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CN114266202A - A modified actuation line model method for simulating wind turbine wakes - Google Patents

A modified actuation line model method for simulating wind turbine wakes Download PDF

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CN114266202A
CN114266202A CN202111568230.4A CN202111568230A CN114266202A CN 114266202 A CN114266202 A CN 114266202A CN 202111568230 A CN202111568230 A CN 202111568230A CN 114266202 A CN114266202 A CN 114266202A
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blade
wind turbine
formula
line model
point
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薛飞飞
许昌
韩星星
程哲
冉续
焦志雄
黄雨薇
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Hohai University HHU
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Hohai University HHU
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Abstract

The invention discloses a method for simulating a modified actuation line model of a wind turbine wake flow, which comprises the following steps: simplifying the wind turbine blade into an actuation line model; acquiring speed information in the leaf pixel points; calculating the axial force and the tangential force at the chlorophyll point through a chlorophyll theory; calculating the volume force on the phyllo-element point; correcting through the blade tip and blade root loss correction model; correcting the two-dimensional airfoil lift coefficient by adopting a three-dimensional delay stall model; the actuation wire area adds a volumetric force; and calculating a simulated flow field. The invention provides a method for simulating a corrected actuating line model of the wake flow of a wind turbine, and the built full-size wind turbine actuating line model can enable the pneumatic characteristics of the actuating line model and the wake flow speed to better match with experimental test data, and has good application prospect in actual engineering.

Description

Modified actuating line model method for simulating wake flow of wind turbine
Technical Field
The invention relates to a modified actuation line model method for simulating the wake flow of a wind turbine, and belongs to the technical field of calculation of the wake flow of the wind turbine by using a brake model.
Background
Wind energy is an important renewable energy source, and the annual average wind power density of 70m high layers in land in China reaches 300W/m2The exploitable amount of the wind energy resource technology is 2.6TW, and the exploitation and utilization value is huge. In a large wind power plant, a wind turbine is necessarily positioned in the wake of an upstream wind turbine, so that the incoming wind speed is reduced, and the wind shear and strong turbulence added by the wake are increased. In recent years, simulating wake effect by using CFD has become a research hotspot.
In the prior art, the numerical simulation of the wake flow of the wind turbine by adopting an actuation line model obtains better prediction accuracy, but because the blade tip and root loss, the three-dimensional airfoil profile delayed stall and the influence of a cabin and a tower are not considered, the generation prediction of the central vortex and the blade tip vortex still has an error problem.
Disclosure of Invention
In order to solve the defects of the prior art, the invention aims to provide a method for simulating a corrected actuating line model of the wake flow of a wind turbine, wherein a full-size wind turbine actuating line model is established, the improved braking line model is used for carrying out numerical simulation calculation on the wake flow field of the wind turbine, and the accuracy of the corrected wind turbine actuating line model is verified by comparing experimental data with an uncorrected model in the aspects of the power coefficient, the thrust coefficient and the wake flow speed of the wind turbine.
In order to achieve the above object, the present invention adopts the following technical solutions:
a method for simulating a modified actuation line model of a wind turbine wake flow comprises the following steps:
simplifying the wind turbine blade into an actuation line model;
acquiring speed information in the leaf pixel points;
calculating the axial force and the tangential force at the chlorophyll point through a chlorophyll theory;
calculating the volume force on the phyllo-element point;
correcting through the blade tip and blade root loss correction model;
correcting the two-dimensional airfoil lift coefficient by adopting a three-dimensional delay stall model;
calculating the resistance of the tower and the engine room;
and calculating a simulated flow field.
Further, the foregoing specific steps of simplifying the wind turbine blade into the actuation line model include:
simplifying the rotating wind wheel blade into an imaginary line segment, and dividing the imaginary line segment into a plurality of segments of phyllanthus;
determining the three-dimensional coordinates of each leaf element point in the rotation process of the blade through a formula, wherein the formula is as follows:
xi＝xwt+rcosφ
yi＝ywt+rcosφ
zi＝zwt+rsinφ
wherein x isi、yi、ziIs the three-dimensional coordinate of the phyllanthus point i; r is the spreading length; phi is the rotation angle of the blade; x is the number ofwt、ywt、zwtIs the three-dimensional coordinate of the hub center of the wind turbine.
