CN102400847A - Wind-driven generator blade wing section - Google Patents
Wind-driven generator blade wing section Download PDFInfo
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- CN102400847A CN102400847A CN2011103859511A CN201110385951A CN102400847A CN 102400847 A CN102400847 A CN 102400847A CN 2011103859511 A CN2011103859511 A CN 2011103859511A CN 201110385951 A CN201110385951 A CN 201110385951A CN 102400847 A CN102400847 A CN 102400847A
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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
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Abstract
The invention relates to a wind-driven generator blade wing section for a horizontal-axis wind-driven generator blade, which applies reverse engineering to acquire coordinate values of the upper surface and the lower surface of a barn-swallow wing section and is obtained by comparison of the wind-tunnel experiment and the standard wing section. In a barn-swallow wing simulating section, the position of the largest thickness t accounts for 27.3%-36.4% of the chord length, and the position of the largest curvature f accounts for 45.5%-54.5% of the chord length; the radius of the front edge of the largest thickness t is reduced by about 1.2 times than the standard wing section, so that the lift force loss caused by premature separation of the air flow on the wing section can be prevented; and the largest curvature f is about 2 times of that of the standard wing section, so that the flow speed difference of the upper surface and the lower surface of the bionic wing section is increased, further the pressure difference of the upper surface and the lower surface is increased and the lift force is improved. In the barn-swallow wing simulating section, the lift force and the lift-drag ratio are better and the whole pneumatic property is improved.
Description
Technical field:
The present invention relates to a kind of aerofoil profile of blade of wind-driven generator, be specifically related to a kind of aerofoil profile of horizontal axis wind-driven generator blade.
Technical background:
Wind-power electricity generation is one of generation of electricity by new energy technology of the tool development prospect in the world today, and its extensive research and development utilization has become the emphasis of 21 century countries in the world new energy development.China is not only the big producing country of wind power equipment, and big export country also is a consumption big country, and household small-size wind power plant market potential is very huge.
At present wind-driven generator mainly has two kinds of forms: horizontal axis and vertical shaft, and using more in the world is horizontal axis wind-driven generator, this wind energy conversion system is applicable to large-scale wind energy turbine set.Pneumatic equipment blades made is the core position that wind-driven generator is caught wind energy; And the aerofoil profile that constitutes the vane aerodynamic profile is determining the performance of blade; Be the key of Blade Design, it is directly determining the efficient of wind energy transformation, and therefore studying high performance aerofoil profile has its necessity.
As far back as mid-term in 20th century, just wind mill airfoil has been carried out particular study abroad.Denmark National Laboratory has proposed Ris Ф-A1, Ris Ф-P, three kinds of wind energy conversion system special airfoils of Ris Ф-B1 family; Sweden aeronautical research institute has designed FFA-W1, WZ, W3 wind energy conversion system special airfoil family; Holland Delft university has developed the DU family of aerofoil sections.These wind energy conversion system special airfoils have characteristics such as milder stalling characteristics, lower leading edge susceptibility and low noise; But its efficient that transforms wind energy is compared very big development space in addition with the Betz theory; The lift and the ratio of lift coefficient to drag coefficient that are aerofoil profile are still waiting further raising; Thereby the increase wind energy utilization reduces energy loss.
In today of social high development, bionics as one independently subject admitted by the more and more scholars expert, and biologically in the development and change in 1 years possessed the character that adapts to nature, its unique researching value is more arranged.
At occurring in nature, birds directly contact with air with insect, and the wing of birds also is laterally to be arranged by a series of aerofoil profiles to form, and are similar with the wind-driven generator operating mode.The present invention is research object with the house swallow, and its wing aerofoil profile is applied on the wind energy conversion system, intends solving the low problem of wind energy utilization.House swallow is modal summer resident, also is one of the fastest birds that fly in the world, and its wing is long and narrow, and this wing is adapted to migrating of flight fast and long distance, has very strong flexibility.
Summary of the invention:
The present invention relates to a kind of pneumatic equipment blades made aerofoil profile; Purpose is to wind-driven generator special airfoil lift and the general not high situation of ratio of lift coefficient to drag coefficient; Its lift and ratio of lift coefficient to drag coefficient under different reynolds' number and the different angle of attack can be promoted significantly; Imitative house swallow aerofoil profile is applied to solves the problem that the horizontal axis wind-driven generator wind energy utilization is low, loss is big on the wind-driven generator, save energy spending.
Above-mentioned purpose of the present invention is achieved in that accompanying drawings is following:
A kind of pneumatic equipment blades made aerofoil profile; Be made up of chord length, thickness, leading-edge radius and camber, said chord length c is 1 o'clock, and the span of maximum ga(u)ge t is 0.0573～0.0617; The span of said leading-edge radius r is 0.00522～0.00679; The span of said camber f is 0.0708～0.0771, and the position at maximum ga(u)ge t place account for chord length c span 27.3%～36.4%, the position at said maximum camber t place accounts for 45.5%～54.5% of said chord length c scope.
