CN112922774A - High-lift wind turbine wing section - Google Patents
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- CN112922774A CN112922774A CN202110287274.3A CN202110287274A CN112922774A CN 112922774 A CN112922774 A CN 112922774A CN 202110287274 A CN202110287274 A CN 202110287274A CN 112922774 A CN112922774 A CN 112922774A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/0608—Rotors characterised by their aerodynamic shape
- F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
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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 discloses a high-lift wind turbine airfoil profile, which takes an S809 airfoil profile as a basic profile, reduces the chord length of an NACA4412 airfoil profile after multiplying a scaling factor alpha, and rotates by a fixed angle beta based on a trailing edge point after the airfoil profile is contracted; at the trailing edge, when the ordinate of the S809 airfoil upper surface is less than the ordinate of the NACA4412 airfoil, this portion of the upper surface of the S809 airfoil is replaced by the surface of the NACA4412 airfoil. The middle section of the upper surface of the wing profile is in smooth transition, the adverse pressure gradient of the wing profile under a large attack angle is ensured to be smaller, and further airflow separation is inhibited.
Description
Technical Field
The invention belongs to the technical field of wind power generation, and particularly relates to a high-lift wind turbine airfoil profile for a wind generating set.
Background
For the geometric shape of the wind turbine blade, the airfoil shape is a 'gene' forming the blade, and the aerodynamic performance of the airfoil shape directly influences the aerodynamic performance of the wind turbine blade, so that the design of the aerodynamic shape of the wind turbine blade of the wind turbine generator set cannot be separated from the design of the airfoil shape. Before the 80's of the last century, aerofoils were commonly used for wind turbine airfoils. However, aeronautical airfoils are usually designed under pressure-sound velocity conditions, aerodynamic performance cannot be effectively guaranteed under low velocity conditions, and in additionThe defect that the thickness is small and the structural requirement cannot be met exists, and meanwhile, the stalling of the airfoil profile is serious under a large attack angle. Therefore, the current research on aeronautical airfoils has difficulty in meeting the design requirements of wind wheels. Therefore, from the 80 s of the 20 th century, the demand for a special airfoil profile for a high-performance wind turbine is more urgent with the trend of increasing the size of the wind turbine blade. In the last century, various foreign institutions developed researches on special airfoils for large-sized wind turbines, and achieved great results, and formed multiple series of special airfoils for wind turbines, such as NACA series airfoils designed by the National Aeronautics and Space Administration (NASA), NREL-S series airfoils designed by the National Renewable Energy Laboratory (NREL), DU series airfoils designed by the Delft university of the Netherlands, and Denmark
The series of wing profiles, FFA series of wing profiles designed by Swedish aviation research institute and the like are adopted by numerous wind power enterprises, and play a vital role in improving the performance of the wind driven generator.
The existing vertical axis wind turbine mostly adopts an S809 wing type, the vicinity of the trailing edge of a wing type suction surface is in smooth transition, and the pneumatic performance of the wing type suction surface can effectively improve the wind energy absorption efficiency of a wind wheel, so that the economic efficiency of the wind turbine is improved. However, although the airfoil profile can ensure that the airfoil profile has a lower resistance coefficient under a small attack angle, airflow separation is easy to occur under a large attack angle, so that the lift coefficient is reduced, the resistance coefficient is increased, and the economic benefit of the wind wheel of the wind turbine is reduced, therefore, the aerodynamic efficiency of the vertical axis wind turbine is not high under a low wind speed.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a high-lift wind turbine airfoil profile for a wind turbine generator system, which can improve the lift coefficient, realize a larger stall angle of attack and smaller resistance, and thus improve the wind energy absorption efficiency of the wind turbine generator system.
The invention is realized by the following steps that the high-lift wind turbine wing section takes the curve profile of the S809 wing section as a prototype, and the structure of the high-lift wind turbine wing section is described as follows:
respectively carrying out front projection on the S809 airfoil profile and the NACA4412 airfoil profile in the same X-Y coordinate system to respectively obtain an S809 airfoil profile and an NACA4412 airfoil profile, and coinciding the S809 airfoil profile with the trailing edge point O of the NACA4412 airfoil profile;
reducing the whole NACA4412 airfoil profile by a scaling factor alpha, and rotating the reduced NACA4412 airfoil profile by an angle beta around the trailing edge point O so that the upper chord of the NACA4412 airfoil profile and the S809 airfoil profile intersects at a point A (x, y);
when the value of y, the ordinate in point A is less than the maximum ordinate value of the NACA4412 airfoil profile, the face between the NACA4412 airfoils O-A is substituted for the face between the S809 airfoils O-A.
