CN101876291A - Wind turbine blade airfoil family - Google Patents
Wind turbine blade airfoil family Download PDFInfo
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- CN101876291A CN101876291A CN2009100834017A CN200910083401A CN101876291A CN 101876291 A CN101876291 A CN 101876291A CN 2009100834017 A CN2009100834017 A CN 2009100834017A CN 200910083401 A CN200910083401 A CN 200910083401A CN 101876291 A CN101876291 A CN 101876291A
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- aerofoil profile
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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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- 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
- Y02E10/74—Wind turbines with rotation axis perpendicular to the wind direction
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Abstract
The invention relates to a wind turbine blade airfoil family which comprises a first airfoil, a second airfoil, a third airfoil and a fourth airfoil which have different relative thicknesses, wherein the relative thickness is a ratio of the maximum thickness between the upper surface and the lower surface of each airfoil to the length of a chord line; each airfoil respectively comprises a front edge, a tail edge, a suction face and a pressure face; the radius of the front edge is smaller, the tail edge has the thickness of 0.25 to 0.63 percent of the chord length from the front edge to the tail edge, the suction face has smaller thickness, and the pressure face is four S-shaped post-loads; the relative thickness between the upper surface and the lower surface of the blade airfoil family is 15-25 percent; and the position of the maximum thickness of the blade airfoil family is located at a 34 to 32.3 percent point away from the front edge, wherein the profiles of the first airfoil, the second airfoil, the third airfoil and the fourth airfoil are respectively formed by smooth connection of dimensionless two-dimensional coordinates of each airfoil, and the dimensionless two-dimensional coordinates of the airfoils are obtained in such a way that the abscissa and the ordinate of each point on the pressure surfaces and the suction surfaces of the first airfoil, the second airfoil, the third airfoil and the fourth airfoil are divided by the chord length of each airfoil.
Description
Technical field
The present invention relates to a kind of pneumatic equipment blades made, particularly a kind of aerofoil profile of pneumatic equipment blades made structure family.
Background technique
The wind-power electricity generation process is mechanical energy by wind power generating set with wind energy transformation exactly, and further makes it to be converted into the process of electric energy.Blade is one of core component of wind power generating set, how the performance of blade has directly influenced the efficient of wind energy conversion, blade is generally formed to amassing to fold along exhibition by certain formative method by how much compatible good aerofoil profiles of gang, thereby the gas dynamics performance of aerofoil profile and structural behaviour directly determining the performance of blade, is the key of Blade Design.
Because the aerodynamic characteristic of aviation aerofoil profile has obtained sufficient research in 20 th Century, traditional pneumatic equipment blades made is generally continued to use the aviation aerofoil profile, as NACA44XX, NACA63XXX, NACA64XXX, NACA65XXX etc.In recent years, fast development and extensive use along with wind power technology, traditional aviation aerofoil profile more and more can not satisfy the demand of wind energy conversion system and special running environment thereof, shows highlightedly that maximum lift coefficient is higher to the receptance of preceding edge roughness, off-design performance is not good, structure and intensity can not satisfy blade and maximize and require etc.
Because outdoor operation, the leading edge of horizontal-shaft wind turbine blade usually can be subjected to the contamination of insect remains and airborne pollutant, thereby the roughness of blade inlet edge is increased.The increase of blade inlet edge roughness can make the maximum lift coefficient of aerofoil profile reduce, thereby has a strong impact on the aeroperformance of blade integral, and that reduces wind energy conversion system goes out function power.
Further, the energy overwhelming majority that blade captures concentrates on the middle part and the LHA of blade, thereby the aerofoil profile that requires this part has aerodynamic performance preferably, compare with the aerofoil profile of other positions, this section aerofoil profile should have bigger maximum lift-drag ratio, good stalling characteristics, lower roughness receptance, low noise, good how much compatibility etc.
Summary of the invention
The object of the present invention is to provide a kind of wind turbine blade airfoil family, to overcome NACA (NACA) the aviation aerofoil profile maximum lift coefficient that is widely used in pneumatic equipment blades made at present to preceding edge roughness is responsive, stalling characteristics are not good, maximum lift-drag ratio is lower, the not high shortcoming of acting ability.