Further, the specific method for acquiring the velocity information in the leaf points is as follows:
in a CFD flow field, searching a grid core nearest to a leaf element point, and assigning speed information stored by the grid core to the leaf element point;
if it satisfies
Figure BDA0003422487930000021
Then u isi＝ucell+ gradu dS, where xi_cellIs a grid core coordinate; DXiIs the mesh size; u. ofiIs the velocity at the phyllotoxin point; u. ofcellIs distance fromThe nearest grid centroid velocity to the leaf pixel point; gradu is the flow field velocity gradient; dS is the distance of the leaf element point to the nearest grid centroid.
Further, the method for calculating the axial force and the tangential force through the phyllotactic theory comprises the following steps:
substituting the velocity of the assigned phylloton point into a formula to obtain an axial force T and a tangential force FNThe formula is
Figure BDA0003422487930000022
Wherein the total velocity
Figure BDA0003422487930000023
Axial velocity
Figure BDA0003422487930000024
Tangential velocity of
Figure BDA0003422487930000025
Where ρ is the air density,
Figure BDA00034224879300000212
is axial normal vector, c is chord length of airfoil profile, inflow angle
Figure BDA0003422487930000026
ClIs the coefficient of lift, CdIs coefficient of resistance, angle of attack
Figure BDA0003422487930000027
Beta is the twist angle of the phyllanthin, dr is the spread length of the phyllanthin,
Figure BDA0003422487930000028
is the velocity at the point of the leaf element,
Figure BDA0003422487930000029
is the angular velocity of the beam of light,
Figure BDA00034224879300000210
is the vector radius.
Further, the step of calculating the volume force at the phyllo site comprises:
Figure BDA00034224879300000211
in the formula (f)x/fy/fzRespectively representing the volume force of the phyllotoxin point in the xyz direction; gamma is the angle of clockwise yaw of the wind turbine; δ is the angle of rotation of the blade; b is the number of leaves; i is the number of the located lutein point;
the three-dimensional Gaussian distribution function is adopted to carry out the fairing of the volume force, and the volume force f borne by a certain grid type center point in the flow fieldMComprises the following steps:
Figure BDA0003422487930000031
wherein d is the distance between the centromere and the lutein; ε is the fairing parameter.
Further, the foregoing procedure of modifying through the blade tip and root loss modification model is as follows:
substituting into a formula to obtain a tip correction coefficient F1And root correction factor FhubThe formula is as follows:
Figure BDA0003422487930000032
wherein g ═ exp (-0.125(B λ -21)) + 0.1; λ is the tip speed ratio; r is the blade radius; rhubThe radius of the blade root of the wind turbine rotor; r is the spread length of the chlorophyll; b is the number of leaves;
Figure BDA0003422487930000033
is the inflow angle.
Further, the process for correcting the two-dimensional airfoil lift coefficient by using the three-dimensional delayed stall model is as follows:
the part below the extension length of the blade 3/4 is corrected and substituted into a formula to solve the three-dimensional airfoil lift coefficient Cl,3dAnd a degree of change in angle of attack, Δ α, the formula being:
Figure BDA0003422487930000034
in the formula (I), the compound is shown in the specification,
Figure BDA0003422487930000035
the slope of a straight line segment of the lift coefficient; delta alpha is the angle of attack change degree; cl,3dIs a three-dimensional airfoil lift coefficient; cl,2dIs a two-dimensional airfoil lift coefficient; alpha is alphamaxThe angle of attack corresponding to the maximum lift coefficient; alpha is alpha0The corresponding attack angle when the lift coefficient is zero; c is the chord length of the blade; n is an empirical formula and is generally taken to be 1.0; k is the von Karman constant.
Further, the method for adding the volume force to the actuation line area comprises the following steps:
substituting a formula to obtain the axial resistance df of the airflow of a tower tube infinitesimalx,towAnd nacelle resistance FnacThe formula is as follows:
Figure BDA0003422487930000036
in the formula utowThe incoming flow speed is the center of the tower tube infinitesimal; ρ is the air density; dtowThe diameter of the central circular section of the tower tube infinitesimal; dh is the height of the tower tube infinitesimal; cD,towThe resistance coefficient of the tower barrel takes 1.0; a. thenacThe sectional area of the engine room; cD,nacThe value of the resistance coefficient of the engine room is 1.0; axial velocity
Figure BDA0003422487930000041
Figure BDA0003422487930000042
Is the axial normal vector of the axial direction,
Figure BDA0003422487930000043
is the velocity at the phyllotoxin point.
