentioned index parameter weighting, obtain the aerofoil profile of high comprehensive performance, the reynolds number range that aerofoil profile provided by the invention is run is at 1*10
6to 6*10
6.
The above; it is only preferred embodiment of the present invention; not do any pro forma restriction to the present invention, those skilled in the art utilize the technology contents of above-mentioned announcement to make a little simple modification, equivalent variations or modification, all drop in protection scope of the present invention.
Claims (2)
1. a heavy thickness aerofoil with blunt tail edge blade for large fan, the cross section external frame of its leaf root part is divided into leading edge, trailing edge, suction surface molded line and pressure side molded line, and the distance of leading edge and trailing edge is chord length, it is characterized in that:
The maximum ga(u)ge of described cross section is 52.36% of chord length, and the distance of maximum ga(u)ge place and leading edge is 32.5% of chord length;
The maximum camber of described cross section is 0.69% of chord length, and the distance of maximum camber place and leading edge is 88.9% of chord length;
The radius of described leading edge is 29.7% of chord length, and the end surface thickness of described trailing edge is 12.64% of chord length.
2. the heavy thickness aerofoil with blunt tail edge blade of a kind of large fan according to claim 1, is characterized in that: described pressure side molded line and suction surface molded line are Bezier curve.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310283686.5A CN103306907B (en) | 2013-07-08 | 2013-07-08 | A kind of heavy thickness aerofoil with blunt tail edge blade of large fan |
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| CN201310283686.5A CN103306907B (en) | 2013-07-08 | 2013-07-08 | A kind of heavy thickness aerofoil with blunt tail edge blade of large fan |
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| CN103306907A CN103306907A (en) | 2013-09-18 |
| CN103306907B true CN103306907B (en) | 2015-09-02 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103939283B (en) * | 2014-04-29 | 2017-01-11 | 苏州飞能可再生能源科技有限公司 | Blade special for vertical axis wind turbine |
| CN104863799A (en) * | 2015-04-17 | 2015-08-26 | 湖北工业大学 | Method for designing wind turbine airfoil by using Bessel function curve |
| CN105781873B (en) * | 2016-05-13 | 2018-06-26 | 申振华 | A kind of large size Blades For Horizontal Axis Wind family of aerofoil sections |
| CN115324929B (en) * | 2022-10-17 | 2023-01-20 | 西门子电机(中国)有限公司 | Motor fan blade and motor fan |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101341332A (en) * | 2005-12-20 | 2009-01-07 | Lm玻璃纤维有限公司 | Wind turbine rotor blade comprising a trailing edge section of constant cross section |
| CN102062044A (en) * | 2010-12-23 | 2011-05-18 | 中国科学院工程热物理研究所 | Wind machine blade airfoil family |
| CN102197215A (en) * | 2008-10-23 | 2011-09-21 | 瑞能系统股份公司 | Profile of a rotor blade and rotor blade of a wind power plant |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0772731B1 (en) * | 1994-11-17 | 2003-06-11 | Iosif Taposu | Airfoil section |
| US7059833B2 (en) * | 2001-11-26 | 2006-06-13 | Bonus Energy A/S | Method for improvement of the efficiency of a wind turbine rotor |
| CN203383988U (en) * | 2013-07-08 | 2014-01-08 | 国电联合动力技术有限公司 | Large-thickness blunt trailing edge airfoil blade of large fan |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101341332A (en) * | 2005-12-20 | 2009-01-07 | Lm玻璃纤维有限公司 | Wind turbine rotor blade comprising a trailing edge section of constant cross section |
| CN102197215A (en) * | 2008-10-23 | 2011-09-21 | 瑞能系统股份公司 | Profile of a rotor blade and rotor blade of a wind power plant |
| CN102062044A (en) * | 2010-12-23 | 2011-05-18 | 中国科学院工程热物理研究所 | Wind machine blade airfoil family |
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Inventor after: Zhou Wenming Inventor after: Dai Haitao Inventor after: Liu Dan Inventor after: Li Meizhi Inventor before: Zhou Wenming Inventor before: Dai Haitao Inventor before: Liu Dan |
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