CN111859801B - Method for designing stall-controlled wind turbine airfoil - Google Patents
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Abstract
The invention relates to a method for designing a stall-type wind turbine airfoil profile, which aims at a horizontal axis wind turbine blade airfoil profile and provides an airfoil profile design method adopting an elliptical concave profile line on a local part of an airfoil suction surface, wherein the maximum lift-drag ratio before stall and the maximum lift-drag ratio after stall are taken as multi-objective functions, on the basis of DU97-W-300 airfoil profile, the local part of the airfoil suction surface adopts an elliptical function expression, and the multi-objective simulated annealing algorithm is utilized to carry out airfoil local profile optimization design to obtain a target airfoil profile. Compared with the traditional horizontal axis wind turbine blade airfoil, the novel airfoil has more excellent post stall aerodynamic performance, so that the blade can generate more wind energy in a stall state.
Description
Technical Field
The invention relates to the field of design of a large-thickness wing section of a horizontal axis wind turbine blade, in particular to a design method of a stall controlled wind turbine wing section.
Background
At present, the research on the large-thickness airfoil of the wind turbine blade focuses on researching the aerodynamic performance before stall, and few students research the improvement of the aerodynamic performance of the airfoil after stall. However, due to the large thickness of the horizontal axis wind turbine blades (e.g., maximum relative thickness 30%, 40%, etc.), the airfoil typically operates at stall conditions. Therefore, it is very important to improve the aerodynamic performance of the wind turbine blade under the stall condition. The general wind turbine airfoil is designed under the condition of a certain design attack angle, the airfoil aerodynamic performance before stall is better, but the airfoil aerodynamic performance after stall is more seriously reduced. In the prior art, a unique local expression method of airfoil suction surface profile is not adopted, so that the flow field distribution of the airfoil after stalling is changed. Accordingly, there is a need to improve the prior art airfoil suction surface profile to improve aerodynamic performance of a wind turbine blade after stall of a large thickness airfoil.
Disclosure of Invention
The invention aims to provide a method for designing a stall-type wind turbine airfoil profile, and the airfoil profile designed by the method can obviously improve the aerodynamic performance of the large-thickness airfoil profile of a wind turbine blade after stall.
The scheme adopted by the invention for solving the technical problems is as follows:
a method of designing a stall controlled wind turbine airfoil, comprising:
s1: on the basis of the original airfoil profile, the profile of an inward concave shape is generated on the local suction surface by using an elliptic function for characterization, and design variables and constraint conditions are determined;
s2: comprehensively considering the aerodynamic performance of the airfoil before and after stall, giving the design power angle and the design Reynolds number before and after stall, and establishing the maximum lift-drag ratio of the airfoil under the smooth condition as an objective function;
s3: and taking the objective function in the step S2 as an optimization target, filtering the profiles which do not meet the requirements through constraint conditions, and giving an optimization algorithm to carry out optimization calculation on the profiles which meet the requirements to obtain the target profile.
Further, the expression of the elliptic function in step S1 is:
in the above formula, the coefficient a is more than b and more than 0, x is the horizontal coordinate of the airfoil on the xoy plane, y is the vertical coordinate of the airfoil xoy plane, c and d are plane coordinate offset parameters, and theta is a transformation angle.
Further, in step S1, five parameters a, b, c, d and θ are used as design variables: x ═ (a, b, c, d, θ);
the constraint conditions are as follows:
the two coefficients of the airfoil local elliptic control function are constrained as follows:
Xmin≤X≤Xmax
the design variable constraint ranges are:
| a | b | c | d | θ/° | |
| maximum value | 0.0 | 0.0 | 0.0 | 0.0 | -30.0 |
| Minimum value | 1.0 | 1.0 | 1.0 | 1.0 | 0.0 |
。
Further, the expression of the objective function in step S2 is:
f(x)＝max(f1(x)，f2(x))
wherein f is1(x)＝CL/CD，f2(x)＝C’L/C’D；
In the formula, CLDesigning lift coefficient of attack angle at certain angle before stall, CDDesigning a resistance coefficient of an attack angle at a certain angle before stall; c'LDesigning a lift coefficient C 'of an attack angle at a certain angle for the design after stall'DAnd designing the resistance coefficient of the attack angle at a certain angle after the stall.