Preferably, the value range of the scale factor alpha is 0.2-0.5.
Preferably, the outer surface of the high-lift wind turbine airfoil consists of S1-S5 sections which are sequentially connected end to end, the S1-S3 sections form the upper surface of the airfoil, and the S4-S5 sections form the lower surface of the airfoil; the section S1 is butted with the section S5 at a front edge point, the section S3 is butted with the section S4 at a rear edge point O, and the section S3 is a surface between the NACA4412 airfoils O-A; wherein,
the sections S1 and S5 are leading edge contraction sections of the airfoil; the S2 section is a smooth transition section of the upper surface of the airfoil; the section S3 is an airfoil upper surface trailing edge section; the section S4 is an airfoil lower surface trailing edge section;
the S3 segment is changed according to the scale factor, and the S1 segment, the S2 segment, the S4 segment and the S5 segment are changed along with the change of the S3 segment on the premise that the S1 segment, the S2 segment, the S4 segment and the S5 segment are consistent with the curve profile of the S809 airfoil.
Preferably, the camber line of the high-lift wind turbine airfoil is in an S shape, the front section of the camber line is concave, the rear section of the camber line is convex, and the intersection point of the camber line and the chord line of the airfoil is located at 0.46 unit;
the maximum thickness of the airfoil is 0.199 units, the chord-wise position corresponding to the maximum thickness is 0.349 units away from the front edge point, and the included angle of the rear edge is 13.36 degrees;
the length of the S1 section is greater than 0.0 unit and less than 0.39 unit; the length of the S2 section is greater than 0.39 units and less than 0.85 units; the length of the S3 section is greater than 0.85 unit and less than 1.0 unit; the length of the S4 section is greater than 0.32 unit and less than 1.0 unit; the length of S5 is greater than 0.0 units and less than 0.32 units;
wherein 1 said unit is equal to the chord length of said airfoil.
Compared with the defects and shortcomings of the prior art, the invention has the following beneficial effects: the invention provides a high-lift wing profile suitable for a wind turbine, the middle section of the upper surface of the wing profile is in smooth transition, the adverse pressure gradient of the wing profile under a large attack angle is ensured to be smaller, further, the airflow separation is inhibited, the wing profile has a larger lift coefficient, a larger stall attack angle and smaller resistance, and the wind energy absorption efficiency of a wind wheel of a wind generating set is improved.
Drawings
FIG. 1 is a geometric profile of an airfoil of the present invention;
FIG. 2 is a geometric configuration of an airfoil of the present invention;
FIG. 3 is a comparison of the geometry of the airfoil of the present invention with the comparative airfoil 1; the comparison airfoil profile 1 is a classical wind turbine airfoil profile S809;
in fig. 1 to 3, O (1.0, 0) is the trailing edge point, and point a (x, y) is the upper chord intersection point of the NACA4412 airfoil profile and the S809 airfoil profile; the solid line indicated by an arrow 1 is the upper chord edge of the airfoil profile, the combined line of the solid line indicated by an arrow 2 and the dashed line is the upper chord edge of the existing S809 airfoil profile, and the dashed line indicated by an arrow NACA4412 is the overall profile of the NACA4412 airfoil profile which is reduced by a scale factor alpha and is rotated by an angle beta by taking a trailing edge point O as the center;
FIG. 4 is a turbulent viscosity comparison of an airfoil of the present invention with a comparative airfoil 1; wherein, fig. a is a comparison airfoil 1, fig. B is an airfoil of the present invention;
FIG. 5 is a comparison of the surface pressure characteristics of the airfoil of the present invention and the comparative airfoil 1;
FIG. 6 is a comparison of lift to drag characteristics of an airfoil of the present invention and a comparative airfoil 1;
in the above fig. 5 to 6, the line 1 is the airfoil profile of the present invention, and the line 2 is the comparative airfoil profile 1; calculating the state: ma 0.108, Re 1106Angle of attack of incoming flow 9 °;
FIG. 7 is a geometric profile of an airfoil of the present invention at different contraction scaling factors;
FIG. 8 is a comparison of drag characteristics of airfoils of the present invention at different contraction scaling factors;
FIG. 9 is a comparison of lift characteristics of airfoils of the present invention at different contraction scaling factors;
FIG. 10 is a geometric profile of an airfoil of the present invention at different fixed turning angles;
FIG. 11 is a comparison of drag characteristics for airfoils of the present invention at different rotation angles;
