CN111400834A - Aerodynamic optimization design method, model and device for wind generating set blade airfoil - Google Patents
Aerodynamic optimization design method, model and device for wind generating set blade airfoil Download PDFInfo
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Abstract
The invention discloses a method, a model and a device for aerodynamic optimization design of a wind generating set blade airfoil, wherein the method carries out parametric design on the airfoil by combining design parameters of the airfoil and a free Bezier curve, and comprises the following steps: s1, determining the leading edge and the trailing edge of the airfoil profile; s2, constructing a pressure surface molded line and a suction surface molded line by a Bezier curve modeling method; s3, combining the front edge and the tail edge with the pressure surface molded line and the suction surface molded line to form a complete airfoil shape; and S4, performing pneumatic optimization design based on the airfoil modeling. The invention adopts the free Bezier curve to model the airfoil of the wind generating set, realizes the parameterization of the geometric shape of the airfoil of the wind generating set and the automatic optimization design of the airfoil of the wind generating set, has good universality and high optimization efficiency, and further perfects the pneumatic design system of the airfoil.
Description
Technical Field
The invention relates to the field of wind driven generator blade design, in particular to a wind driven generator blade airfoil aerodynamic optimization design method, a wind driven generator blade airfoil aerodynamic optimization design model and a wind driven generator blade airfoil aerodynamic optimization design device.
Background
The aerodynamic performance of the wing profile of the wind generating set directly determines the wind energy conversion efficiency of the blade. The low-speed wind generating set blade adopts a thin and slightly concave wing shape; the blades of the modern high-speed wind generating set adopt streamline blades, the airfoil profile of the blades is usually selected from NACA and Gottigen series, and the airfoil profiles are characterized by small resistance, high aerodynamic efficiency and enough Reynolds number.
Early horizontal-axis wind turbine generator blades generally used aerofoils, such as the NACA44 and NACA230 series of foils, because of their high maximum lift coefficient, low pitch momentum, and low minimum drag coefficient. However, the wing profile of the wind generating set has different design requirements from the common aviation wing profile, which mainly appear in the following aspects: (1) the thickness of the common aviation wing profile is low, and the wing profile of the wind generating set needs to have larger maximum thickness in order to meet the strength requirement; (2) aeronautical airfoils mainly require a moderate stall characteristic near a stall angle, while aeronautical airfoil profiles require a moderate lift coefficient at all angles of attack after stall; (3) the aviation airfoil profile is generally calculated according to a smooth surface, and the airfoil profile of the wind generating set is possibly subjected to surface icing or surface roughness change caused by damage to the airfoil profile surface by impurities in the air due to the severe working environment, so that the airfoil profile of the wind generating set is required to have low roughness sensitivity; (4) airplanes generally require the high lift-to-drag ratio of airfoils at cruise mach numbers and cruise lift, while wind generating sets require airfoils having high lift-to-drag ratios in all speed ranges from small to large wind speeds up to the maximum lift coefficient; (5) aeronautical airfoils require the airfoil to have as high a maximum lift as possible while meeting cruise design requirements, which for stall controlled wind turbine generators require limiting the maximum lift of the airfoil.
For this reason, advanced wind energy technology countries such as the United states, Sweden, the Netherlands and Denmark develop respective airfoil series, of which S series airfoils of the national laboratory of renewable energy (NRE L) and FFA-W series airfoils of Rui 4 Scenario are most representative.
In 1984, under the subsidy of the U.S. department of energy, the U.S. renewable energy laboratory developed the research on the airfoil families of wind generating sets, and in the 90 s, different performances have been developed for various wind generating sets, from the root to the tip, and a plurality of airfoil families capable of meeting the structural requirements are classified according to the size and the load control type of the wind generating sets. The application effect shows that the new wing section greatly increases the energy output of the wind driven generator, and the annual energy production increase range of different types of wind driven generator sets is 10-35%.