The invention achieves the following beneficial effects:
1. the invention can enable the pneumatic characteristic and the wake velocity of the actuating line model to better coincide with the experimental test data, and has good application prospect in the actual engineering;
2. theoretical support is provided for work such as wind turbine wake flow calculation, wind turbine power prediction and the like.
Drawings
FIG. 1 is a flow chart of a modified actuation line model of the present invention;
figure 2 is a rotation of the wind rotor of the invention;
FIG. 3 illustrates a wind turbine source and item model of the present invention;
FIG. 4 is a folate stress assay of the present invention;
FIG. 5 is a G1 model of a wind turbine of the present invention;
FIG. 6 is a wind turbine center radial velocity profile at-1D before the G1 model correction wake;
FIG. 7 is a wind turbine center radial velocity profile 2D after the G1 model modifies the wake;
FIG. 8 is a 3D rotor center radial velocity profile after the G1 model modifies the wake;
FIG. 9 is a wind turbine center radial velocity profile 4D after the G1 model modifies the wake;
FIG. 10 is a wind turbine center radial velocity profile 6D after the G1 model modifies the wake;
FIG. 11 is the rotor center radial velocity profile 9D after the G1 model correction wake.
Detailed Description
The invention is further described below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.
As shown in fig. 1 to 11, the method for establishing a model based on a modified actuation line includes the following steps:
step 1: as shown in fig. 2, the rotating wind turbine blade is simplified into an imaginary line segment, and is divided into several segments of phyllanthus, an actuation line model is preliminarily formed, and then a volume force is added to the source term of the control equation through steps 2) -9).
Finally, the full-size wind turbine actuating line model comprising the blade, the cabin and the tower source items shown in the figure 3 is obtained.
Step 2: determining the three-dimensional coordinates of each leaf element point in the rotation process of the blade, wherein the calculation formula is as follows:
xi＝xwt+rcosφ
yi＝ywt+rcosφ
zi＝zwt+rsinφ
wherein x isi、yi、ziIs the three-dimensional coordinate of the phyllanthus point i; r is the spreading length; phi is the rotation angle of the blade; x is the number ofwt、ywt、zwtIs the three-dimensional coordinate of the hub center of the wind turbine.
And step 3: in the CFD flow field, information of the flow field such as pressure, velocity, volume force source terms, etc. is stored in a grid center, and when the blade rotates in the calculation region, the leaf element point does not necessarily coincide with the grid center, so that the grid center closest to the leaf element point needs to be found first, and then the stored velocity information is assigned to the leaf element point. And meanwhile, when the grid type center coordinate and the leaf element point coordinate satisfy:
Figure BDA0003422487930000051
at this time, ui＝ucell+ gradu dS, where xi_cellIs a grid core coordinate; DXiIs the mesh size; u. ofiIs the velocity at the phyllotoxin point; u. ofcellIs the nearest grid centroid velocity to the leaf pixel point; gradu is the flow field velocity gradient; dS is the distance of the leaf element point to the nearest grid centroid.
And 4, step 4: as shown in FIG. 4, which is a velocity triangle of the relative velocity of the airflow with respect to the blade and the axial and tangential forces, the axial and tangential forces T and F are derived from the velocity at the blistering point and the blistering theoryN：
Figure BDA0003422487930000052
Wherein the total velocity
Figure BDA0003422487930000053
Axial velocity
Figure BDA0003422487930000054
Tangential velocity of
Figure BDA0003422487930000055
Where ρ is the air density,
Figure BDA0003422487930000056
is axial normal vector, c is chord length of airfoil profile, inflow angle
Figure BDA0003422487930000057
Coefficient of lift ClAnd coefficient of resistance CdObtaining the angle of attack and airfoil profile aerodynamic data; angle of attack
Figure BDA0003422487930000058
Beta is the torsion angle of the phyllanthin; dr is the spread length of the phyllanthin;
Figure BDA0003422487930000059
is the velocity at the phyllotoxin point;
Figure BDA00034224879300000510
is the angular velocity;
Figure BDA00034224879300000511
is the vector radius.
