CN208486977U - Vane airfoil profile and wind-driven generator - Google Patents
Vane airfoil profile and wind-driven generator Download PDFInfo
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- CN208486977U CN208486977U CN201820852033.2U CN201820852033U CN208486977U CN 208486977 U CN208486977 U CN 208486977U CN 201820852033 U CN201820852033 U CN 201820852033U CN 208486977 U CN208486977 U CN 208486977U
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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 utility model relates to technical field of wind power generation, are related to vane airfoil profile and wind-driven generator.Vane airfoil profile includes following geometrical structure parameter: first thickness peak value T1 occurs in x1；T1 is located at c*14.0%~c*15.3%, and x1 is located at c*5.5%~c*6.3%；There is second thickness peak value T2 in x2, T2 is aerofoil profile maximum gauge；T2 is located at c*25.5%~c*25.9%, and x2 is located at c*29.1%~c*31.1%；There is thickness valley T3 in the third place point x3 between first position point x1 and second position point x2；T3 is located at T2*84.5%~T2*88.2%；X3 is located at c*14.0%~c*15.9%.For vane airfoil profile compared with conventional NACA aerofoil profile, profile drag is small, and lift resistance ratio is high, has superior aeroperformance.Wind-driven generator has above-mentioned advantage compared with prior art.
Description
Technical field
The utility model relates to technical field of wind power generation, in particular to vane airfoil profile and wind-driven generator.
Background technique
As energy issue of world becomes increasingly conspicuous, wind energy is rapidly developed as environmental-friendly renewable energy.Wind
Power machine blade is the core component of Wind turbines, and blade is opened up along it to being formed by stacking from aerofoil profile, therefore airfoil performance
Quality directly determines the superiority and inferiority of Wind turbines performance.With Wind turbines constantly enlargement development, blade is increasingly longer, especially
It is that root of blade has higher requirement to the structure and aerodynamic characteristic of aerofoil profile.
Increasing profile thickness can be improved the architectural characteristic of aerofoil profile, but with the increase of profile thickness, the pneumatic property of aerofoil profile
It can reduce, for example the maximum lift coefficient and maximum lift-drag ratio of aerofoil profile can reduce, the coarse sensibility of the leading edge of aerofoil profile will increase
Deng.And the aerodynamic characteristic of thick wing type can be improved while meeting airfoil structure characteristic using blunt trailing edge, increase aerofoil profile trailing edge
Thickness can reduce the suction gradient of airfoil suction side, postpone aerofoil profile turbulence separation, to improve wing section lift coefficient, reduce the wing
The coarse sensibility of type leading edge.
Utility model content
The purpose of this utility model is to provide a kind of vane airfoil profile and wind-driven generator, there is high lift-drag ratio and more excellent
Aeroperformance.
In a first aspect, the utility model embodiment provides a kind of vane airfoil profile, including following geometrical structure parameter: with the wing
The tie point of type upper and lower surface is coordinate origin, establishes rectangular coordinate system using straight line where aerofoil profile chord length as X-axis, indicates string with c
It is long；
In first position, there is first thickness peak value T1 in point x1；T1 is located in following interval range: c*14.0%~c*
15.3%, x1 are located in following interval range: c*5.5%~c*6.3%；
In the second position, there is second thickness peak value T2 in point x2, and T2 is aerofoil profile maximum gauge；T2 is located at following interval range
Interior: c*25.5%~c*25.9%, x2 are located in following interval range: c*29.1%~c*31.1%；
There is thickness valley T3 in the third place point x3 between first position point x1 and second position point x2；T3 be located at
In lower interval range: T2*84.5%~T2*88.2%；X3 is located in following interval range: c*14.0%~c*15.9%.
With reference to first aspect, the utility model embodiment provides the first possible embodiment of first aspect,
In, T1=c*14.9%；X1=c*6.2%；
T2=c*25.7%；X2=c*30.4%；
T3=T2*85.1%；X3=c*15.3%.
With reference to first aspect, the utility model embodiment provides the first possible embodiment of first aspect,
In, above-mentioned aerofoil profile maximum camber f is located in following interval range: c*3.5%~c*4.5%；Maximum opposite camber is located at following
In interval range: c*38.0%~c*40.0%.
With reference to first aspect, the utility model embodiment provides the first possible embodiment of first aspect,
In, above-mentioned aerofoil profile maximum camber f=c*4.1%；Maximum opposite camber is located at 38.9% chord length.