The leading-edge radius of imitative house swallow aerofoil profile of the present invention has reduced about 1 times than standard aerofoil profile NACA4412, thereby this wind-exposuring area that can reduce aerofoil profile reduces pressure drag; Maximum ga(u)ge is compared with the standard aerofoil profile and has been reduced about 1.1 times, can prevent that the air-flow on the aerofoil profile from premature disengagement occurring when flowing through upper surface, causes loss of lift; The maximum camber of imitative house swallow aerofoil profile approximately is about 2 times of standard aerofoil profile apparently higher than the standard aerofoil profile, and this just makes the upper and lower airfoil surface current difference of bionical aerofoil profile strengthen, thereby the upper and lower surface pressure difference of aerofoil profile strengthens, so lift increases.
The present invention has the following advantages: shape and surface structure that aerofoil profile of the present invention does not change itself just can obtain good aerodynamic characteristic: the angle of attack scope during experiment is-10 °～40 °; Reynolds' number is respectively 60000,80000; The lift coefficient that records imitative house swallow aerofoil profile has improved 36.25%, 26.9% respectively than standard aerofoil profile, and ratio of lift coefficient to drag coefficient has improved 28.9%, 38.5% respectively than standard aerofoil profile; Laboratory data of the present invention is to obtain through actual tunnel test, compares with the data that simulation analysis in the past obtains to have more convincingness.
Description of drawings:
The schematic representation of the bionical aerofoil profile of Fig. 1.
Fig. 2 is the partial enlarged drawing at Figure 1A place.
Fig. 3 is under the situation of the actual blowing of tunnel test, and imitative house swallow aerofoil profile and standard aerofoil profile NACA4412 are-10 °～40 ° at the angle of attack, and reynolds' number is the correlation curve figure of 60000,80000 o'clock lift coefficient.
Fig. 4 is under the situation of the actual blowing of tunnel test, and imitative house swallow aerofoil profile and standard aerofoil profile NACA4412 are-10 °～40 ° at the angle of attack, and reynolds' number is the correlation curve figure of 60000,80000 o'clock ratio of lift coefficient to drag coefficient.
Among the figure: r-leading-edge radius t-maximum ga(u)ge f-camber c-chord length d-bending line B-top airfoil C-lower aerofoil
Embodiment:
With reference to figure 1, the chord length c of imitative house swallow aerofoil profile is a unit length 1, and leading-edge radius r is 0.00679, and maximum ga(u)ge t is 0.0573, and camber f is 0.0771, and the maximum ga(u)ge position is: x
t/ c=27.3%, promptly the position at maximum ga(u)ge t place is 27.3% of chord length c; The position of camber is: x
f/ c=54.5%, promptly the position at camber f place accounts for 54.5% of chord length, wherein x
tBe the abscissa value of maximum ga(u)ge position on aerofoil profile, x
fBe the abscissa value of camber position on aerofoil profile.Leading-edge radius has reduced about 1 times than standard aerofoil profile NACA4412, thereby this wind-exposuring area that can reduce aerofoil profile reduces pressure drag; Maximum ga(u)ge is compared with the standard aerofoil profile and has been reduced about 1.1 times, can prevent that the air-flow on the aerofoil profile from premature disengagement occurring when flowing through upper surface, causes loss of lift; The maximum camber of imitative house swallow aerofoil profile approximately is about 2 times of standard aerofoil profile apparently higher than the standard aerofoil profile, and this just makes the upper and lower airfoil surface current difference of imitative house swallow aerofoil profile strengthen, thereby aerofoil profile upper and lower surfaces pressure difference strengthens, so lift increases.
Imitative house swallow aerofoil profile 1, the pairing coordinate figure of its upper and lower aerofoil satisfies following table:
Table 1
Imitative house swallow aerofoil profile 2, the pairing coordinate figure of its upper and lower aerofoil satisfies following table:
Table 2
Fig. 3 is the change curve of the lift coefficient of imitative house swallow aerofoil profile and standard aerofoil profile with the angle of attack, tests obtaining through actual blowing at wind tunnel laboratory.Can find out the whole overgauge aerofoil profiles of lift coefficient of imitative house swallow aerofoil profile.And along with the increase lift coefficient of the angle of attack is the trend of growth, when the angle of attack was increased to 40 ° of left and right sides, lift coefficient began to have a declining tendency.As can be seen from the figure when reynolds' number is 60000, the lift coefficient of imitative house swallow aerofoil profile reached maximum when the angle of attack was 38 °, was 0.3488; And standard aerofoil profile NACA4412 is 60000 o'clock at reynolds' number, and maximum lift coefficient is 0.256, and imitative house swallow aerofoil profile can increase by 36.25% than the lift coefficient of standard aerofoil profile NANCA4412.The lift coefficient of imitative house swallow aerofoil profile improves 36.25%, 26.9% respectively than standard aerofoil profile when reynolds' number is respectively 60000,80000.
