CN103321857A - Large-thickness blunt-trailing-edge airfoil-shaped blade of large-scale wind turbine - Google Patents

Large-thickness blunt-trailing-edge airfoil-shaped blade of large-scale wind turbine Download PDF

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Publication number
CN103321857A
CN103321857A CN2013102836757A CN201310283675A CN103321857A CN 103321857 A CN103321857 A CN 103321857A CN 2013102836757 A CN2013102836757 A CN 2013102836757A CN 201310283675 A CN201310283675 A CN 201310283675A CN 103321857 A CN103321857 A CN 103321857A
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Prior art keywords
chord length
edge
leading edge
maximum
blade
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CN2013102836757A
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CN103321857B (en
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周文明
代海涛
刘丹
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Guoneng United Power Technology (Baoding) Co.,Ltd.
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Guodian United Power Technology Co Ltd
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    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02BCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B10/00Integration of renewable energy sources in buildings
    • Y02B10/30Wind power
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02PCLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50Manufacturing or production processes characterised by the final manufactured product

Abstract

The invention relates to a large-thickness blunt-trailing-edge airfoil-shaped blade of a large-scale wind turbine. The outer contour of the cross section of a root portion of the blade is divided into a leading edge, a trailing edge, a suction-surface molded line and a pressure-surface molded line. The distance between the leading edge and the trailing edge is chord length, the maximum thickness of the cross section is 65.0%-75.0% of the chord length, and the distance between the thickest position and the leading edge is 25%-35% of the chord length. The maximum camber of the cross section is 0.1%-0.5% of the chord length, the distance between the maximum camber position and the leading edge is 85%-97% of the chord length, the radius of the leading edge is 35.0%-45.0% of the chord length, and the end-face thickness of the trailing edge is 25%-35% of the chord length. The airfoil shape is a precedent in domestic airfoil shapes, with relative thickness of over 40%, special for wind turbines; by the airfoil shape, static rigidity of the blade can be improved and structural weight can be reduced, and an important technical basis is provided to development of large-size efficient wind turbines with low costs.