With reference to first aspect, the utility model embodiment provides the first possible embodiment of first aspect,
In, from leading edge, in region at 13%~15% chord length, profile thickness change rate becomes higher than other area thickness of aerofoil profile
Rate.
With reference to first aspect, the utility model embodiment provides the first possible embodiment of first aspect,
In, from leading edge, in region at 20% chord length, profile thickness change rate is higher than other area thickness change rates of aerofoil profile.
With reference to first aspect, the utility model embodiment provides the first possible embodiment of first aspect,
In, above-mentioned aerofoil profile upper surface curvature variation is less than aerofoil profile lower surface curvature variation.
With reference to first aspect, the utility model embodiment provides the first possible embodiment of first aspect,
In, the upper surface data point coordinate of above-mentioned aerofoil profile is shown in Table 1；The lower surface data point coordinate of aerofoil profile is shown in Table 2；
1 aerofoil profile upper surface data point of table
2 aerofoil profile lower surface data point of table
| x | y | x | y | x | y |
| 0 | -0.00041 | 0.08564 | -0.08771 | 0.5151 | -0.09626 |
| 0.00015 | -0.00369 | 0.09488 | -0.09167 | 0.53961 | -0.09163 |
| 0.00053 | -0.00705 | 0.10491 | -0.09556 | 0.56445 | -0.08675 |
| 0.00116 | -0.01047 | 0.11577 | -0.09937 | 0.5896 | -0.08161 |
| 0.00205 | -0.01392 | 0.12749 | -0.10305 | 0.61505 | -0.07625 |
| 0.00321 | -0.01741 | 0.1401 | -0.10654 | 0.64077 | -0.07074 |
| 0.00462 | -0.02091 | 0.15359 | -0.10979 | 0.66669 | -0.06512 |
| 0.0063 | -0.02443 | 0.16797 | -0.11276 | 0.69264 | -0.05946 |
| 0.00824 | -0.02795 | 0.18321 | -0.11538 | 0.71851 | -0.05385 |
| 0.01045 | -0.03149 | 0.1993 | -0.11762 | 0.74415 | -0.04835 |
| 0.01293 | -0.03503 | 0.2162 | -0.11944 | 0.76952 | -0.04303 |
| 0.01568 | -0.03858 | 0.23386 | -0.1208 | 0.79456 | -0.03793 |
| 0.01872 | -0.04216 | 0.25224 | -0.12168 | 0.81924 | -0.03308 |
| 0.02205 | -0.04575 | 0.27131 | -0.12208 | 0.8435 | -0.02852 |
| 0.0257 | -0.04937 | 0.29101 | -0.12198 | 0.86731 | -0.02426 |
| 0.02968 | -0.05303 | 0.31133 | -0.12139 | 0.89051 | -0.02033 |
| 0.03402 | -0.05672 | 0.33219 | -0.12031 | 0.91295 | -0.01674 |
| 0.03874 | -0.06045 | 0.35357 | -0.11876 | 0.93436 | -0.01349 |
| 0.04387 | -0.06423 | 0.37543 | -0.11676 | 0.95446 | -0.01057 |
| 0.04945 | -0.06805 | 0.39775 | -0.11432 | 0.97297 | -0.00799 |
| 0.05552 | -0.07192 | 0.42048 | -0.11146 | 0.98974 | -0.00572 |
| 0.06212 | -0.07584 | 0.44359 | -0.1082 | 1 | -0.00434 |
| 0.06931 | -0.07978 | 0.46708 | -0.10456 | ||
| 0.07713 | -0.08375 | 0.49091 | -0.10057 |
With reference to first aspect, the utility model embodiment provides the first possible embodiment of first aspect,
In, above-mentioned vane airfoil profile is used for wind power generation blade.
Second aspect, the utility model embodiment provides a kind of wind-driven generator, including is made of the vane airfoil profile
Wind blade and engine block；
The wind blade is connect with the engine block.
The utility model has the advantages that
The utility model embodiment provides a kind of vane airfoil profile, including following geometrical structure parameter: with following table in aerofoil profile
The tie point in face is coordinate origin, is that X axis establishes rectangular coordinate system with straight line where aerofoil profile chord length, indicates chord length with c；?
There is first thickness peak value T1 in one location point x1；T1 is located in following interval range: c*14.0%~c*15.3%, x1 be located at
In lower interval range: c*5.5%~c*6.3%；In the second position, there is second thickness peak value T2 in point x2, and T2 is that aerofoil profile is maximum thick
Degree；T2 is located in following interval range: c*25.5%~c*25.9%, x2 are located in following interval range: c*29.1%~c*
31.1%；There is thickness valley T3 in the third place point x3 between first position point x1 and second position point x2；T3 be located at
In lower interval range: T2*84.5%~T2*88.2%；X3 is located in following interval range: c*14.0%~c*15.9%.Leaf
Piece aerofoil profile has the advantage that profile drag is small compared with conventional NACA aerofoil profile, and lift resistance ratio is high, has superior pneumatic property
Energy.