FIG. 12 is a comparison of lift characteristics of airfoils of the present invention at different angles of rotation.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and examples, wherein the examples are theoretical calculation analysis of the present invention. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The invention discloses a high-lift wind turbine airfoil profile, which is shown by combining with figures 1 to 3, the structure of the high-lift wind turbine airfoil profile takes the curve profile of an S809 airfoil profile as a prototype, and the structure of the high-lift wind turbine airfoil profile is described by the forming process as follows:
respectively carrying out front projection on the S809 airfoil profile and the NACA4412 airfoil profile in the same X-Y coordinate system to respectively obtain an S809 airfoil profile and an NACA4412 airfoil profile, and coinciding the S809 airfoil profile with the trailing edge point O of the NACA4412 airfoil profile;
reducing the whole NACA4412 airfoil profile by a scaling factor alpha, and rotating the reduced NACA4412 airfoil profile by an angle beta around the trailing edge point O so that the upper chord of the NACA4412 airfoil profile and the S809 airfoil profile intersects at a point A (x, y);
when the value of y, the ordinate in point A is less than the maximum ordinate value of the NACA4412 airfoil profile, the face between the NACA4412 airfoils O-A is substituted for the face between the S809 airfoils O-A.
In the embodiment of the invention, the main design indexes of the high-lift wind turbine airfoil are as follows: (1) the Reynolds number is designed to be in the order of 100 ten thousand, and the Mach number is designed to be 0.1; (2) the air flow separation inhibiting characteristic is good; (3) the surface pressure characteristic is good; (4) the lift-drag characteristic is good; (5) the stall characteristic is relaxed. According to the indexes, the value range of the scale factor alpha can be set to be 0.2-0.5.
In the practical application process of the invention, the outer surface of the high-lift wind turbine airfoil consists of S1-S5 sections which are sequentially connected end to end, the S1-S3 sections form the upper surface of the airfoil, and the S4-S5 sections form the lower surface of the airfoil; the section S1 is butted with the section S5 at a front edge point, the section S3 is butted with the section S4 at a rear edge point O, and the section S3 is a surface between the NACA4412 airfoils O-A; wherein the sections S1 and S5 are leading edge contraction sections of the airfoil; the S2 section is a smooth transition section of the upper surface of the airfoil; the section S3 is an airfoil upper surface trailing edge section; the section S4 is an airfoil lower surface trailing edge section; the S3 segment is changed according to the scale factor, and the S1 segment, the S2 segment, the S4 segment and the S5 segment are changed along with the change of the S3 segment on the premise that the S1 segment, the S2 segment, the S4 segment and the S5 segment are consistent with the curve profile of the S809 airfoil.
More specifically, as a preferred embodiment, the invention provides a high-lift wind turbine airfoil, wherein the camber line is S-shaped, the front section of the camber line is concave, the rear section of the camber line is convex, and the intersection point of the camber line and the chord line of the airfoil is located at 0.46 unit; the maximum thickness of the airfoil is 0.199 units, the chord-wise position corresponding to the maximum thickness is 0.349 units away from the front edge point, and the included angle of the rear edge is 13.36 degrees; the length of the S1 section is greater than 0.0 unit and less than 0.39 unit; the length of the S2 section is greater than 0.39 units and less than 0.85 units; the length of the S3 section is greater than 0.85 unit and less than 1.0 unit; the length of the S4 section is greater than 0.32 unit and less than 1.0 unit; the length of S5 is greater than 0.0 units and less than 0.32 units; wherein 1 said unit is equal to the chord length of said airfoil.
In order to embody the airfoil profile characteristics of the high-lift wind turbine provided by the invention, the following experimental examples are compared, so that the advantages of the airfoil profile of the high-lift wind turbine are verified. It adopts wing type pneumaticsThe analysis software (solving the RANS equation) performs pneumatic performance analysis, and the calculation state parameters are as follows: angle of attack of incoming flow: 9 deg., Mach number 0.108, Reynolds number 1X 106。
1. Authentication
The difference of aerodynamic performance of the wing profile of the invention and the comparison wing profile is analyzed and compared by taking the classic windmill wing profile S809 as the comparison wing profile 1 and comparing with the wing profile of the invention.