Description

A kind of large thickness aerofoil with blunt tail edge blade of large fan
Technical field
The present invention relates to wind power generation field, particularly relate to a kind of large thickness aerofoil with blunt tail edge blade of large fan.
Background technique
Along with the energy and environmental problem become increasingly conspicuous, abundant, the pollution-free and reproducible wind energy of reserves is 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, as the length of critical component-blade also thereupon from several years ago about 20 meters (1 megawatt unit) increase to (5 megawatt unit) and even at present maximum about 75 meters (10 megawatt unit) about 60 meters.Yet, the flexible increase after length of blade increases, corresponding construction rigidity reduces greatly, has weakened it and has resisted the ability of various extraneous load impacts, has also increased it and has scanned the risk of pylon, and corresponding unit reliability reduces.In addition, blade maximizes own wt is enlarged markedly, and causes cost to increase, and also will bring many problems to follow-up operation, installation and maintenance.For this reason, the foreign scholar has proposed the large thickness Airfoil Design of a kind of what is called technology recently, being about to original blade increases to more than 40% chord length near position aerofoil profile maximum ga(u)ge in blade root and the leaf, this technology is to solve above-mentioned feasible scheme to the vital structural characteristics problem of large-scale developer blade once proposition with regard to being generally believed by industry.Therefore, how to found high, the lightweight new large thickness aerofoil profile fan blade of a kind of structural rigidity, real one of the current important research and development problem that belongs to.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of large thickness aerofoil with blunt tail edge blade of large fan, makes that its structural rigidity is high, weight lowers, the blower fan combination property improves, thereby overcomes the deficiency that existing structural rigidity is low, weight is large.
For solving the problems of the technologies described above, the invention provides a kind of large 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 65.0%-75.0% of chord length, and the distance of maximum ga(u)ge place and leading edge is the 25%-35% of chord length; The maximum camber of described cross section is the 0.1%-1.5% of chord length, and the distance of maximum camber place and leading edge is the 85%-97% of chord length; The radius of described leading edge is the 35.0%-45.0% of chord length, and the end surface thickness of described trailing edge is the 25%-35% of chord length.
As a kind of improvement of the present invention, the present invention also can realize by following proposal:
A kind of large thickness aerofoil with blunt tail edge blade of large fan, wherein, described maximum ga(u)ge is 70% of chord length, the distance of maximum ga(u)ge place and leading edge is 30% of chord length, maximum camber is 0.5% of chord length, the distance of maximum camber place and leading edge is 95% of chord length, and leading-edge radius is 38.0% of chord length, and the trailing edge end surface thickness is 31.42% of chord length.
A kind of large thickness aerofoil with blunt tail edge blade of large fan, wherein, described pressure side molded line and suction surface molded line are Bezier curve.
After adopting such design, the present invention has the following advantages at least:
1, the application of the vane airfoil profile that provides of this programme can effectively solve the 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 profile not only Effective Raise the quiet rigidity of blade more than 20%, and make the blade deadweight also reduce to reach about 5%.
Description of drawings
Above-mentioned only is the general introduction of technical solution of the present invention, and for can clearer understanding technological means of the present invention, the present invention is described in further detail below in conjunction with accompanying drawing and embodiment.
Fig. 1 is the blade root cross-sectional structure schematic diagram of the large 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 among Fig. 1.
Fig. 3 is the cross section external frame plotted curve of the large 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 large 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 large 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 relative thickness and be 70% vane airfoil profile (called after UP70), the blade root cross section of the large thickness aerofoil with blunt tail edge blade of large fan provided by the present invention is made 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 curvature at tie point place is continuous, and suction surface molded line 3 terminal 11 and pressure side molded line 4 ends 13 are connected to form trailing edge 2.
At first, the title of each several part among Fig. 1 is defined as follows:
1, mean camber line 10: do the incircle of 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 points is called wing chord, and the length of wing chord is called for short chord length.
3, camber C: the maximum normal distance between mean camber line 10 and the wing chord is called the maximum camber of aerofoil profile, is called for short camber, and it is called relative maximum camber with the ratio of chord length.
4, leading-edge radius: the apothem of the leading edge 1 by aerofoil profile is called leading-edge radius, and it is called relative leading-edge radius with the ratio of chord length.
5, maximum ga(u)ge D: maximum inscribe diameter of a circle is called the maximum ga(u)ge of aerofoil profile in the aerofoil profile incircle, 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 at maximum ga(u)ge place along wing chord, it is called relative maximum ga(u)ge position with the ratio of chord length.
7, maximum camber position: be called the maximum camber position by leading edge point to the distance of maximum camber place chordwise, it is called relative maximum camber position with the ratio of chord length.
8, the trailing edge end face 12: the line segment that end 13 lines of the end 11 of suction surface molded line 3 and pressure side molded line 4 consist of is trailing edge end face 12, and its thickness becomes relative trailing edge end surface thickness with the ratio of chord length.
With reference to shown in Figure 3, pressure side molded line 4 of the present invention and suction surface molded line 3 adopt be the Bezier(shellfish hereby) curve, the relative thickness of this programme design is that the geometric data of 70% aerofoil profile (UP70) is as follows:
The scope of UP70 each several part parameter value:
Through repeatedly experimental verification, most preferred embodiment data of the present invention are as follows:
The Design of Aerodynamic Configuration that can carry out the large scale wind power machine blade according to geometry and the pneumatic performance data of above-mentioned aerofoil profile.
The aerodynamic data figure of UP70 aerofoil profile sees with reference to Fig. 4, Fig. 5, and wherein, abscissa is leading edge and trailing edge line and the angle of the 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 UP70 is comparatively good as seen from the figure.The main layout of large thickness aerofoil with blunt tail edge of large scale wind power machine blade of the present invention is in close root of blade position, this position is that blade mainly carries the position, the aerofoil profile of this position of large scale wind power machine blade needs large thickness, high power coefficient, low roughness receptance, high reynolds number stability, this programme passes through the performance to the mode comprehensive assessment aerofoil profile of above-mentioned index parameter weighting, obtained the aerofoil profile of high comprehensive performance, the reynolds number range of aerofoil profile operation provided by the invention is at 1*10 6To 6*10 6
The above; it only is preferred embodiment of the present invention; be not that the present invention is done any pro forma restriction, 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 (3)