The utility model embodiment provides a kind of wind-driven generator, including wind blade and hair made of vane airfoil profile
Motor body；Wind blade is connect with engine block.Wind-driven generator has above-mentioned advantage compared with prior art, herein
It repeats no more.
Other feature and advantage of the utility model will illustrate in the following description, also, partly from specification
In become apparent, or understood and implementing the utility model.The purpose of this utility model and other advantages are illustrating
Specifically noted structure is achieved and obtained in book, claims and attached drawing.
To enable the above objects, features, and advantages of the utility model to be clearer and more comprehensible, preferred embodiment is cited below particularly, and
Cooperate appended attached drawing, is described in detail below.
Detailed description of the invention
It, below will be right in order to illustrate more clearly of specific embodiment of the present invention or technical solution in the prior art
Specific embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, it is described below
In attached drawing be that some embodiments of the utility model are not paying creativeness for those of ordinary skill in the art
Under the premise of labour, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is for vane airfoil profile provided by the embodiment of the utility model and in the prior art outside the geometry of naca4423 aerofoil profile
Shape figure；
Fig. 2 is that vane airfoil profile provided by the embodiment of the utility model and the difference of naca4423 aerofoil profile in the prior art are attacked
Angle lift curve；
Fig. 3 is that vane airfoil profile provided by the embodiment of the utility model and the difference of naca4423 aerofoil profile in the prior art are attacked
Angle resistance curve；
Fig. 4 is that vane airfoil profile provided by the embodiment of the utility model and the difference of naca4423 aerofoil profile in the prior art are attacked
Angle rises resistance curve；
Fig. 5 is vane airfoil profile provided by the embodiment of the utility model and naca4423 airfoil tip speed ratio in the prior art
With cp curve；
Fig. 6 is vane airfoil profile provided by the embodiment of the utility model and naca4423 aerofoil profile wind speed and function in the prior art
Rate curve.
Specific embodiment
The technical solution of the utility model is clearly and completely described below in conjunction with attached drawing, it is clear that described
Embodiment is the utility model a part of the embodiment, instead of all the embodiments.Based on the embodiments of the present invention, originally
Field those of ordinary skill every other embodiment obtained without making creative work belongs to practical
Novel protected range.
In the description of the present invention, it should be understood that term " center ", " longitudinal direction ", " transverse direction ", " length ", " width
Degree ", " thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside",
The orientation or positional relationship of the instructions such as " clockwise ", " counterclockwise ", " axial direction ", " radial direction ", " circumferential direction " is based on the figure
Orientation or positional relationship is merely for convenience of describing the present invention and simplifying the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as to the utility model
Limitation.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more of the features.The meaning of " plurality " is two or two in the description of the present invention,
More than, unless otherwise specifically defined.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " Gu
It is fixed " etc. terms shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；It can be
Mechanical connection, is also possible to be electrically connected；It can be directly connected, two can also be can be indirectly connected through an intermediary
The interaction relationship of connection or two elements inside element.It for the ordinary skill in the art, can basis
Concrete condition understands the concrete meaning of above-mentioned term in the present invention.
The utility model is further described in detail below through specific implementation examples and in conjunction with the accompanying drawings.
It should be noted that tonex26 is to use vane airfoil profile provided by the embodiment of the utility model in following picture and text
Blade model is made, naca4423 is the common blade model compared with tonex26.
With reference to shown in Fig. 1-Fig. 6:
The utility model embodiment provides a kind of vane airfoil profile, including following geometrical structure parameter: with following table in aerofoil profile
The tie point in face is coordinate origin, is that X axis establishes rectangular coordinate system with straight line where aerofoil profile chord length, indicates chord length with c；?
There is first thickness peak value T1 in one location point x1；T1 is located in following interval range: c*14.0%~c*15.3%, x1 be located at
In lower interval range: c*5.5%~c*6.3%；In the second position, there is second thickness peak value T2 in point x2, and T2 is that aerofoil profile is maximum thick
Degree；T2 is located in following interval range: c*25.5%~c*25.9%, x2 are located in following interval range: c*29.1%~c*
31.1%；There is thickness valley T3 in the third place point x3 between first position point x1 and second position point x2；T3 be located at
In lower interval range: T2*84.5%~T2*88.2%；X3 is located in following interval range: c*14.0%~c*15.9%.