For achieving the above object, wind turbine blade airfoil family provided by the invention comprises the aerofoil profile of first to fourth different relative thicknesses, and described relative thickness is the ratio of the length of the maximum ga(u)ge between each aerofoil profile upper and lower surfaces and the string of a musical instrument;
Each aerofoil profile is formed by leading edge, trailing edge, suction surface, pressure side;
Trailing edge has the thickness of chord length 0.25%～0.63% from the leading edge to trailing edge, and pressure side is to load after four S shapes;
Relative thickness between the upper and lower surfaces of this wind turbine blade airfoil family is 15%-25%;
The position of the maximum ga(u)ge of this wind turbine blade airfoil family is at distance leading edge point 34%～32.3% place;
Wherein, the profile of first to fourth aerofoil profile, be respectively by on first to fourth aerofoil profile pressure side and the suction surface by the dimensionless two-dimensional coordinate that obtains this aerofoil profile after the abscissa of each point and the chord length of y coordinate divided by this aerofoil profile, form by this dimensionless two-dimensional coordinate smooth connection.
Geometrical construction characteristics of the present invention have effectively overcome the NACA aviation aerofoil profile maximum lift coefficient that is widely used in pneumatic equipment blades made at present to preceding edge roughness is responsive, stalling characteristics are not good, maximum lift-drag ratio is lower, the not high shortcoming of acting ability.Compare with the NACA aerofoil profile, the leading edge radius of curvature of wind turbine blade airfoil family of the present invention and the thickness of suction surface are less, under identical condition, can not only effectively improve power coefficient, and can obviously improve the structural behaviour of blade, reduce blade area, reduce blade then and use material and manufacture cost.Compare with other aerofoil profile, under identical condition, can improve Wind Power Utilization efficient 20%～30%, and can obviously improve the structural behaviour of blade.
Description of drawings
Fig. 1 is the perspective view of a pneumatic equipment blades made of application family of aerofoil sections structure of the present invention.
Fig. 2 is the composite diagram of wind energy conversion system special airfoil of the present invention family.
Fig. 3 is the profile diagram of first aerofoil profile of wind energy conversion system special airfoil of the present invention family.
Fig. 4 is the profile diagram of second aerofoil profile of wind energy conversion system special airfoil of the present invention family.
Fig. 5 is the profile diagram of the 3rd aerofoil profile of wind energy conversion system special airfoil of the present invention family.
Fig. 6 is the profile diagram of the 4th aerofoil profile of wind energy conversion system special airfoil of the present invention family.
Embodiment
Below in conjunction with accompanying drawing the present invention is described in detail, be to be noted that described specific embodiment only is intended to be convenient to the understanding of the present invention, and it is not played any qualification effect.
Referring now to Fig. 1, Fig. 1 has shown the pneumatic equipment blades made 100 that uses family of aerofoil sections 140 of the present invention.Family of aerofoil sections of the present invention preferably can be used for the horizontal-shaft wind turbine blade.Blade 100 comprises medial area 110, LHA 120 and the blade tip district 130 of next-door neighbour's wheel hub (not shown).Usually, medial area 110 accounts for blade 100 and opens up 50% of length, and LHA accounts for 30% of blade 100 exhibition length, and blade tip district 130 accounts for 20% of blade 100 exhibition length.
Fig. 2 has shown wind mill airfoil of the present invention family 140.Family of aerofoil sections 140 includes leading edge 200, suction surface 220, trailing edge 210, pressure side 230 and the string of a musical instrument 190.The string of a musical instrument 190 extends to trailing edge 210 from each leading edge 200 of family of aerofoil sections 140.The leading edge angle of first aerofoil profile 150, second aerofoil profile 160, the 3rd aerofoil profile 170, the 4th aerofoil profile 180, suction surface thickness, trailing edge thickness, pressure side radian, profile thickness etc. are all inequality shown in Fig. 2, are fit to use LHA 120 and blade tip district 130 at blade shown in Figure 1 100 respectively.
All have how much good compatibility between each aerofoil profile, the blade transverse section of each aerofoil profile section is according to method as known in the art, can connect by the transitional surface that connects the appropriate section between any two adjacent air foil shapes, the aerofoil profile transverse section can translation-angle according to known method, so that blade is imported effective resistance, thereby form the blade incidence that requires determined variation by aerodynamic quality.
Profile thickness is meant the distance between the aerofoil profile upper and lower surface, and the ratio of maximum ga(u)ge and chord length is called the relative thickness of aerofoil profile.The scope of the relative thickness of family of aerofoil sections 140 is 15%-25% among the present invention, and the position of maximum ga(u)ge is at distance leading edge point 34%～32.3% place, and reynolds' number is 3 * 10
6Operating mode under, its maximum lift coefficient between 1.6-1.7, be applicable to length of blade more than 20 meters, power 600kW above, Stall Type or become the wind energy conversion system of oar type.Family of aerofoil sections of the present invention is in Re=3 * 10
6Operating mode under, stalling characteristics are good, the air-flow angle of attack greater than critical angle of attack (angle of attack of maximum lift coefficient correspondence) after, along with the increase of the angle of attack, the lift coefficient of aerofoil profile changes mild.