Further, in step S2, the designed angle of attack before stall is 6 °, the designed angle of attack after stall is 14 °, and the designed reynolds number Re is 3.0 × 106。
Further, step S3 further includes:
(a) initializing design variables, generating an airfoil profile which adopts an elliptic function to generate a concave shape, and filtering out a non-delayed stall airfoil profile through a constraint condition;
(b) calling in a delay stall airfoil profile meeting the requirement, and acquiring data point coordinate information on the delay stall airfoil profile;
(c) setting the aerodynamic performance parameters of the airfoil profile to be calculated, calculating and converging a series of delay stall airfoil families meeting the requirements, and outputting data point information of each airfoil profile and the corresponding aerodynamic performance parameters thereof
(d) Calculating a fitness value of the output airfoil family and the corresponding aerodynamic performance parameters thereof through an objective function;
(e) coupling the calculation modules in the four steps to a simulated annealing multi-objective evolutionary algorithm for optimization iteration, and outputting a target airfoil profile when an iteration condition is met; if the iteration condition is not met, the profile of the airfoil profile is adjusted in a self-adaptive mode, and the step (a) is executed in a rotating mode.
Further, the aerodynamic performance parameters in step (c) include a lift coefficient and a drag coefficient of the design angle of attack within a certain angle range.
Further, the parameters related to the simulated annealing algorithm are as follows: the population number was 30, the maximum number of iterations 200, the cooling rate 0.9, the initial temperature 1000, the end temperature 0.001, and the chain length 220.
Further, the original airfoil suction surface is formed with a semi-elliptical shape near 50% chord length to create a concave shape.
The invention further aims to provide a delayed stall-type wind turbine blade airfoil which is optimally designed according to the design method of the stall-type wind turbine large-thickness airfoil.
Compared with the prior art, the invention has at least the following beneficial effects: the method of the invention is directed at the horizontal axis wind turbine blade airfoil, and proposes an airfoil design method which locally adopts an elliptical concave profile on the suction surface of the airfoil, and takes the maximum lift-drag ratio before stall and the maximum lift-drag ratio after stall as a multi-objective function, on the basis of DU97-W-300 airfoil, the suction surface of the airfoil locally adopts the elliptical function to express, and utilizes the multi-objective simulated annealing algorithm to carry out the optimization design of the local profile of the airfoil, so that the designed new airfoil has obvious delayed stall characteristic, and the stall aerodynamic performance is obviously improved afterwards; the method can be popularized and applied to the wing profiles of the blades of the horizontal-axis wind driven generator, and the novel wing profiles are adopted to replace the wing profiles of the blades of the traditional horizontal-axis wind driven generator, so that the method has good social value and economic benefit.
Drawings
FIG. 1 is a flow chart of an airfoil optimization design according to an embodiment of the present invention;
FIG. 2 is a schematic view of a partial semi-elliptical shape of an airfoil suction surface in accordance with an embodiment of the present invention;
FIG. 3 is a schematic diagram of ICEM optimized delayed stall airfoil meshing in accordance with an embodiment of the present invention;
FIG. 4 is a schematic view of a delayed stall WT-E-300 new airfoil profile according to an embodiment of the present invention;
FIG. 5 shows an airfoil lift coefficient of WT-E-300 according to an embodiment of the present invention;
FIG. 6 shows an airfoil drag coefficient WT-E-300 according to an embodiment of the present invention
FIG. 7 shows an airfoil lift-drag ratio of WT-E-300 in accordance with an embodiment of the present invention.
Detailed Description
The following examples are provided to further illustrate the present invention for better understanding, but the present invention is not limited to the following examples.
In view of the fact that the general wind turbine airfoil profile in the prior art is designed under the condition of a certain design attack angle, the aerodynamic performance of the airfoil profile before stalling is good, but the aerodynamic performance of the airfoil profile after stalling is reduced more seriously, the invention provides the design method of the large-thickness airfoil profile of the stall type wind turbine, and the airfoil profile designed by the invention can obviously improve the aerodynamic performance of the large-thickness airfoil profile of the wind turbine blade after stalling.
The invention provides an optimized design method of an airfoil profile of a wind driven generator blade with the maximum airfoil lift-drag ratio of a multi-objective function under the design working condition and the stall working condition on the basis of an airfoil profile DU97-W-300 (the maximum relative thickness of the airfoil profile is 30%) special for a general wind turbine, adopts a simulated annealing multi-objective evolutionary algorithm to realize the control and parameter optimization of the local profile of the airfoil suction surface of the horizontal axis wind driven generator, couples airfoil fluid calculation software fluent into the algorithm program, and calculates the aerodynamic performance of the airfoil profile. Finally, aerodynamic performance comparison analysis is carried out on the WT-E-300 new airfoil which is designed in an optimized mode and a DU97-W-300 airfoil which is commonly used for wind turbine blades.
