CN103244361A - Moderate-thickness airfoil blade of large-scale fan - Google Patents
Moderate-thickness airfoil blade of large-scale fan Download PDFInfo
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- CN103244361A CN103244361A CN2013102094437A CN201310209443A CN103244361A CN 103244361 A CN103244361 A CN 103244361A CN 2013102094437 A CN2013102094437 A CN 2013102094437A CN 201310209443 A CN201310209443 A CN 201310209443A CN 103244361 A CN103244361 A CN 103244361A
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Abstract
The invention relates to a moderate-thickness airfoil blade of a large-scale fan. An outer profile of the cross section of the middle part of the airfoil blade is divided into a leading edge, a trailing edge, a suction surface mold line and a pressure surface mold line, wherein a distance between the leading edge and the trailing edge is the chord length; the maximum thickness of the cross section is 24.5-25.5% of the chord length; a distance between a part at the maximum thickness and the leading edge is 25-35% of the chord length; the maximum camber of the cross section is 2.0-3.0% of the chord length; a distance between a part at the maximum camber and the leading edge is 70-80% of the chord length; the radius of the leading edge is 4.0-4.5% of the chord length; and the thickness of the end surface of the trailing edge is 0-5% of the chord length. The comprehensive performances of an airfoil are superior to the comprehensive performances of the traditional DU and NACA airfoils with the same relative thickness; the wind-power utilization efficiency is improved; the structural weight is reduced; the fatigue load is reduced; and the airfoil blade becomes an import technological base of developing a large-scale, efficient and low-cost wind turbine.
Description
Technical field
The present invention relates to wind power generation field, particularly relate to a kind of intermediate gauge airfoil fan 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.The core component of wind-powered electricity generation unit-----blade has the aerofoil section of different-thickness and torsional angle distribution, and operational efficiency and the reliability of its airfoil aerodynamic performances and complete machine are closely related.Early stage wind energy conversion system when blade design first-selection be to develop comparative maturity, lifting resistance characteristic aviation aerofoil profile preferably, but the design that facts have proved this class aerofoil profile is not well positioned to meet blower fan design and use requirement, as for the Stall Type wind energy conversion system, can produce too high peak energy and peak load in the stall zone, not only damaged generator, and increased the weight of the load of blade, reduced the life-span of blade, work in the open air for a long time owing to wind energy conversion system simultaneously, be subjected to sand and dust, effect such as raindrop blade surface roughness increases, and the aerofoil profile aeroperformance worsens the energy loss that causes rapidly can reach 20%-30%.
The research work of present domestic wind energy conversion system special airfoil is at the early-stage, domestic partial blade factory can only survey and draw imitated to the fan blade of external production, in default of geometry and the pneumatic performance data of aerofoil profile, directly influenced the autonomous Design level of Chinese large-sized wind energy conversion system.Therefore how to found the new intermediate gauge aerofoil profile fan blade of a kind of Wind Power Utilization efficient height, lightweight construction, the task of top priority of China's wind energy conversion system development.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of intermediate gauge airfoil fan of large fan, its weight attenuating, blower fan combination property is improved, thereby 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 intermediate gauge airfoil fan of large fan, wherein the external frame of cross section is divided into leading edge, trailing edge, suction surface molded lines and pressure side molded lines, the distance of leading edge and trailing edge is chord length, the maximum ga(u)ge of described cross section is the 24.5%-25.5% 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 2.0%-3.0% of chord length, and the distance of maximum camber place and leading edge is the 70%-80% of chord length; The radius of described leading edge is the 4.0%-4.5% of chord length, and the end surface thickness of described trailing edge is the 0%-5% of chord length.
As a kind of improvement of the present invention, the present invention also can realize by following proposal:
A kind of intermediate gauge airfoil fan of large fan, wherein, described maximum ga(u)ge is 25.12% of chord length, the distance of maximum ga(u)ge place and leading edge is 32% of chord length, maximum camber is 2.55% of chord length, the distance of maximum camber place and leading edge is 79% of chord length, and leading-edge radius is 4.3% of chord length, and the trailing edge end surface thickness is 0.5% of chord length.
A kind of intermediate gauge airfoil fan of large fan, wherein, described pressure side molded lines and suction surface molded lines are Bezier curve.
After adopting such design, the present invention has the following advantages at least:
1, the relative thickness that provides of this programme is traditional DU, the NACA aerofoil profile that 25% aerofoil profile (called after UP25) combination property is better than identical relative thickness, improves 4.2% than traditional DU91-W-250 combination property.
2, new aerofoil profile has not only improved Wind Power Utilization efficient, and has alleviated structure weight, has reduced fatigue load, has become the important technology basis of the large-scale high efficiency, low cost wind energy conversion system of development.
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 leaf central part cross-sectional structure schematic representation of the intermediate gauge airfoil fan 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 intermediate gauge airfoil fan of a kind of large fan of the present invention.
Fig. 4 is the intermediate gauge airfoil fan of a kind of large fan of the present invention and the lift coefficient comparison diagram of DU91-W-250.