The Danish RIS phi national laboratory develops three airfoil families of RIS phi-A1, RIS phi-B1 and RIS phi-P in the later 90 s by using a computational fluid mechanics method, and the RIS phi-A1 series of airfoils are mainly suitable for passive stall control wind generating sets and active control wind generating sets, but have higher sensitivity to roughness than expected; the RIS phi-B1 series airfoil is used for a MW-level wind generating set controlled by a variable speed and a variable torque, has the relative thickness of 15-53 percent and high maximum lift coefficient, thereby enabling a slimmer blade to keep high aerodynamic efficiency; the RIS phi-P series airfoil is used for torque conversion control of a wind generating set and reduces the sensitivity to roughness.
Under the subsidies of European Union JOU L E plan, Netherlands energy and environmental bureau and the like, the university of Delft in the Netherlands develops a DU wind generating set airfoil family, and forms a DU airfoil family with the relative thickness of 15-40 percent, and the design principle of the airfoil is that an outer ring airfoil has the properties of high lift-drag ratio, high maximum lift coefficient, moderate stall characteristic, insensitivity to roughness, low noise and the like.
The swedish research institute designed FFA-W3 series of airfoils in the 90 s, which included various airfoils of various thicknesses of 19% to 60%. The FFA-W series airfoil has the advantages of higher lift coefficient and lift-drag ratio under the design working condition and good stall performance under the non-design working condition.
With the continuous increase of the single-machine capacity of the wind generating set and the development of new technology, technology and materials, the existing commercialized main-stream machine type has been changed from the original stalling wind generating set into the variable-pitch wind generating set. In order to meet the requirements of the variable pitch rectangular wind generating set, the novel airfoil profile has the following characteristics: (1) the method is suitable for the development of thin wing profiles of different variable-pitch and variable-speed wind generating sets; (2) with the development of large-scale wind generating set, the performance and structure of the wind power blade root have higher requirements, and the maximum thickness of the root is expanded to more than 65%; (3) with the further research on the blunt trailing edge airfoil, the blunt trailing edge airfoil with medium thickness is emphasized with the development of the wind power blade; (4) with the further research of the unsteady aerodynamic performance of the wind turbine blade, the airfoil design technology with good dynamic stall characteristics is greatly developed.
Compared with other countries with developed wind energy technology, China is still quite laggard in developing special airfoils for wind generating sets. At present, the traditional aviation airfoil profile is still basically adopted for designing the wind generating set in China. In addition, some research units perform aerodynamic research on the basis of the wing profiles of the wind generating sets existing abroad, or perform improvement on the wing profiles. However, up to now, the wing profiles suitable for large-scale wind generating sets have not been independently developed in China.
Disclosure of Invention
The invention aims to provide a method for the aerodynamic optimization design of the blade airfoil of the wind generating set, which can automatically optimize the design, has strong universality and high optimization efficiency.
In order to solve the technical problems, the invention adopts the following technical scheme:
a method for aerodynamic optimization design of a wind generating set blade airfoil is characterized in that the airfoil is subjected to parametric design through combination of design parameters of the airfoil and a free Bezier curve, and comprises the following steps:
s1, determining the leading edge and the trailing edge of the airfoil profile:
determining the coordinates of the leading edge point and the trailing edge point of the airfoil according to the chord length Cx and the tangential chord length Ct of the airfoil, and combining the leading edge radius R1Trailing edge radius R2Determining the leading edge and the trailing edge of the airfoil;
s2, constructing a pressure surface molded line and a suction surface molded line by a Bezier curve modeling method:
with the semi-sharp angle omega of the airfoil leading edge and the leading edge1Is taken as the starting point of the Bezier curve and is defined by the leading edge geometric angle β1And front edge semi-sharp angle omega1By tan (β)1+ω1Y '(0), determining the slope y' (0) of the first edge P2P3 of the characteristic polygon of the Bezier curve; with a semi-sharp angle omega between the trailing edge and the trailing edge2Is taken as the end point of the Bezier curve and is defined by the trailing edge geometric angle β2And trailing edge semi-sharp angle omega2By tan (β)2+ω2Y '(1), determining the slope y' (1) of the second side P1P3 of the characteristic polygon of the Bezier curve; the first side and the second side are intersected at a vector point P3, and a characteristic polygon of a quadratic Bezier curve is formed by vector points P1, P2 and P3; further forming a high-order Bezier curve on the basis of the secondary Bezier curve; respectively constructing a pressure surface molded line and a suction surface molded line according to the Bezier curve modeling method;
s3, combining the front edge and the tail edge with the pressure surface molded line and the suction surface molded line to form a complete airfoil shape;
and S4, performing pneumatic optimization design based on the airfoil modeling.