Specifically, the design flow of this embodiment is shown in fig. 1, and includes the following steps:
s1: on the basis of the original airfoil profile, a profile of an inward concave shape is generated on the suction surface by locally using an elliptic function for representation, and design variables and constraint conditions are determined;
referring to FIG. 2, on the basis of a general airfoil profile DU97-W-300 outline 1 of a wind turbine blade, the invention replaces the shape of the original outline with a half-ellipse 2 concave shape near the 50% chord length of the suction surface of the airfoil to obtain a new airfoil profile shape, and the partial profile ellipse expression (1) of the suction surface is shown as follows:
in the formula (1), a is more than b and more than 0; x is the horizontal coordinate of the wing profile on the xoy plane, and y is the vertical coordinate of the wing profile xoy plane; the airfoil shape shown in figure 2 can be obtained by selecting proper coefficients a and b and changing the angle theta through plane coordinate deviation c and d parameters and rotation, and the suction surface of the airfoil profile has the characteristic of a local elliptic concave shape, so that the stall aerodynamic performance of the airfoil after stall can be effectively improved.
Determining design variables
According to the idea of expression of the local semicircular elliptic function of the airfoil suction surface profile, the concave shape of the local profile of the airfoil suction surface of the blade can be obtained by controlling the coefficients of the elliptic functions a and b, and five parameters of the local elliptic profile control functions a, b, c, d and theta of the airfoil suction surface are selected as design variables:
X＝(a，b，c，d，θ) (2)
determining constraints
In order to change the local elliptic contour line of the airfoil suction surface of the horizontal-axis wind turbine blade in a controllable range, two coefficients of an airfoil local elliptic control function are constrained as follows:
Xmin≤X≤Xmax (3)
the design variable constraint ranges are shown in table 1:
TABLE 1 design variable Range
| a | b | c | d | θ/° | |
| Maximum value | 0.0 | 0.0 | 0.0 | 0.0 | -30.0 |
| Minimum value | 1.0 | 1.0 | 1.0 | 1.0 | 0.0 |
。
S2: comprehensively considering the aerodynamic performance of the airfoil before and after stall, giving the design power angle and the design Reynolds number before and after stall, and establishing the maximum lift-drag ratio of the airfoil under the smooth condition as an objective function;
the aerodynamic performance of the airfoil before and after stall is comprehensively considered, and under the working conditions that the designed attack angle is 6 degrees before the airfoil stalls and the designed attack angle is 14 degrees after the airfoil stalls, the designed Reynolds number Re is 3.0 multiplied by 106The mach number Ma is 0.15, and the maximum lift-drag ratio under the smooth condition is taken as a multi-objective function:
f(x)＝max(f1(x)，f2(x)) (4)
f1(x)＝CL/CD (5)
f2(x)＝C’L/C’D (6)
in formula (5), CLDesign lift coefficient at attack angle of 6 deg. C before stallDDesigning a resistance coefficient of an attack angle at 6 degrees before stalling; c'LDesign coefficient of lift at 14 DEG for post stall angle of attack, C'DThe drag coefficient at 14 ° angle of attack was designed for post stall.