Vane airfoil profile has the advantage that profile drag is small compared with conventional NACA aerofoil profile, and lift resistance ratio is high, has more excellent
Different aeroperformance.
In the optinal plan of the present embodiment, T1=c*14.9%；X1=c*6.2%；T2=c*25.7%；X2=c*
30.4%；T3=T2*85.1%；X3=c*15.3%.
In the optinal plan of the present embodiment, aerofoil profile maximum camber f is located in following interval range: c*3.5%~c*
4.5%；Maximum opposite camber is located in following interval range: c*38.0%~c*40.0%.
In the optinal plan of the present embodiment, aerofoil profile maximum camber f=c*4.1%；Maximum opposite camber is located at 38.9% string
Strong point.
In the optinal plan of the present embodiment, from leading edge, in region at 13%~15% chord length, profile thickness becomes
Rate is higher than other area thickness change rates of aerofoil profile.
In the optinal plan of the present embodiment, from leading edge, in region at 20% chord length, profile thickness change rate is high
In other area thickness change rates of aerofoil profile.
In the optinal plan of the present embodiment, aerofoil profile upper surface curvature variation is less than aerofoil profile lower surface curvature variation.
Wherein, the naca4423 aerofoil profile in Fig. 5 and vane airfoil profile provided by the embodiment of the utility model are in the identical wind of use
It is measured on the basis of size of wheel.
According to Fig.5, in same variable, vane airfoil profile performance provided by the embodiment of the utility model is obviously excellent
In naca4423 aerofoil profile.
Naca4423 aerofoil profile in Fig. 6 and vane airfoil profile provided by the embodiment of the utility model are in the identical wind wheel ruler of use
It is very little, it is measured on the basis of same rotational speed.
According to Fig.6, in same variable, vane airfoil profile performance provided by the embodiment of the utility model is obviously excellent
In naca4423 aerofoil profile.
In the optinal plan of the present embodiment, the upper surface data point coordinate of aerofoil profile is shown in Table 1；The lower surface data point of aerofoil profile is sat
Mark is shown in Table 2；
1 aerofoil profile upper surface data point of table
2 aerofoil profile lower surface data point of table
| x | y | x | y | x | y |
| 0 | -0.00041 | 0.08564 | -0.08771 | 0.5151 | -0.09626 |
| 0.00015 | -0.00369 | 0.09488 | -0.09167 | 0.53961 | -0.09163 |
| 0.00053 | -0.00705 | 0.10491 | -0.09556 | 0.56445 | -0.08675 |
| 0.00116 | -0.01047 | 0.11577 | -0.09937 | 0.5896 | -0.08161 |
| 0.00205 | -0.01392 | 0.12749 | -0.10305 | 0.61505 | -0.07625 |
| 0.00321 | -0.01741 | 0.1401 | -0.10654 | 0.64077 | -0.07074 |
| 0.00462 | -0.02091 | 0.15359 | -0.10979 | 0.66669 | -0.06512 |
| 0.0063 | -0.02443 | 0.16797 | -0.11276 | 0.69264 | -0.05946 |
| 0.00824 | -0.02795 | 0.18321 | -0.11538 | 0.71851 | -0.05385 |
| 0.01045 | -0.03149 | 0.1993 | -0.11762 | 0.74415 | -0.04835 |
| 0.01293 | -0.03503 | 0.2162 | -0.11944 | 0.76952 | -0.04303 |
| 0.01568 | -0.03858 | 0.23386 | -0.1208 | 0.79456 | -0.03793 |
| 0.01872 | -0.04216 | 0.25224 | -0.12168 | 0.81924 | -0.03308 |
| 0.02205 | -0.04575 | 0.27131 | -0.12208 | 0.8435 | -0.02852 |
| 0.0257 | -0.04937 | 0.29101 | -0.12198 | 0.86731 | -0.02426 |
| 0.02968 | -0.05303 | 0.31133 | -0.12139 | 0.89051 | -0.02033 |
| 0.03402 | -0.05672 | 0.33219 | -0.12031 | 0.91295 | -0.01674 |
| 0.03874 | -0.06045 | 0.35357 | -0.11876 | 0.93436 | -0.01349 |
| 0.04387 | -0.06423 | 0.37543 | -0.11676 | 0.95446 | -0.01057 |
| 0.04945 | -0.06805 | 0.39775 | -0.11432 | 0.97297 | -0.00799 |
| 0.05552 | -0.07192 | 0.42048 | -0.11146 | 0.98974 | -0.00572 |
| 0.06212 | -0.07584 | 0.44359 | -0.1082 | 1 | -0.00434 |
| 0.06931 | -0.07978 | 0.46708 | -0.10456 | ||
| 0.07713 | -0.08375 | 0.49091 | -0.10057 |
The utility model embodiment provides a kind of wind-driven generator, including wind blade and hair made of vane airfoil profile
Motor body；Wind blade is connect with engine block.