FIG. 3 is a comparison of the geometrical profiles of an airfoil of the invention (design with a contraction scaling factor α of 0.3 and a rotation angle β of 9 °) with a comparison airfoil 1; FIG. 4 is a comparison of the turbulence viscosity of the inventive airfoil and the comparative airfoil 1; FIG. 5 is a comparison of the surface pressure characteristics of the airfoil of the present invention and the comparative airfoil 1; fig. 6 is a comparison of the lift-drag ratio characteristics of the airfoil of the present invention and the comparative airfoil 1.
It can be seen from fig. 4 that the maximum turbulence viscosity of the comparative airfoil 1 is greater than 1000, whereas the maximum turbulence viscosity of the inventive airfoil is only about 700, which is significantly reduced. The airfoil of the invention reduces the turbulence viscosity, so that the drag coefficient is also reduced.
As can be seen from fig. 5, the airfoil of the present invention can change the velocity profile of the upper surface of the airfoil. The inventive airfoil leading and mid-section Cp are substantially smaller than the comparative airfoil 1 and the peak is smaller than the comparative airfoil 1. However, the Cp of the airfoil of the invention close to the trailing edge is greater than that of the comparative airfoil 1, due to the greater camber than that of the comparative airfoil 1. While this characteristic predicts that at smaller incoming flow angles of attack the trailing edge separation of the inventive airfoil will be increased compared to the comparative airfoil 1, it also means that the drag coefficient will also be increased. But the larger sweep range is limited to between 0.82-1.0c, which has less impact on flow separation at high incoming flow angles due to the separation point moving to the airfoil leading edge.
It can be seen from fig. 6 that the inventive airfoil has a much wider low drag range than the comparative airfoil 1, while the maximum lift coefficient is much higher than the S809 airfoil. Although the minimum drag coefficient of the airfoil of the present invention is higher than that of the comparative airfoil 1, the airfoil is more suitable for horizontal axis wind turbines, especially under the condition of small tip speed ratio. Because the change of the wind speed brings the change of the attack angle, the airfoil profile is also suitable for the vertical axis wind turbine working under the unsteady wind conditions of gust, turbulence and the like.
After the verification of the representative experimental examples, the airfoil profile provided by the invention can reduce the maximum turbulent viscosity and the resistance coefficient under the condition of a Reynolds number of 100 ten thousand levels, has a wider low resistance range, and simultaneously increases the maximum lift coefficient and the stall attack angle, thereby improving the wind energy absorption efficiency of the wind wheel of the wind turbine generator set.
In the airfoil profile, the contraction scale factor alpha and the rotation angle beta are key indexes of design, and the influence of the contraction scale factor alpha and the rotation angle beta on the aerodynamic characteristics of the airfoil profile is reflected. The airfoil of the invention with different shrinkage scale factors alpha and rotation angles beta is respectively subjected to aerodynamic performance analysis by airfoil aerodynamic analysis software (solving RANS equation), and the calculation state parameters are as follows: angle of attack of incoming flow: 9 deg., Mach number 0.108, Reynolds number 1X 106。
2. Comparative example 1
Different design schemes of the airfoil profile of the invention with the same rotation angle (beta is 10 degrees) and different shrinkage scale factors (alpha is 0.2, 0.3, 0.4 and 0.5) are compared, and the influence of the shrinkage scale factors on the design of the airfoil profile of the invention is analyzed and compared.
FIG. 7 is a geometric profile of an airfoil of the present invention at different contraction scaling factors; FIG. 8 is a comparison of drag characteristics of airfoils of the present invention at different contraction scaling factors; fig. 9 is a comparison of the lift characteristics of the airfoil of the invention for different contraction scaling factors.
Table 1 shows the maximum lift comparison and lift increment table between the airfoil profile of the present invention with different contraction ratio shadows and S809:
TABLE 1 maximum lift contrast and lift increment table
| S809 | F-0.2-10 | F-0.3-10 | F-0.4-10 | F-0.5-10 | |
| Clmax | 0.996 | 1.085 | 1.157 | 1.174 | 1.101 |
| Increment of | 0.00％ | 8.94％ | 16.16％ | 17.87％ | 10.54％ |
As can be seen from FIGS. 7-9 and Table 1, the range of influence of the NACA4412 airfoil increases with increasing contraction scale factor and the slope of the lift coefficient decreases with increasing contraction scale factor. At the same time, stall angle of attack is delayed as the contraction scaling factor α increases. The maximum lift Cl of the airfoil according to the invention is not less than 0.5, except for the case of a contraction scaling factor alphamaxBut also increases as its coefficient increases. The drag coefficient is less affected by the contraction scaling factor α, but it is generally apparent that the inventive airfoil has a lower drag coefficient at stall and a larger low drag range than the comparative airfoil 1.