S3: taking the objective function in the step S2 as an optimization target, filtering profiles which do not meet the requirements through constraint conditions, and giving an optimization algorithm to carry out optimization calculation on the delayed stall airfoil profiles which meet the requirements to obtain a target airfoil profile;
to achieve the integrated coupling optimization design of the delayed stall airfoil, four modular programs are programmed: delayed stall airfoil profile generation, ICEM adaptive grid technology (as shown in FIG. 3), FLUENT numerical calculation and optimization design module. The four modules are coupled into a simulated annealing algorithm for optimization iteration by programming a data interface program. The method specifically comprises the following steps:
(a) initializing variables, generating an airfoil profile line which adopts an elliptic function to generate a concave shape, and filtering out a non-delayed stall airfoil profile line through a constraint condition;
(b) compiling a data transfer program to call a data file of the delay stall airfoil profile meeting the requirements into an ICEM self-adaptive meshing module, reading the data file by the ICEM self-adaptive meshing module, automatically generating a structured mesh for the delay stall airfoil profile so as to read data point coordinate information on the profile, and outputting the data point coordinate information to a mesh format readable by FLUENT;
(c) the FLUENT calculation module calls the grid information output in the step (b), sets the aerodynamic performance parameters of the airfoil profile needing to be calculated, wherein the aerodynamic performance parameters comprise a lift coefficient and a drag coefficient of a designed attack angle within a certain angle range, calculates and converges the series of delayed stall airfoil families meeting the requirements, and outputs data point information on each airfoil profile line and the aerodynamic performance parameters corresponding to each airfoil profile;
(d) calculating a fitness value of the output airfoil family data and the corresponding aerodynamic performance parameters through an objective function;
(e) coupling the sub-program modules (a), (b), (c) and (d) to a simulated annealing algorithm optimization program for optimization iteration, thereby performing operations such as line planning, heating, constant temperature and cooling, wherein the related parameters of the simulated annealing algorithm are as follows: the population number is 30, the maximum iteration number is 200, the cooling rate is 0.9, the initial temperature is 1000, the finishing temperature is 0.001, and the chain length is 220; when the iteration condition is met, outputting a target airfoil profile; if the iteration condition is not met, the profile of the airfoil profile is adjusted in a self-adaptive manner, and the step (a) is executed in a rotating manner
And optimizing iteration through a simulated annealing algorithm, and finally outputting the delayed stall new airfoil with the maximum relative thickness of 30%, namely WT-E-300, as shown in figure 4.
In order to verify that the new airfoil has a high aerodynamic performance, in particular after stall. FIGS. 5, 6 and 7 show aerodynamic performance comparison plots of the new airfoil WT-E-300 with the conventional DU97-W-300 airfoil. Table 2 shows the maximum lift coefficient, maximum lift-drag ratio and average aerodynamic data over a range of angles of attack for the WT-E-300 airfoil and the DU97-W-300 airfoil. From the graph, it can be seen that: when the attack angle is larger than 14 degrees, the airfoil is in a stall state, the aerodynamic performance of the WT-E-300 new airfoil is superior to that of the DU97-W-300 airfoil, and the delayed stall characteristic is obviously shown. The maximum lift coefficient of the new airfoil WT-E-300 was 1.581, which is about 6.0% greater than that of the DU97-W-300 airfoil; the average lift coefficient of the WT-E-300 airfoil is 1.262, while the average lift coefficient of the DU97-W-300 airfoil is 1.126, which is increased by 12.1%; although the maximum lift-drag ratio of the WT-E-300 new airfoil is slightly reduced, the average lift-drag ratio is 37.128, while the average lift-drag ratio of the DU97-W-300 airfoil is 35.069, which is increased by 5.9%.
TABLE 2 Airfoil aerodynamic Performance parameter comparison
Note: the position or range of attack angle, C, being shown in parenthesesL，maxTo the maximum coefficient of lift, CL，averIs an average lift coefficient, L/D, within a certain range of angle of attack，maxAt maximum lift-to-drag ratio, L/D，averIs the average lift-drag ratio in a certain range of attack angle.
While the foregoing is directed to the preferred embodiment of the present invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof, and the scope thereof is determined by the claims that follow.
Claims (9)
1. A method of designing a stall controlled wind turbine airfoil, comprising:
s1: on the basis of the original airfoil profile, a profile of an inward concave shape is generated on the suction surface by locally using an elliptic function for representation, and design variables and constraint conditions are determined;
s2: comprehensively considering the aerodynamic performance of the airfoil before and after stall, giving the design power angle and the design Reynolds number before and after stall, and establishing the maximum lift-drag ratio of the airfoil under the smooth condition as an objective function;
s3: taking the objective function in the step S2 as an optimization target, filtering profiles which do not meet the requirements through constraint conditions, and giving an optimization algorithm to carry out optimization calculation on the delayed stall airfoil profiles which meet the requirements to obtain a target airfoil profile; wherein, this step specifically includes:
(a) initializing design variables, generating an airfoil profile which adopts an elliptic function to generate a concave shape, and filtering out a non-delayed stall airfoil profile through a constraint condition;
(b) calling in a delay stall airfoil profile meeting the requirement, and acquiring data point coordinate information on the delay stall airfoil profile;
(c) setting the aerodynamic performance parameters of the airfoil profile to be calculated, calculating and converging a series of delay stall airfoil families meeting the requirements, and outputting data point information of each airfoil profile and the corresponding aerodynamic performance parameters thereof
(d) Calculating a fitness value of the output airfoil family and the corresponding aerodynamic performance parameters thereof through an objective function;
(e) coupling the calculation modules in the steps (a) - (d) to a simulated annealing multi-objective evolutionary algorithm for optimization iteration, and outputting a target airfoil profile when an iteration condition is met; and (c) if the iteration condition is not met, performing self-adaptive adjustment on the airfoil profile, and performing rotation in the step (a).