Wind-driven generator can be improved hair using wind blade made of vane airfoil profile provided by the embodiment of the utility model
Electrical efficiency.It is specific as shown in Figure 6.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " example ", " specifically show
The description of example " or " some examples " etc. means specific features, structure, material or spy described in conjunction with this embodiment or example
Point is contained at least one embodiment or example of the utility model.In the present specification, to the schematic table of above-mentioned term
It states and is necessarily directed to identical embodiment or example.Moreover, particular features, structures, materials, or characteristics described can be with
It can be combined in any suitable manner in any one or more of the embodiments or examples.In addition, without conflicting with each other, this field
Technical staff can by the feature of different embodiments or examples described in this specification and different embodiments or examples into
Row combination and combination.
Although the embodiments of the present invention have been shown and described above, it is to be understood that above-described embodiment is
Illustratively, it should not be understood as limiting the present invention, those skilled in the art are in the scope of the utility model
Inside it can make changes, modifications, alterations, and variations to the above described embodiments.
Claims (10)
1. a kind of vane airfoil profile, which is characterized in that including following geometrical structure parameter: being to sit with the tie point of aerofoil profile upper and lower surface
Origin is marked, rectangular coordinate system is established using straight line where aerofoil profile chord length as X-axis, indicates chord length with c；
In first position, there is first thickness peak value T1 in point x1；T1 is located in following interval range: c*14.0%~c*
15.3%, x1 are located in following interval range: c*5.5%~c*6.3%；
In the second position, there is second thickness peak value T2 in point x2, and T2 is aerofoil profile maximum gauge；T2 is located in following interval range:
C*25.5%~c*25.9%, x2 are located in following interval range: c*29.1%~c*31.1%；
There is thickness valley T3 in the third place point x3 between first position point x1 and second position point x2；T3 is located at following area
Between in range: T2*84.5%~T2*88.2%；X3 is located in following interval range: c*14.0%~c*15.9%.
2. vane airfoil profile according to claim 1, which is characterized in that
T1=c*14.9%；X1=c*6.2%；
T2=c*25.7%；X2=c*30.4%；
T3=T2*85.1%；X3=c*15.3%.
3. vane airfoil profile according to claim 1, which is characterized in that aerofoil profile maximum camber f is located in following interval range:
C*3.5%~c*4.5%；Maximum opposite camber is located in following interval range: c*38.0%~c*40.0%.
4. vane airfoil profile according to claim 3, which is characterized in that aerofoil profile maximum camber f=c*4.1%；It is maximum opposite
Camber is located at 38.9% chord length.
5. vane airfoil profile according to claim 1, which is characterized in that further include: from leading edge to 13%~15% chord length
In the region at place, profile thickness change rate is higher than other area thickness change rates of aerofoil profile.
6. vane airfoil profile according to claim 1, which is characterized in that from leading edge in region at 20% chord length,
Profile thickness change rate is higher than other area thickness change rates of aerofoil profile.
7. vane airfoil profile according to claim 1, which is characterized in that aerofoil profile upper surface curvature variation is less than aerofoil profile following table
Face curvature change rate.
8. vane airfoil profile according to claim 1-7, which is characterized in that the upper surface data point coordinate of aerofoil profile
It is shown in Table 1；The lower surface data point coordinate of aerofoil profile is shown in Table 2；
1 aerofoil profile upper surface data point of table
2 aerofoil profile lower surface data point of table
。
9. vane airfoil profile according to claim 8, which is characterized in that the vane airfoil profile is used for wind power generation blade.
10. a kind of wind-driven generator, which is characterized in that including made of the described in any item vane airfoil profiles of claim 1-9
Wind blade and engine block；
The wind blade is connect with the engine block.
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| CN108468620A (en) * | 2018-06-01 | 2018-08-31 | 天津超算科技有限公司 | Vane airfoil profile and wind-driven generator |
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| CN108468620A (en) * | 2018-06-01 | 2018-08-31 | 天津超算科技有限公司 | Vane airfoil profile and wind-driven generator |
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