As can be seen, compare with the aerofoil profile of other condition of equivalent thickness from the outside geometric properties of family of aerofoil sections 140, this family of aerofoil sections leading edge 200 is point relatively, and promptly leading-edge radius is little, and the aerofoil profile leading-edge radius of different-thickness has different spans; The thickness of suction surface 220 is smaller, thus guarantee lift coefficient near or when reaching maximum, the position of the turning point on the suction surface 220 from the Laminar Flow to the turbulent flow very near or reach leading edge point 200, can reach from the position of leading edge point to 5% chord length.So just make the maximum lift coefficient of family of aerofoil sections all have the immunity of preceding edge roughness.
In the present invention, preferably, the trailing edge 210 of family of aerofoil sections 140 all has certain thickness, thickness range is 0.25%～0.63% chord length, with trailing edge thickness is that zero NACA fine stern edge aerofoil profile is compared, this geometric properties can suitably weaken the pressure recovery degree of suction surface overdraught, and making flows keeps adhering to, thereby can suitably improve the lift coefficient of aerofoil profile; In addition, also reduced the machining accuracy of manufacturing pneumatic equipment blades made to a certain extent.Preferably, can load the back loading of the S shape profile that increases body near trailing edges, improve lift coefficient at the pressure side 230 of family of aerofoil sections 140.
Fig. 3-Fig. 6 has shown the embodiment of four aerofoil profiles that family of aerofoil sections 140 of the present invention is comprised, the appearance profile of aerofoil profile among each embodiment.
The dimensionless two-dimensional coordinate data point of first aerofoil profile 150, second aerofoil profile 160, the 3rd aerofoil profile 170 and the 4th aerofoil profile 180 suction surfaces of family of aerofoil sections 140 of the present invention is listed on the suction surface hurdle respectively among the table 1-4.The string of a musical instrument of each aerofoil profile extends to trailing edge from leading edge, and the length of the string of a musical instrument is chord length, obtains the dimensionless geometric coordinate of this aerofoil profile suction surface after the abscissa of the each point on each aerofoil profile suction surface and the chord length of y coordinate divided by this aerofoil profile.The dimensionless two-dimensional coordinate data point of above-mentioned aerofoil profile pressure side is listed on the pressure side hurdle respectively among the table 1-4.Obtain the dimensionless geometric coordinate of this aerofoil profile pressure side after the abscissa of the each point on each aerofoil profile pressure side and the chord length of y coordinate divided by this aerofoil profile.Can form the suction surface and the pressure side profile of above-mentioned aerofoil profile respectively by the smooth connection of spline curve according to listed data point in the table.First, second, third aerofoil profile can be used as pneumatic equipment blades made LHA aerofoil profile; The 4th aerofoil profile can be used as pneumatic equipment blades made middle part aerofoil profile.
Certain point in the table on x/c value representation suction surface or the pressure side on string of a musical instrument direction with respect to the position of leading edge, the height of y/c value representation certain point from the string of a musical instrument to the suction surface or on the pressure side.The dimensionless two-dimensional coordinate data of describing aerofoil profile in the table can be amplified and dwindle and be kept the shape invariance of aerofoil profile, the scalable scheme of coordinate multiply by for X, Y coordinate figure among the table 1-4 or divided by non-vanishing constant, is met the aerofoil profile of the different chord lengths size of designing requirement then.
Specify each aerofoil profile below:
Fig. 3 has shown first aerofoil profile 150 of family of aerofoil sections 140 of the present invention, and preferred, the relative thickness of this aerofoil profile is 15%, is used for the blade tip district 130 of blade 100.Aerofoil profile at reynolds' number 3 * 10
6Operating mode under carry out work, and with other aerofoil profiles in the wind energy conversion system special airfoil family 140 have good how much compatible.
Concrete shape provides with the dimensionless coordinate form in table 1.On x/c value representation suction surface 153 or the pressure side 155 certain point on the string of a musical instrument 152 directions with respect to the position of leading edge 151, the y/c value then represent from the string of a musical instrument 152 to suction surface 153 or pressure side 155 on the height of certain point.These values are scalable as the function of identical constant or quantity, amplify or dwindle and aerofoil profile that shape remains unchanged so that ratio to be provided.