2. The method of designing a stall controlled wind turbine airfoil according to claim 1, wherein the elliptical function in step S1 is expressed as:
in the above formula, the coefficient a > b >0, x is the horizontal coordinate of the airfoil on the xoy plane, y is the vertical coordinate of the airfoil xoy plane, c and d are plane coordinate offset parameters, and theta is a transformation angle.
3. The method for designing a stall controlled wind turbine airfoil according to claim 1, wherein five parameters a, b, c, d and θ are used as design variables in step S1: x ═ (a, b, c, d, θ);
the constraint conditions are as follows:
the two coefficients of the airfoil local elliptic control function are constrained as follows:
Xmin≤X≤Xmax
the design variable constraint ranges are:
a：0-1，b：0-1，c：0-1，d：0-1，θ：-30-0°。
4. the method for designing a stall controlled wind turbine airfoil according to claim 1, wherein the expression for maximizing the airfoil lift-drag ratio under smooth conditions as an objective function in step S2 is:
f(x)＝max(f1(x),f2(x))；
wherein f is1(x)＝CL/CD，f2(x)＝CL/C'D；
In the formula, CLDesigning lift coefficient of attack angle at certain angle before stall, CDDesigning a resistance coefficient of an attack angle at a certain angle before stalling; c'LDesigning a lift coefficient at a certain angle of attack for the post-stall, C'DAnd designing a resistance coefficient of an attack angle at a certain angle after the stall.
5. The method of designing a stall controlled wind turbine airfoil according to claim 1 or 4, wherein in step S2, the design angle of attack before stall is 6 °, the design angle of attack after stall is 14 °, and the design Reynolds number Re is 3.0 x 10 ═ 3.0 x 106。
6. The method of designing a stall controlled wind turbine airfoil according to claim 1, wherein the aerodynamic parameters in step (c) include lift coefficient and drag coefficient for a design angle of attack in the range of 0-24 °.
7. A method of designing a stall controlled wind turbine airfoil according to claim 1, wherein the parameters associated with the simulated annealing algorithm are as follows: the population number was 30, the maximum number of iterations 200, the cooling rate 0.9, the initial temperature 1000, the end temperature 0.001, and the chain length 220.
8. A method of designing a stall controlled windmill airfoil according to claim 1 wherein the original airfoil suction surface is formed with a semi-elliptical shape to a concave shape near 50% chord length.
9. A delayed stall controlled wind turbine blade airfoil optimally designed according to the stall controlled wind turbine airfoil design method as claimed in any one of claims 1 to 8.