As a further improvement of the present invention, in S2, the further forming a high-order Bezier curve on the basis of the quadratic Bezier curve includes: determining a vector point P4 between vector points P1 and P3 according to a certain proportion t (t is less than or equal to 1), similarly determining a vector point P5 between P2 and P3, and determining a cubic Bezier curve by a feature polygon consisting of four vector points P1, P2, P4 and P5; a point P6 is selected between P4 and P5, and a Bezier curve determined by a characteristic polygon P1P4P6P5P2 changes the profile line by adjusting the five control points.
Further, in the pneumatic optimization design in S4, the optimization method includes: selecting profile line of airfoil pressure surface,Coordinates of 5 control points [ cx (xi, yi) on the suction surface profile line respectively]Selecting airfoil maximum lift-drag ratio [ Cl/Cd ] for optimizing variables]For optimization purposes, the maximum thickness C of the airfoil profile is measuredmaxAnd (5) making constraint, namely the airfoil profile meets the set chord-thickness ratio, and selecting a gradient optimization algorithm as an optimization method.
Further, in the aerodynamic optimization design in S4, CFD simulation software is used to establish an aerodynamic model, a C-type structured grid is integrally selected for calculation, and a boundary layer grid is added to the airfoil surface during calculation, and encryption processing is performed.
Further, in the pneumatic model, a finite volume method is adopted to solve a Reynolds average Navier-Stokes equation set in a two-dimensional compressible integral form, in a control equation, a Roe windward discrete format with second-order precision is adopted to disperse flow terms, a central differential format with second-order precision is adopted to disperse viscous flow terms, and implicit L U-SGS is adopted to perform time dispersion.
Further, in the pneumatic model, the turbulence model selects a k-omega two-equation turbulence model to perform numerical simulation calculation, a Wilcox k-omega model is adopted in a near-wall area, and k-omega models are adopted in a boundary layer edge and a free shear layer to calculate, and a mixing function is used for transition between the k-omega model and the k-omega model, wherein the k-omega model belongs to a two-equation vortex viscosity mode of incompressible/compressible turbulence integrated to the wall.
Further, the airfoil chord length Cx and the tangential chord length Ct in the S1 are calculated according to a momentum phylloton theory; the design parameters of the airfoil include in addition to: airfoil chord length Cx, tangential chord length Ct, leading edge radius R1Trailing edge radius R2Front edge semi-sharp angle omega1Semi-closed angle omega of trailing edge2Leading edge geometry angle β1Trailing edge geometry angle β2(ii) a Further comprising: maximum thickness Cmax(ii) a The mounting angle lambda.
Further, the wind generating set is a low wind speed wind generating set.
On the other hand, the invention also discloses a wind generating set blade airfoil aerodynamic optimization design model which is established by adopting the wind generating set blade airfoil aerodynamic optimization design method.
On the other hand, the invention also discloses a wind generating set blade airfoil aerodynamic optimization design device, which is characterized in that: one or more processors; and the storage device is used for storing one or more programs, and when the one or more programs are executed by the one or more processors, the one or more processors realize the aerodynamic optimization design method of the airfoil of the wind generating set blade.
By adopting the technical scheme, the invention at least has the following advantages:
1. the invention adopts the free Bezier curve to model the airfoil of the wind generating set, realizes the parameterization of the geometric shape of the airfoil of the wind generating set and the automatic optimization design of the airfoil of the wind generating set, has good universality and high optimization efficiency, and further perfects the pneumatic design system of the airfoil.