And 5: the axial force and the tangential force on the blade unit are combined into a three-dimensional volume force in a Cartesian coordinate system, and a calculation formula is as follows:
Figure BDA00034224879300000512
in the formula (f)x/fy/fzRespectively representing the volume force of the phyllotoxin point in the xyz direction; gamma is the angle of clockwise yaw of the wind turbine; δ is the angle of rotation of the blade; b is the number of leaves; i is the number of the located lutein point.
Then, performing volume force fairing by adopting a three-dimensional Gaussian distribution function, wherein the volume force applied to a certain grid type center point in a flow field is as follows:
Figure BDA00034224879300000513
wherein d is the distance between the centromere and the lutein; ε is the fairing parameter related to the mesh size.
Step 6: the tip vortex and the root vortex generated by the wind turbine in the rotation process fall off and then enter the wake zone, the induced speed distribution of the rotor is influenced, and the tip and root loss correction model is adopted for correction.
Further, the specific calculation process in the blade tip and root loss correction model is as follows:
Figure BDA0003422487930000061
wherein g ═ exp (-0.125(B λ -21)) + 0.1; fhubModifying the coefficient for the blade root; f1Correcting the coefficient for the blade tip; λ is the tip speed ratio; r is the blade radius; rhubThe radius of the blade root of the wind turbine rotor; r is the spread length of the chlorophyll; b is the number of leaves;
Figure BDA0003422487930000062
is the inflow angle.
And 7: when the wind turbine rotates, the suction surface at the root part of the blade can have certain spread flow, so that Coriolis force pointing to the trailing edge of the airfoil profile of the blade is generated, the Coriolis force and the centrifugal force generated by the rotation of the wind turbine act together, the adverse pressure gradient in the boundary layer on the surface of the blade is resisted, the separation of the boundary layer is delayed, the lift coefficient of the airfoil profile is improved, and the three-dimensional stall delay effect of the wind turbine blade is realized. And correcting the lift coefficient of the two-dimensional airfoil profile by adopting a three-dimensional delay stall model.
Further, when the two-dimensional airfoil lift coefficient is corrected, the part of the blade 3/4 with the length less than the span length is corrected, and a specific correction calculation formula is as follows:
Figure BDA0003422487930000063
in the formula, Cl,3dIs a three-dimensional airfoil lift coefficient; delta alpha is the angle of attack change degree;
Figure BDA0003422487930000064
the slope of a straight line segment of the lift coefficient; cl,2dIs a two-dimensional airfoil lift coefficient; alpha is alphamaxThe angle of attack corresponding to the maximum lift coefficient; alpha is alpha0The corresponding attack angle when the lift coefficient is zero; c is the chord length of the blade; n is an empirical formula and is generally taken to be 1.0; k is the von Karman constant.
And 8: the nacelle and the tower of the wind turbine not only can attenuate the speed in the wake flow, but also can affect the turbulence energy of the wake flow, and particularly, the interaction between the wake flow formed by the tower and the wake flow generated by the blades can accelerate the fracture of blade tip vortexes, so the resistance of the tower and the nacelle needs to be calculated, and the calculation formula is as follows:
Figure BDA0003422487930000065
in the formula, dfx,towThe airflow axial resistance of a tower drum infinitesimal; ρ is the air density; fnacIs the cabin drag; u. oftowThe incoming flow speed is the center of the tower tube infinitesimal; dtowThe diameter of the central circular section of the tower tube infinitesimal; dh is the height of the tower tube infinitesimal; cD,towThe resistance coefficient of the tower barrel takes 1.0; a. thenacThe sectional area of the engine room; cD,nacThe value of the resistance coefficient of the engine room is 1.0; u is the axial velocity.
And step 9: calculating a simulated flow field: after the blades are rotated, the brake wire mesh is identified by repeating the above steps at each time step.