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Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2382872A1 (en) * | 1999-08-25 | 2001-03-01 | Forskningscenter Riso (Riso National Laboratory) | Modified wind turbine airfoil |
| CN101458735A (en) * | 2008-12-31 | 2009-06-17 | 重庆大学 | Aerofoil with high lift-drag ratio |
| CN101615216A (en) * | 2009-07-28 | 2009-12-30 | 重庆大学 | The aerofoil profile trailing edge is carried out the method that streamlined thickens |
| CN101886619A (en) * | 2010-07-07 | 2010-11-17 | 重庆大学 | Special airfoil for blade tip of wind driven generator |
| CN101898644A (en) * | 2009-05-25 | 2010-12-01 | 丹麦技术大学 | System and method for designing airfoil |
| CN102235325A (en) * | 2011-07-01 | 2011-11-09 | 重庆大学 | Method for designing airfoil section of blade tip of wind machine based on airfoil section integration and mixed trailing edge modification |
| CN102691631A (en) * | 2011-03-22 | 2012-09-26 | 通用电气公司 | System and method for increasing energy capture by wind turbines |
| CN103047079A (en) * | 2012-12-22 | 2013-04-17 | 中国科学院工程热物理研究所 | Efficient low-load wing section special for horizontal shaft wind turbine blade and designing method of wind section |
| CN103277245A (en) * | 2013-06-14 | 2013-09-04 | 中国科学院工程热物理研究所 | Large-thickness blunt-trailing-edge wind-power airfoil profiles and a design method thereof |
| CN104317992A (en) * | 2014-10-11 | 2015-01-28 | 重庆工商大学 | Positive design method of wind turbine airfoil and wind turbine airfoil family |
| CN104612892A (en) * | 2014-12-30 | 2015-05-13 | 中国科学院工程热物理研究所 | Multi-disciplinary optimization design method for airfoil profile of wind turbine |
| CN105404743A (en) * | 2015-11-25 | 2016-03-16 | 湖北工业大学 | Wind turbine airfoil design method combining B spline with curvature smooth continuity |
| CN105868470A (en) * | 2016-03-29 | 2016-08-17 | 湖北工业大学 | Wind turbine wing shape and blade appearance parameter integrated design method |
| CN109145506A (en) * | 2018-09-20 | 2019-01-04 | 中国科学院工程热物理研究所 | The optimum design method of aerofoil profile on the outside of a kind of high aeroperformance low noise level wind energy conversion system |
| CN109190283A (en) * | 2018-09-20 | 2019-01-11 | 中国科学院工程热物理研究所 | A kind of wind mill airfoil Aerodynamic optimization method considering high Turbulent Free incoming flow effect |
| CN109460566A (en) * | 2018-09-20 | 2019-03-12 | 中国科学院工程热物理研究所 | A kind of pneumatic Robust Optimal Design method of pneumatic equipment bladess inside thick wing type |
| CN109783912A (en) * | 2018-12-29 | 2019-05-21 | 湖北工业大学 | A kind of lifting-force type vertical-axis wind power generator vane airfoil profile optimum design method |
| EP3543108A1 (en) * | 2018-03-22 | 2019-09-25 | Facebook, Inc. | Automatic airfoil and wing design based on dynamic modeling of structural and aerodynamic performance |
| CN111400834A (en) * | 2020-03-20 | 2020-07-10 | 国电联合动力技术有限公司 | Aerodynamic optimization design method, model and device for wind generating set blade airfoil |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110052400A1 (en) * | 2009-08-31 | 2011-03-03 | Sarbuland Khan | Horizontal axis wind turbine (HAWT) |
| WO2013054404A1 (en) * | 2011-10-12 | 2013-04-18 | 三菱重工業株式会社 | Wind turbine blade, wind power generation device provided with same, and design method for wind turbine blade |
| CN104863799A (en) * | 2015-04-17 | 2015-08-26 | 湖北工业大学 | Method for designing wind turbine airfoil by using Bessel function curve |
| CN105787212B (en) * | 2016-03-29 | 2019-03-01 | 湖北工业大学 | A kind of wind mill airfoil design method of anti-aeroeleastic deformation |
-
2020
- 2020-07-16 CN CN202010688073.XA patent/CN111859801B/en active Active
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2382872A1 (en) * | 1999-08-25 | 2001-03-01 | Forskningscenter Riso (Riso National Laboratory) | Modified wind turbine airfoil |