Table 1
Fig. 4 has shown second aerofoil profile 160 of wind energy conversion system special airfoil family 140, and its leading edge is 161, and the string of a musical instrument is 162, and suction surface is 163, and trailing edge is 164, and pressure side is 165.The thickness of this aerofoil profile is 18%, is applicable to the LHA 120 of blade 100.This aerofoil profile at reynolds' number 3 * 10
6Operating mode design, with other aerofoil profiles in the wind energy conversion system special airfoil family 140 have good how much compatible.The concrete shape of second aerofoil profile 160 provides with the dimensionless coordinate form in table 2.
Table 2
Fig. 5 has shown the 3rd aerofoil profile 170 of wind energy conversion system special airfoil family 140, and its leading edge is 171, and the string of a musical instrument is 172, and suction surface is 173, and trailing edge is 174, and pressure side is 175.The thickness of this aerofoil profile is 21%, is applicable to the LHA 120 of blade 100.This aerofoil profile at reynolds' number 3 * 10
6Operating mode design, with other aerofoil profiles in the wind energy conversion system special airfoil family 140 have good how much compatible.The concrete shape of the 3rd aerofoil profile 170 provides with the dimensionless coordinate form in table 3.
Table 3
Fig. 6 has shown the 4th aerofoil profile 180 of wind energy conversion system special airfoil family 140, and its leading edge is 181, and the string of a musical instrument is 182, and suction surface is 183, and trailing edge is 184, and pressure side is 185.The thickness of this aerofoil profile is 25%, is applicable to the LHA 120 of blade 100.This aerofoil profile at reynolds' number 3 * 10
6Operating mode design, with other aerofoil profiles in the wind energy conversion system special airfoil family 140 have good how much compatible.The concrete shape of the 4th aerofoil profile 180 provides with the dimensionless coordinate form in table 4.
Table 4
The above; only be the preferred embodiments of the present invention; protection scope of the present invention is not limited thereto; any people who is familiar with this technology can understand conversion or the replacement of expecting in the disclosed technical scope of the present invention; all should be encompassed in of the present invention comprising within the scope; therefore, protection scope of the present invention should be as the criterion with the protection domain of claims.
Claims (5)
1. wind turbine blade airfoil family comprises the aerofoil profile of first to fourth different relative thicknesses, and described relative thickness is the ratio of the length of the maximum ga(u)ge between each aerofoil profile upper and lower surfaces and the string of a musical instrument;
Each aerofoil profile is formed by leading edge, trailing edge, suction surface, pressure side;
Trailing edge has the thickness of chord length 0.25%～0.63% from the leading edge to trailing edge, and pressure side is to load after four S shapes;
Relative thickness between the upper and lower surfaces of this wind turbine blade airfoil family is 15%-25%;
The position of the maximum ga(u)ge of this wind turbine blade airfoil family is at distance leading edge point 34%～32.3% place;
Wherein, the profile of first to fourth aerofoil profile, be respectively by on first to fourth aerofoil profile pressure side and the suction surface by the dimensionless two-dimensional coordinate that obtains this aerofoil profile after the abscissa of each point and the chord length of y coordinate divided by this aerofoil profile, form by this dimensionless two-dimensional coordinate smooth connection.
2. wind turbine blade airfoil family according to claim 1, wherein, the dimensionless geometric coordinate of the first aerofoil profile suction surface and pressure side is respectively:
Wherein, on the suction surface of x/c value representation first aerofoil profile certain point on string of a musical instrument direction with respect to the position of leading edge, the height of certain point on the y/c value is then represented from the string of a musical instrument to the first aerofoil profile suction surface;
Wherein, on the pressure side of x/c value representation first aerofoil profile certain point on string of a musical instrument direction with respect to the position of leading edge, the height of certain point on the y/c value is then represented from the string of a musical instrument to the first aerofoil profile pressure side.
3. wind turbine blade airfoil family according to claim 1, wherein, the dimensionless geometric coordinate of the second aerofoil profile suction surface and pressure side is respectively:
Wherein, on the suction surface of x/c value representation second aerofoil profile certain point on string of a musical instrument direction with respect to the position of leading edge, the height of certain point on the y/c value is then represented from the string of a musical instrument to the second aerofoil profile suction surface;
Wherein, on the pressure side of x/c value representation second aerofoil profile certain point on string of a musical instrument direction with respect to the position of leading edge, the height of certain point on the y/c value is then represented from the string of a musical instrument to the first aerofoil profile pressure side.
4. wind turbine blade airfoil family according to claim 1, wherein, the dimensionless geometric coordinate of the 3rd aerofoil profile suction surface and pressure side is respectively:
Wherein, on the suction surface of x/c value representation the 3rd aerofoil profile certain point with respect to the position of leading edge, the y/c value is then represented the height of certain point from the string of a musical instrument to the three aerofoil profile suction surfaces on string of a musical instrument direction;
Wherein, on the pressure side of x/c value representation the 3rd aerofoil profile certain point with respect to the position of leading edge, the y/c value is then represented the height of certain point from the string of a musical instrument to the three aerofoil profile pressure sides on string of a musical instrument direction.