Fig. 4 is ratio of lift coefficient to drag coefficient the plotted curve under different Reynolds number and the different angle of attack of imitative house swallow aerofoil profile with the standard aerofoil profile.When reynolds' number is 80000, when the angle of attack was 4 °, the ratio of lift coefficient to drag coefficient of imitative house swallow aerofoil profile was 6.5 to the maximum, had increased by 30% than the maximum lift-drag ratio 5 of standard aerofoil profile.Imitative house swallow aerofoil profile has improved 28.9%, 38.5% respectively than the ratio of lift coefficient to drag coefficient of standard aerofoil profile when reynolds' number is respectively 60000,80000.
Can find out that to sum up working as the angle of attack is-10 °～40 °; Reynolds' number is respectively 60000,80000 o'clock imitative house swallow aerofoil profiles and has better lift and ratio of lift coefficient to drag coefficient than standard aerofoil profile NACA4412; Be applied on the horizontal axis wind-driven generator and can better improve wind energy utilization, reduce energy loss.
Claims (3)
1. pneumatic equipment blades made aerofoil profile; Form by chord length, thickness, leading-edge radius and camber; It is characterized in that said chord length (c) is at 1 o'clock, the span of maximum ga(u)ge (t) is 0.0573～0.0617; The span of said leading-edge radius (r) is 0.00522～0.00679; The span of said camber (f) is 0.0708～0.0771, and the position at maximum ga(u)ge (t) place account for chord length (c) span 27.3%～36.4%, the position at said maximum camber (t) place accounts for 45.5%～54.5% of said chord length (c) scope.
2. a kind of pneumatic equipment blades made aerofoil profile according to claim 1 is characterized in that, the pairing coordinate figure of the upper and lower aerofoil of said aerofoil profile satisfies:
3. a kind of pneumatic equipment blades made aerofoil profile according to claim 1 is characterized in that, the pairing coordinate figure of the upper and lower aerofoil of said aerofoil profile is full:
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| CN2011103859511A CN102400847B (en) | 2011-11-29 | 2011-11-29 | Wind-driven generator blade wing section |
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| CN102400847A true CN102400847A (en) | 2012-04-04 |
| CN102400847B CN102400847B (en) | 2013-06-19 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103133273A (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 |
| CN103244359A (en) * | 2013-05-30 | 2013-08-14 | 国电联合动力技术有限公司 | Moderate-thickness airfoil blade of large-scale fan |
| CN103883483A (en) * | 2014-04-17 | 2014-06-25 | 吉林大学 | 100 W wind turbine blade |
| CN104214054A (en) * | 2014-08-28 | 2014-12-17 | 吉林大学 | Small-sized wind power generator blade |
| CN105844034A (en) * | 2016-03-30 | 2016-08-10 | 刘雄飞 | Sparrow hawk wing section bionic method for blades of horizontal-axis wind turbines |
| CN108397344A (en) * | 2018-01-25 | 2018-08-14 | 华北电力大学 | The determination method of wind power generation blade pitch angle |
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile sideway oscillation flow tunnel testing device |
| CN109969381A (en) * | 2019-04-12 | 2019-07-05 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103133273B (en) * | 2013-03-26 | 2015-12-02 | 国电联合动力技术有限公司 | A kind of thin airfoil type blade of large fan |
| CN103133273A (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 |
| CN103244359A (en) * | 2013-05-30 | 2013-08-14 | 国电联合动力技术有限公司 | Moderate-thickness airfoil blade of large-scale fan |
| CN103883483A (en) * | 2014-04-17 | 2014-06-25 | 吉林大学 | 100 W wind turbine blade |
| CN103883483B (en) * | 2014-04-17 | 2016-04-06 | 吉林大学 | A kind of 100W blade of wind-driven generator |
| CN104214054B (en) * | 2014-08-28 | 2016-08-17 | 吉林大学 | A kind of small-sized wind power generator blade |
| CN104214054A (en) * | 2014-08-28 | 2014-12-17 | 吉林大学 | Small-sized wind power generator blade |
| CN105844034A (en) * | 2016-03-30 | 2016-08-10 | 刘雄飞 | Sparrow hawk wing section bionic method for blades of horizontal-axis wind turbines |
| CN105844034B (en) * | 2016-03-30 | 2019-07-12 | 中国矿业大学银川学院 | The sparrow hawk aerofoil profile bionic method of horizontal shaft wind-driven generator vane |
| CN108397344A (en) * | 2018-01-25 | 2018-08-14 | 华北电力大学 | The determination method of wind power generation blade pitch angle |
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile sideway oscillation flow tunnel testing device |
| CN108414182B (en) * | 2018-04-23 | 2023-11-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing type yaw oscillation wind tunnel test device |
| CN109969381A (en) * | 2019-04-12 | 2019-07-05 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of low reynolds number airfoil with high ratio of lift over drag with sharp leading edge heavy camber |
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Granted publication date: 20130619 Termination date: 20131129 |