| CN101458735A (en) * | 2008-12-31 | 2009-06-17 | 重庆大学 | Aerofoil with high lift-drag ratio |
| CN101898644A (en) * | 2009-05-25 | 2010-12-01 | 丹麦技术大学 | System and method for designing airfoil |
| CN101615216A (en) * | 2009-07-28 | 2009-12-30 | 重庆大学 | The aerofoil profile trailing edge is carried out the method that streamlined thickens |
| CN101886619A (en) * | 2010-07-07 | 2010-11-17 | 重庆大学 | Special airfoil for blade tip of wind driven generator |
| CN102691631A (en) * | 2011-03-22 | 2012-09-26 | 通用电气公司 | System and method for increasing energy capture by wind turbines |
| CN102235325A (en) * | 2011-07-01 | 2011-11-09 | 重庆大学 | Method for designing airfoil section of blade tip of wind machine based on airfoil section integration and mixed trailing edge modification |
| CN103047079A (en) * | 2012-12-22 | 2013-04-17 | 中国科学院工程热物理研究所 | Efficient low-load wing section special for horizontal shaft wind turbine blade and designing method of wind section |
| CN103277245A (en) * | 2013-06-14 | 2013-09-04 | 中国科学院工程热物理研究所 | Large-thickness blunt-trailing-edge wind-power airfoil profiles and a design method thereof |
| CN104317992A (en) * | 2014-10-11 | 2015-01-28 | 重庆工商大学 | Positive design method of wind turbine airfoil and wind turbine airfoil family |
| CN104612892A (en) * | 2014-12-30 | 2015-05-13 | 中国科学院工程热物理研究所 | Multi-disciplinary optimization design method for airfoil profile of wind turbine |
| CN105404743A (en) * | 2015-11-25 | 2016-03-16 | 湖北工业大学 | Wind turbine airfoil design method combining B spline with curvature smooth continuity |
| CN105868470A (en) * | 2016-03-29 | 2016-08-17 | 湖北工业大学 | Wind turbine wing shape and blade appearance parameter integrated design method |
| EP3543108A1 (en) * | 2018-03-22 | 2019-09-25 | Facebook, Inc. | Automatic airfoil and wing design based on dynamic modeling of structural and aerodynamic performance |
| CN109145506A (en) * | 2018-09-20 | 2019-01-04 | 中国科学院工程热物理研究所 | The optimum design method of aerofoil profile on the outside of a kind of high aeroperformance low noise level wind energy conversion system |
| CN109190283A (en) * | 2018-09-20 | 2019-01-11 | 中国科学院工程热物理研究所 | A kind of wind mill airfoil Aerodynamic optimization method considering high Turbulent Free incoming flow effect |
| CN109460566A (en) * | 2018-09-20 | 2019-03-12 | 中国科学院工程热物理研究所 | A kind of pneumatic Robust Optimal Design method of pneumatic equipment bladess inside thick wing type |
| CN109783912A (en) * | 2018-12-29 | 2019-05-21 | 湖北工业大学 | A kind of lifting-force type vertical-axis wind power generator vane airfoil profile optimum design method |
| CN111400834A (en) * | 2020-03-20 | 2020-07-10 | 国电联合动力技术有限公司 | Aerodynamic optimization design method, model and device for wind generating set blade airfoil |
Non-Patent Citations (16)
| Title |
|---|
| 垂直轴风力机翼型气动优化设计;梁昌平等;《航空计算技术》;20160925(第05期);全文 * |
| 基于CFD技术与遗传算法的风力机大厚度翼型优化设计;汪泉等;《水电能源科学》;20200619(第06期);全文 * |
| 基于Fluent的风力机叶片翼型气动性能数值计算;吴友健等;《节能》;20200125(第01期);全文 * |
| 基于复合形法的垂直轴风力机翼型优化设计;曲建俊等;《可再生能源》;20110615(第03期);全文 * |
| 基于多点攻角的风力机翼型优化设计;汪泉等;《哈尔滨工程大学学报》;20161201(第11期);全文 * |
| 基于多目标遗传算法的风力机翼型形状优化;张石强等;《太阳能学报》;20110828(第08期);全文 * |
| 基于改进的粒子群算法的风力机叶片优化设计;杨从新等;《新技术新工艺》;20131025(第10期);全文 * |
| 基于最大风能利用系数的风力机翼型设计;程江涛等;《机械工程学报》;20101220(第24期);全文 * |
| 基于翼型集成和混合式尾缘改型理论的风力机叶尖翼型设计;陆群峰等;《太阳能学报》;20130428(第04期);全文 * |
| 基于自适应模拟退火遗传算法的风力机翼型优化设计;刘华威等;《可再生能源》;20180620(第06期);全文 * |
| 基于连续攻角的风力机翼型整体气动性能提高的优化设计;汪泉等;《机械工程学报》;20170731(第13期);全文 * |
| 水平轴风力机翼型设计与动态失速数值模拟;赵旭等;《太阳能学报》;20090328(第03期);全文 * |
| 翼型集成理论与B样条结合的风力机翼型优化设计方法研究;陈进等;《太阳能学报》;20141028(第10期);全文 * |
| 雷诺数对粗糙表面翼型气动性能的影响;李仁年等;《南京航空航天大学学报》;20111015(第05期);全文 * |
| 风力机专用翼型发展现状及其关键气动问题分析;陈培等;《电网与清洁能源》;20090225(第02期);全文 * |
| 风力机翼型转捩与失速特性的数值计算;李志敏等;《山东电力高等专科学校学报》;20130215(第01期);全文 * |
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