5. wind turbine blade airfoil family according to claim 1, wherein, the dimensionless geometric coordinate of the 4th aerofoil profile suction surface and pressure side is respectively:
Wherein, on the suction surface of x/c value representation the 4th aerofoil profile certain point with respect to the position of leading edge, the y/c value is then represented the height of certain point from the string of a musical instrument to the four aerofoil profile suction surfaces on string of a musical instrument direction;
Wherein, on the pressure side of x/c value representation the 4th aerofoil profile certain point with respect to the position of leading edge, the y/c value is then represented the height of certain point from the string of a musical instrument to the four aerofoil profile pressure sides on string of a musical instrument direction.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104018999A (en) * | 2014-06-18 | 2014-09-03 | 西北工业大学 | 25%-thickness main airfoil for megawatt wind turbine blade |
| CN104405596A (en) * | 2014-12-12 | 2015-03-11 | 华北电力大学 | Wind turbine generator system low-wind-speed airfoil section family |
| CN104819106A (en) * | 2015-04-30 | 2015-08-05 | 南京北大工道创新有限公司 | Wind turbine blade wing section group |
| CN105781904A (en) * | 2016-03-22 | 2016-07-20 | 西北工业大学 | 30% thickness aerofoil suitable for megawatt-grade wind turbine blade |
| CN107020548A (en) * | 2017-05-19 | 2017-08-08 | 西北工业大学 | A kind of polishing method for improving compressor blade aeroperformance |
| CN110985285A (en) * | 2019-11-21 | 2020-04-10 | 广东海洋大学 | Vertical axis wind turbine blade, vertical axis wind wheel and vertical axis wind turbine |
| CN113044199A (en) * | 2021-04-20 | 2021-06-29 | 西北工业大学 | High-performance low Reynolds number tandem laminar flow wing section based on connecting wing layout unmanned aerial vehicle |
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2009
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102062044B (en) * | 2010-12-23 | 2012-06-27 | 中国科学院工程热物理研究所 | Wind machine blade airfoil family |
| 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 |
| CN104018999B (en) * | 2014-06-18 | 2016-11-23 | 西北工业大学 | A kind of 25% thickness main wing type for blade of megawatt level wind machine |
| CN104018999A (en) * | 2014-06-18 | 2014-09-03 | 西北工业大学 | 25%-thickness main airfoil for megawatt wind turbine blade |
| CN104405596A (en) * | 2014-12-12 | 2015-03-11 | 华北电力大学 | Wind turbine generator system low-wind-speed airfoil section family |
| CN104405596B (en) * | 2014-12-12 | 2017-02-22 | 华北电力大学 | Wind turbine generator system low-wind-speed airfoil section family |
| CN104819106A (en) * | 2015-04-30 | 2015-08-05 | 南京北大工道创新有限公司 | Wind turbine blade wing section group |
| CN105781904A (en) * | 2016-03-22 | 2016-07-20 | 西北工业大学 | 30% thickness aerofoil suitable for megawatt-grade wind turbine blade |
| CN107020548A (en) * | 2017-05-19 | 2017-08-08 | 西北工业大学 | A kind of polishing method for improving compressor blade aeroperformance |
| CN110985285A (en) * | 2019-11-21 | 2020-04-10 | 广东海洋大学 | Vertical axis wind turbine blade, vertical axis wind wheel and vertical axis wind turbine |
| CN110985285B (en) * | 2019-11-21 | 2024-05-31 | 广东海洋大学 | Vertical axis wind turbine blade, vertical axis wind wheel and vertical axis wind turbine |
| CN113044199A (en) * | 2021-04-20 | 2021-06-29 | 西北工业大学 | High-performance low Reynolds number tandem laminar flow wing section based on connecting wing layout unmanned aerial vehicle |
| CN113044199B (en) * | 2021-04-20 | 2023-12-15 | 西北工业大学 | High-performance low-Reynolds number serial laminar flow wing profile based on coupling wing layout unmanned aerial vehicle |
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Effective date of registration: 20170823 Address after: 300392 Tianjin City Huayuan Industrial Zone Branch Road No. 15 Building No. 5 Room 501 Patentee after: Zhongke Guofeng science and Technology Co Ltd Address before: 100190 No. 11 West Fourth Ring Road, Beijing Patentee before: Institute of Engineering Thermophysics, Chinese Academy of Sciences |