3. Comparative example 2
Different design schemes of the airfoil profile of the invention with the same contraction scale factor (alpha is 0.3) and different rotation angles (beta is 8 degrees, 9 degrees, 10 degrees and 11 degrees) are compared, and the influence of the rotation angles on the design of the airfoil profile of the invention is analyzed and compared.
FIG. 10 is a geometric profile of an airfoil of the present invention at different contraction scaling factors; FIG. 11 is a comparison of drag characteristics for airfoils of the present invention at different contraction scaling factors; FIG. 12 is a comparison of lift characteristics of airfoils of the present invention at different contraction scaling factors.
As can be seen from FIGS. 10-12, as the rotation angle increases, the camber of the upper surface of the airfoil of the present invention near the trailing edge also increases. The lift stall angle of attack is retarded as the angle of rotation increases. Under the condition of high attack angle, the airfoil profile with large rotation angle can limit the separation of the trailing edge, so that the resistance can be obviously reduced.
Through the comparison, the influence of the contraction scale factor and the rotation angle of the airfoil profile on the aerodynamic characteristics of the airfoil profile is obtained. It is believed that the larger the contraction scaling factor α in the airfoil design of the present invention, the higher the lift stall angle of attack. And the change of the aerodynamic load is the same as the contraction scale factor alpha with the increase of the rotation angle beta.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (4)
1. A high-lift wind turbine airfoil profile, characterized in that the profile of the S809 airfoil profile is used as a prototype, the structure of the high-lift wind turbine airfoil profile is described as follows:
respectively carrying out front projection on the S809 airfoil profile and the NACA4412 airfoil profile in the same X-Y coordinate system to respectively obtain an S809 airfoil profile and an NACA4412 airfoil profile, and coinciding the S809 airfoil profile with the trailing edge point O of the NACA4412 airfoil profile;
reducing the whole NACA4412 airfoil profile by a scaling factor alpha, and rotating the reduced NACA4412 airfoil profile by an angle beta around the trailing edge point O so that the upper chord of the NACA4412 airfoil profile and the S809 airfoil profile intersects at a point A (x, y);
when the value of y, the ordinate in point A is less than the maximum ordinate value of the NACA4412 airfoil profile, the face between the NACA4412 airfoils O-A is substituted for the face between the S809 airfoils O-A.
2. The high-lift wind turbine airfoil of claim 1, characterized in that the value of the scaling factor α is in the range of 0.2 to 0.5.
3. The high-lift wind turbine airfoil as claimed in claim 2, wherein the outer surface of said airfoil consists of sections S1-S5 connected end to end, sections S1-S3 forming the upper surface of the airfoil, and sections S4-S5 forming the lower surface of the airfoil; the section S1 is butted with the section S5 at a front edge point, the section S3 is butted with the section S4 at a rear edge point O, and the section S3 is a surface between the NACA4412 airfoils O-A; wherein,
the sections S1 and S5 are leading edge contraction sections of the airfoil; the S2 section is a smooth transition section of the upper surface of the airfoil; the section S3 is an airfoil upper surface trailing edge section; the section S4 is an airfoil lower surface trailing edge section;
the S3 segment is changed according to the scale factor, and the S1 segment, the S2 segment, the S4 segment and the S5 segment are changed along with the change of the S3 segment on the premise that the S1 segment, the S2 segment, the S4 segment and the S5 segment are consistent with the curve profile of the S809 airfoil.
4. The high-lift airfoil of claim 3, wherein the mean camber line of said airfoil is S-shaped, with the forward section of the mean camber line being concave and the aft section being convex, and the intersection of the mean camber line and the chord line of the airfoil being at 0.46 units;
the maximum thickness of the airfoil is 0.199 units, the chord-wise position corresponding to the maximum thickness is 0.349 units away from the front edge point, and the included angle of the rear edge is 13.36 degrees;
the length of the S1 section is greater than 0.0 unit and less than 0.39 unit; the length of the S2 section is greater than 0.39 units and less than 0.85 units; the length of the S3 section is greater than 0.85 unit and less than 1.0 unit; the length of the S4 section is greater than 0.32 unit and less than 1.0 unit; the length of S5 is greater than 0.0 units and less than 0.32 units;
wherein 1 said unit is equal to the chord length of said airfoil.
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