Fig. 5 is the intermediate gauge airfoil fan of a kind of large fan of the present invention and the ratio of lift coefficient to drag coefficient comparison diagram of DU91-W-250.
Embodiment
With reference to Fig. 1, Fig. 2, the invention provides relative thickness and be 25% vane airfoil profile (called after UP25), the intermediate gauge airfoil fan of large fan provided by the present invention, wherein the external frame of cross section mainly is made of leading edge 1, trailing edge 2, suction surface molded lines 3 and pressure side molded lines 4, wherein leading edge 1 is circular arc, leading edge 1 is connected with suction surface molded lines 3, pressure side molded lines 4 respectively, and the curvature at tie point place is continuous, and suction surface molded lines 3 terminal 11 and pressure side molded lines 4 ends 13 are connected to form trailing edge 2.
At first, the name to each several part among Fig. 1 is called following definition:
1, mean camber line 10: do the incircle of a series of suction surface molded lines 3 and pressure side molded lines 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 lines 3 and pressure side molded lines 4 constitute 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 lines 4 of the present invention and suction surface molded lines 3 adopt be the Bezier(shellfish now) curve, the relative thickness of this programme design is that the geometric data of 25% aerofoil profile (UP25) is as follows:
The scope of UP25 each several part parameter value:
Through experimental verification repeatedly, most preferred embodiment data of the present invention are as follows:
The 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 designs.
The aerodynamic data comparison diagram of UP25 and DU91-W-250 aerofoil profile is seen with reference to Fig. 4, Fig. 5, y coordinate is respectively lift coefficient and ratio of lift coefficient to drag coefficient among the figure, the angle of the line that abscissa is aerofoil profile leading edge and trailing edge and the direction of the wind comes from (unit for °), the aeroperformance of UP25 obviously is better than traditional DU aerofoil profile of stack pile as seen from the figure.The main layout of large scale wind power machine intermediate gauge airfoil fan of the present invention is at close blade medium position, this position is the position that blade is mainly exerted oneself, the aerofoil profile of this position of large scale wind power machine blade needs high coefficient of lift combined, high lift-drag ratio, mild stalling characteristics, 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 traditional DU, NACA aerofoil profile that combination property is better than identical relative thickness, the reynolds number range of aerofoil profile operation provided by the invention is at 3*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 intermediate gauge airfoil fan of a large fan, wherein the external frame of cross section is divided into leading edge, trailing edge, suction surface molded lines and pressure side molded lines, 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 24.5%-25.5% 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 2.0%-3.0% of chord length, and the distance of maximum camber place and leading edge is the 70%-80% of chord length;
The radius of described leading edge is the 4.0%-4.5% of chord length, and the end surface thickness of described trailing edge is the 0%-5% of chord length.
2. the intermediate gauge airfoil fan of a kind of large fan according to claim 1, it is characterized in that: described maximum ga(u)ge is 25.12% of chord length, the distance of maximum ga(u)ge place and leading edge is 32% of chord length, maximum camber is 2.55% of chord length, the distance of maximum camber place and leading edge is 79% of chord length, leading-edge radius is 4.3% of chord length, and the trailing edge end surface thickness is 0.5% of chord length.
3. the intermediate gauge airfoil fan of a kind of large fan according to claim 1 and 2, it is characterized in that: described pressure side molded lines and suction surface molded lines are Bezier curve.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2013102094437A CN103244361A (en) | 2013-05-30 | 2013-05-30 | Moderate-thickness airfoil blade of large-scale fan |
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| CN2013102094437A CN103244361A (en) | 2013-05-30 | 2013-05-30 | Moderate-thickness airfoil blade of large-scale fan |
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Cited By (1)
| 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 (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100104436A1 (en) * | 2008-10-27 | 2010-04-29 | General Electric Company | Active curcilation control of aerodynamic structures |
| CN101813070A (en) * | 2010-04-13 | 2010-08-25 | 南京航空航天大学 | Vane airfoil profile of low power wind driven generator |
| CN203321758U (en) * | 2013-05-30 | 2013-12-04 | 国电联合动力技术有限公司 | Medium-thickness airfoil blade for large turbines |
-
2013
- 2013-05-30 CN CN2013102094437A patent/CN103244361A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100104436A1 (en) * | 2008-10-27 | 2010-04-29 | General Electric Company | Active curcilation control of aerodynamic structures |
| CN101813070A (en) * | 2010-04-13 | 2010-08-25 | 南京航空航天大学 | Vane airfoil profile of low power wind driven generator |
| CN203321758U (en) * | 2013-05-30 | 2013-12-04 | 国电联合动力技术有限公司 | Medium-thickness airfoil blade for large turbines |
Non-Patent Citations (1)
| Title |
|---|
| 陈进等: "基于粗糙度敏感性研究的风力机专用翼型设计", 《空气动力学学报》, vol. 29, no. 2, 30 April 2011 (2011-04-30) * |
Cited By (1)
| 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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Application publication date: 20130814 |