2. The invention changes the dependence of the traditional method on the design experience, shortens the design period, reduces the workload and improves the working efficiency.
Drawings
The foregoing is only an overview of the technical solutions of the present invention, and in order to make the technical solutions of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and the detailed description.
FIG. 1 is an airfoil design parameter map;
FIG. 2 is a flow chart of a method for aerodynamic optimization design of a wind turbine generator system blade airfoil profile according to an embodiment of the invention;
FIG. 3 is a schematic view of a Bezier curve modeling method;
FIG. 4 is an airfoil Bezier curve profile;
FIG. 5 is an airfoil overall C-shaped structured grid diagram;
FIG. 6 is a diagram of an airfoil surface boundary layer meshing process;
FIG. 7 is a diagram of boundary layer mesh divisions at the airfoil trailing edge and trail;
FIG. 8 is a comparison before and after optimization of airfoil geometry.
Detailed Description
The invention provides a pneumatic optimization design method for a wind generating set blade airfoil, which has the overall design concept that the airfoil is subjected to parametric design by combining the design parameters of the airfoil and a free Bezier curve, and the airfoil of the wind generating set is modeled by adopting the free Bezier curve, so that the parameterization of the geometric shape of the airfoil of the wind generating set and the automatic optimization design of the airfoil of the wind generating set are realized.
The design parameters of the airfoil, as shown in fig. 1, include: airfoil chord length (axial chord length) Cx; a tangential chord length Ct; radius of leading edge R1(ii) a Radius of trailing edge R2(ii) a Front edge semi-closed angle omega1Determining the sensitivity degree to incoming flow, namely the variable working condition performance; trailing edge semi-sharp angle omega2Influencing the wake, leading edge geometry angle (geometric entrance angle) β1Associated with inlet flow angle, trailing edge geometry angle (geometric exit angle) β2Associated with the outlet flow angle; further comprising: maximum thickness CmaxRelated to the strength of the leaf profile; the mounting angle lambda.
Wherein, the free Bezier curve is set as Bj,k(t) (j ═ 0,1,2, ….. K) is a set of K Bernstein basis functions, with the control vertex pj(j ═ 0,1,2, ….. K), the corresponding K Bezier curves are defined as:
in the formula:
the Bezier curve obtained by the definition has geometric invariance and variation reduction. Geometric invariance means that the position and the shape of a Bezier curve are only related to the position of the vertex of a characteristic polygon of the Bezier curve, and the Bezier curve does not depend on the selection of a coordinate system; the variation reducibility means that the number of the intersection points of any straight line and p (t) in a plane is not more than the number of the intersection points of the straight line and the characteristic polygon of the straight line, and the property reflects that a Bezier curve is smoother than a broken line where the characteristic polygon is located.
Based on the above airfoil design parameters and free Bezier curves, the airfoil is parameterized, as shown in fig. 2, the aerodynamic optimization design method for the airfoil of the wind turbine generator set blade in this embodiment includes:
s1, determining the leading edge and the trailing edge of the airfoil profile:
determining the coordinates of the leading edge point and the trailing edge point of the airfoil profile according to the airfoil chord length Cx and the tangential chord length Ct which are obtained by momentum phylloton theory calculation and combining the radius R of the leading edge1Trailing edge radius R2Determining the leading edge and the trailing edge of the airfoil; the design of the front edge and the tail edge can adopt a circular design, an oval design and the like.