1. the large thickness aerofoil with blunt tail edge blade of a 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 the 65.0%-75.0% of chord length, and the distance of maximum ga(u)ge place and leading edge is the 25%-35% of chord length;
The maximum camber of described cross section is the 0.1%-1.5% of chord length, and the distance of maximum camber place and leading edge is the 85%-97% of chord length;
The radius of described leading edge is the 35.0%-45.0% of chord length, and the end surface thickness of described trailing edge is the 25%-35% of chord length.
2. the large thickness aerofoil with blunt tail edge blade of a kind of large fan according to claim 1, it is characterized in that: described maximum ga(u)ge is 70% of chord length, the distance of maximum ga(u)ge place and leading edge is 30% of chord length, maximum camber is 0.5% of chord length, the distance of maximum camber place and leading edge is 95% of chord length, leading-edge radius is 38.0% of chord length, and the trailing edge end surface thickness is 31.42% of chord length.
3. the large thickness aerofoil with blunt tail edge blade of a kind of large fan according to claim 1 and 2, it is characterized in that: described pressure side molded line and suction surface molded line are Bezier curve.
CN201310283675.7A 2013-07-08 2013-07-08 Large-thickness blunt-trailing-edge airfoil-shaped blade of large-scale wind turbine Active CN103321857B (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015165140A1 (en) * 2014-04-29 2015-11-05 苏州飞能可再生能源科技有限公司 Vertical-axis wind turbine-dedicated high-efficiency blade

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4830574A (en) * 1988-02-29 1989-05-16 United Technologies Corporation Airfoiled blade
CN1780982A (en) * 2003-04-28 2006-05-31 艾劳埃斯·乌本 Rotor blade of a wind energy facility
CN101220799A (en) * 2007-01-12 2008-07-16 西门子公司 Wind turbine rotor blade with vortex generators
US8419373B1 (en) * 2011-10-12 2013-04-16 Mitsubishi Heavy Industries, Ltd. Wind turbine blade, wind turbine generator equipped with wind turbine blade and method of designing wind turbine blade
CN103133272A (en) * 2013-03-26 2013-06-05 国电联合动力技术有限公司 Thin airfoil type blade of large-scale fan
CN203383989U (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

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4830574A (en) * 1988-02-29 1989-05-16 United Technologies Corporation Airfoiled blade
CN1780982A (en) * 2003-04-28 2006-05-31 艾劳埃斯·乌本 Rotor blade of a wind energy facility
CN101220799A (en) * 2007-01-12 2008-07-16 西门子公司 Wind turbine rotor blade with vortex generators
US8419373B1 (en) * 2011-10-12 2013-04-16 Mitsubishi Heavy Industries, Ltd. Wind turbine blade, wind turbine generator equipped with wind turbine blade and method of designing wind turbine blade
CN103133272A (en) * 2013-03-26 2013-06-05 国电联合动力技术有限公司 Thin airfoil type blade of large-scale fan
CN203383989U (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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015165140A1 (en) * 2014-04-29 2015-11-05 苏州飞能可再生能源科技有限公司 Vertical-axis wind turbine-dedicated high-efficiency blade

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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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Effective date of registration: 20170428

Address after: 071024 Baoding wind energy street, Hebei, No. 88

Patentee after: Guodian United Power Technology (Baoding) Co., Ltd.

Address before: 100000 Beijing City, Zhongguancun, South Street, building B, building No., level 56, level 16

Patentee before: Guodian United Power Technology Co., Ltd.

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Address after: 071051 No.88, Fengfeng street, high tech Development Zone, Baoding City, Hebei Province

Patentee after: Guoneng United Power Technology (Baoding) Co.,Ltd.

Address before: No. 88, Fengfeng street, Baoding City

Patentee before: GUODIAN UNITED POWER TECHNOLOGY (BAODING) Co.,Ltd.