S2, constructing a pressure surface molded line and a suction surface molded line by a Bezier curve modeling method:
through type
When t is 0, P' (0) is n (P)1-P0) (ii) a When t is 1, P' (1) is n (P)n-Pn-1) And the tangent directions of the starting point and the end point of the Bezier curve are consistent with the trends of the first edge and the last edge of the characteristic polygon. Therefore, referring to FIG. 3, the present embodiment uses the airfoil leading edge and the leading edge semi-sharp angle ω1Is taken as the starting point of the Bezier curve and is defined by the leading edge geometric angle β1And front edge semi-sharp angle omega1By tan (β)1+ω1Y '(0), determining the slope y' (0) of the first edge P2P3 of the characteristic polygon of the Bezier curve; with a semi-sharp angle omega between the trailing edge and the trailing edge2Is taken as the end point of the Bezier curve and is defined by the trailing edge geometric angle β2And trailing edge semi-sharp angle omega2By tan (β)2+ω2Y '(1), determining the slope y' (1) of the second side P1P3 of the characteristic polygon of the Bezier curve; the first side and the second side are intersected at a vector point P3, and a characteristic polygon of a quadratic Bezier curve is formed by vector points P1, P2 and P3; this curve is uniquely defined and not adjustable.
In order to obtain a high-order Bezier curve with larger degree of freedom, a vector point P4 is determined between vector points P1 and P3 according to a certain proportion t (t is less than or equal to 1), similarly, a vector point P5 is determined between P2 and P3, and a feature polygon consisting of four vector points P1, P2, P4 and P5 determines a cubic Bezier curve. On the curve, the control points P4 and P5 can only move on the straight lines P1P3 and P2P3, which limits the adjustable space of the Bezier curve.
To solve this problem, a point P6 is selected between P4 and P5, so that the Bezier curve defined by the characteristic polygon P1P4P6P5P2 has a high degree of freedom, and the profile of the pressure surface can be largely changed by adjusting the five control points, and similarly, the profile of the pressure surface is constructed by the above method. The complete airfoil profile and the control points are distributed as shown in fig. 4, and the suction surface/pressure surface can be freely adjusted through 5 control points respectively, so that a good foundation is laid for next pneumatic optimization work. And respectively constructing a pressure surface molded line and a suction surface molded line according to the Bezier curve modeling method.
S3, combining the front edge and the tail edge with the pressure surface molded line and the suction surface molded line to form a complete airfoil shape;
and S4, performing pneumatic optimization design based on the airfoil modeling.
(1) Meshing techniques
And adopting CFD simulation software, carrying out grid division on the computational grid in the preprocessing software, and integrally selecting the C-shaped structured grid for calculation. The meshing case is shown in fig. 5:
in order to better capture the flow condition of the boundary layer on the surface of the airfoil and eliminate the influence caused by grids, boundary layer grids (boundary layer grids) are added on the surface of the airfoil during calculation, and encryption processing is adopted. The division of the surface boundary layer meshes is shown in fig. 6 and 7.
In the control equation, a two-order accuracy Roe windward discrete format is adopted to disperse flow terms, a two-order accuracy central differential format is adopted to disperse viscosity flow terms, and implicit L U-SGS (lower-upper symmetry gas-phase) is adopted to disperse time.
The turbulence model selects a k-omega (with SST wall function) two-equation turbulence model to carry out numerical simulation calculation, a Wilcox k-omega model is adopted in a near-wall region, k-omega models are adopted in a boundary layer edge and a free shear layer to calculate, and a mixing function is used for transition between the k-omega model and the k-omega model, so that the k-omega model belongs to a two-equation vortex viscosity mode of incompressible/compressible turbulence integrated to the wall.
(2) Optimization method
The aerodynamic optimization design of the fan airfoil is carried out on the basis of the NACA4418 airfoil, and the coordinates [ cx (x) of each 5 control points of airfoil pressure surface/suction surface molded lines are selectedi,yi)]Selecting airfoil maximum lift-drag ratio [ Cl/Cd ] for optimizing variables]For optimization purposes, the maximum thickness C of the airfoil profile is measuredmaxAnd (5) performing constraint, namely the airfoil profile meets the set chord-thickness ratio to implement optimization design, and adopting a gradient optimization algorithm.
A comparison of airfoil geometry before and after optimization is shown in FIG. 8.
And (4) optimizing the result:
| parameter(s) | Physical significance | Before optimization | After optimization | Optimization rate% |
| Cl/cd | Lift to drag ratio | 85.71 | 89.91 | 4.9 |
From the optimization target change table, the optimization rate can be intuitively seen to be as high as 4.9%, and the optimization target is achieved.
The blade airfoil pneumatic optimization design method of the wind generating set can be suitable for blade airfoil pneumatic design of any machine type, and is particularly suitable for low-wind-speed wind generating sets.
The embodiment also provides a wind generating set blade airfoil aerodynamic optimization design device, which comprises one or more processors; and the storage device is used for storing one or more programs, and when the one or more programs are executed by the one or more processors, the one or more processors realize the aerodynamic optimization design method of the airfoil of the wind generating set blade.
In conclusion, the free Bezier curve is adopted to model the airfoil profile of the wind generating set, so that the parameterization of the geometric shape of the airfoil profile of the wind generating set and the automatic optimization design of the airfoil profile of the wind generating set are realized, and the aerodynamic design system of the airfoil profile is further perfected. The curvature of the Bezier curve is continuous, the requirement of the design of the airfoil of the blade of the wind generating set is met, the fairing of the whole curve can be ensured, and the Bezier curve is connected with the front edge and the rear edge of the airfoil for transition fairing. The invention changes the dependence of the traditional method on the design experience, shortens the design period, reduces the workload and improves the working efficiency.
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 present invention in any way, and it will be apparent to those skilled in the art that the above description of the present invention can be applied to various modifications, equivalent variations or modifications without departing from the spirit and scope of the present invention.
Claims (10)
1. The aerodynamic optimization design method for the airfoil profile of the wind generating set blade is characterized in that the airfoil profile is subjected to parametric design through combination of design parameters of the airfoil profile and a free Bezier curve, and the method comprises the following steps:
s1, determining the leading edge and the trailing edge of the airfoil profile:
determining the coordinates of the most leading edge point and the most trailing edge point of the airfoil profile according to the chord length Cx and the tangential chord length Ct of the airfoil profile, and combining the coordinatesEdge radius R1Trailing edge radius R2Determining the leading edge and the trailing edge of the airfoil;
s2, constructing a pressure surface molded line and a suction surface molded line by a Bezier curve modeling method:
with the semi-sharp angle omega of the airfoil leading edge and the leading edge1Is taken as the starting point of the Bezier curve and is defined by the leading edge geometric angle β1And front edge semi-sharp angle omega1By tan (β)1+ω1Y '(0), determining the slope y' (0) of the first edge P2P3 of the characteristic polygon of the Bezier curve; with a semi-sharp angle omega between the trailing edge and the trailing edge2Is taken as the end point of the Bezier curve and is defined by the trailing edge geometric angle β2And trailing edge semi-sharp angle omega2By tan (β)2+ω2Y '(1), determining the slope y' (1) of the second side P1P3 of the characteristic polygon of the Bezier curve; the first side and the second side are intersected at a vector point P3, and a characteristic polygon of a quadratic Bezier curve is formed by vector points P1, P2 and P3; further forming a high-order Bezier curve on the basis of the secondary Bezier curve; respectively constructing a pressure surface molded line and a suction surface molded line according to the Bezier curve modeling method;
s3, combining the front edge and the tail edge with the pressure surface molded line and the suction surface molded line to form a complete airfoil shape;
and S4, performing pneumatic optimization design based on the airfoil modeling.
2. The aerodynamic airfoil profile optimization design method of a wind turbine generator system blade as claimed in claim 1, wherein in the step S2, further forming a high-order Bezier curve based on the quadratic Bezier curve comprises:
determining a vector point P4 between vector points P1 and P3 according to a certain proportion t (t is less than or equal to 1), similarly determining a vector point P5 between P2 and P3, and determining a cubic Bezier curve by a feature polygon consisting of four vector points P1, P2, P4 and P5; a point P6 is selected between P4 and P5, and the Bezier curve determined by the characteristic polygon P1P4P6P5P2 changes the profile line by adjusting the five control points.
3. The aerodynamic optimization design method of the wind generating set blade airfoil profile according to claim 1 or 2, wherein the aerodynamic optimization design in the S4 comprises the following steps:
selecting at least 5 control point coordinates [ cx (xi, yi) on airfoil profile pressure surface line and suction surface line respectively]Selecting airfoil maximum lift-drag ratio [ Cl/Cd ] for optimizing variables]For optimization purposes, the maximum thickness C of the airfoil profile is measuredmaxAnd (5) making constraint, namely the airfoil profile meets the set chord-thickness ratio, and selecting a gradient optimization algorithm as an optimization method.
4. The aerodynamic optimization design method of the wind generating set blade airfoil profile according to claim 1 or 2, wherein in the aerodynamic optimization design in S4, CFD simulation software is adopted to establish an aerodynamic model, a C-shaped structured grid is selected as a whole for calculation, and a boundary layer grid is added on the airfoil profile surface during calculation, and encryption processing is adopted.
5. The aerodynamic optimization design method of the blade airfoil profile of the wind generating set according to claim 4, wherein in the aerodynamic model, a finite volume method is adopted to solve a Reynolds average Navier-Stokes equation set in a two-dimensional compressible integral form, in the control equation, a Roe windward discrete format with second-order precision is adopted to disperse flow terms, a central differential format with second-order precision is adopted to disperse viscous flow terms, and an implicit L U-SGS is adopted to perform time dispersion.
6. The aerodynamic optimization design method of the wind generating set blade airfoil profile according to claim 4, wherein in the aerodynamic model, a k-omega two-equation turbulence model is selected for the turbulence model to carry out numerical simulation calculation, a Wilcox k-omega model is adopted in a near-wall region, a k-omega model is adopted in a boundary layer edge and a free shear layer, and transition is carried out between the k-omega model and the k-omega model through a mixing function, and the k-omega model belongs to a two-equation vortex viscosity mode of the incompressible/compressible turbulence integrated to the wall surface.
7. The aerodynamic optimization design method of the wind generating set blade airfoil profile according to claim 1,the method is characterized in that the airfoil chord length Cx and the tangential chord length Ct in the S1 are obtained by calculation according to a momentum phylloton theory; the design parameters of the airfoil include in addition to: airfoil chord length Cx, tangential chord length Ct, leading edge radius R1Trailing edge radius R2Front edge semi-sharp angle omega1Semi-closed angle omega of trailing edge2Leading edge geometry angle β1Trailing edge geometry angle β2(ii) a Further comprising: maximum thickness Cmax(ii) a The mounting angle lambda.
8. The aerodynamic optimization design method of the wind generating set blade airfoil profile according to claim 1, wherein the wind generating set is a low wind speed wind generating set.
9. A wind generating set blade airfoil aerodynamic optimization design model is characterized by being established by the wind generating set blade airfoil aerodynamic optimization design method according to any one of claims 1 to 8.
10. The utility model provides a pneumatic optimal design device of wind generating set blade airfoil which characterized in that:
one or more processors;
a storage device for storing one or more programs,
when executed by the one or more processors, cause the one or more processors to implement the method of aerodynamic optimization of a wind turbine generator system blade airfoil according to any one of claims 1 to 8.
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| CN113297775A (en) * | 2021-06-09 | 2021-08-24 | 上海尚实能源科技有限公司 | Modeling method of impeller mechanical blade pneumatic model |
| CN114692344A (en) * | 2022-06-02 | 2022-07-01 | 广东海洋大学 | Wind driven generator optimization design method and system based on computer assistance |
| CN115841548A (en) * | 2023-02-21 | 2023-03-24 | 陕西空天信息技术有限公司 | Computer-aided generation method and system of blade model |
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| CN115841548A (en) * | 2023-02-21 | 2023-03-24 | 陕西空天信息技术有限公司 | Computer-aided generation method and system of blade model |
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