Verification is performed by using the wind turbine G1 as a research object for numerical simulation verification of the modified actuation line model. The diameter of a wind wheel of the wind turbine is 1.1m, the diameter of a hub is 0.03m, the height of a tower barrel is 0.8m, and the design of blades adopts RG 14. The wind turbine G1 is used as a model, the blade radius is 0.55m at the inlet wind speed of 5m/s, and the rated rotating speed is 850rad min-1The wind turbine G1 position in the flow field, and the overall length, width and height of the model validation calculation domain are shown in fig. 5. 6-11 are comparisons of radial mean wind speed at center of rotor at 6 positions of G1 wind turbine before-1D wake and after 2D, 3D, 4D, 6D, 9D and test data, wherein black dots represent the test data, dashed lines represent the actuation line model, and solid lines represent the modified actuation line model. As can be seen, the center trail (y/D ═ 0) velocity of the modified actuation line model is closer to the experimental value than the conventional actuation line model, since the tip and root losses are corrected. At far wake, the modified actuation line model value is closer to the experimental value. The traditional actuation line model has higher prediction accuracy on the thrust coefficient and the power factor, but certain errors still exist in the prediction on the central vortex and the blade tip vortex due to the loss of the blade tip and the blade root. The analysis shows that the coincidence degree of the corrected model and the experimental value is superior to that of the uncorrected model, and the wind speed attenuation condition of the wake flow of the wind turbine can be better simulated.
The following table 1 shows that the calculated thrust coefficient, power coefficient and experimental measured value show that the corrected wind turbine actuation line model is very close to the experimental value in the prediction result of the aerodynamic performance and is obviously superior to the uncorrected model, especially the prediction of the thrust coefficient, because the corrected model considers the loss of the blade tip and the blade root of the wind turbine, namely the load coefficient is reduced, the calculated wind turbine thrust is lower than that of the uncorrected model.
Figure BDA0003422487930000071
TABLE 1 comparison table of parameters before and after correction
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.

Claims (8)

1.一种模拟风力机尾流的修正致动线模型方法，其特征在于，包括如下步骤：1. a modified actuation line model method for simulating a wind turbine wake, is characterized in that, comprises the steps: 将风轮叶片简化为致动线模型；Simplify the wind rotor blade as an actuation line model; 获取叶素点中的速度信息；Get the speed information in the leaf element point; 通过叶素理论计算叶素点处轴向力和切向力；Calculate the axial force and tangential force at the blade element point by the blade element theory; 计算叶素点上的体积力；Calculate the body force on the leaf element point; 通过叶尖叶根损失修正模型进行修正；Correction is made through the blade tip and root loss correction model; 采用三维延迟失速模型对二维翼型升力系数进行修正；The lift coefficient of the two-dimensional airfoil is modified by the three-dimensional delayed stall model; 计算塔筒与机舱阻力；Calculate tower and nacelle resistance; 计算模拟流场。Calculate the simulated flow field. 2.根据权利要求1所述的一种模拟风力机尾流的修正致动线模型方法，其特征在于，所述将风轮叶片简化为致动线模型的具体步骤包括：2 . The modified actuation line model method for simulating the wake of a wind turbine according to claim 1 , wherein the specific step of simplifying the wind turbine blade into an actuation line model comprises: 2 . 将旋转的风轮叶片简化成一条假想的线段，并将其分成若干段叶素；Simplify the rotating rotor blade into an imaginary line segment and divide it into several segments; 通过公式确定叶片旋转过程中各叶素点的三维坐标，所述公式为：The three-dimensional coordinates of each leaf element point in the process of blade rotation are determined by the formula, and the formula is: xi＝xwt+rcosφx i =x wt +rcosφ yi＝ywt+rcosφy i =y wt +rcosφ zi＝zwt+rsinφ zi = z wt +rsinφ 其中，xi、yi、zi为叶素点i的三维坐标；r为展长；φ为叶片的旋转角度；xwt、ywt、zwt为风力机轮毂中心的三维坐标。Among them, x i , yi , and zi are the three-dimensional coordinates of the blade element point i; r is the extension; φ is the rotation angle of the blade; x wt , y wt , and z wt are the three-dimensional coordinates of the center of the wind turbine hub. 3.根据权利要求2所述的一种模拟风力机尾流的修正致动线模型方法，其特征在于，所述获取叶素点中的速度信息的具体方法如下：3. The modified actuation line model method for simulating a wind turbine wake according to claim 2, wherein the specific method for obtaining the speed information in the blade element point is as follows: 在CFD流场中，寻找离叶素点最近的网格型心，然后将该网格型心存储的速度信息赋给叶素点；In the CFD flow field, find the grid centroid closest to the leaf element point, and then assign the velocity information stored in the grid centroid to the leaf element point; 若满足
Figure FDA0003422487920000011
则ui＝ucell+gradu*dS，式中xi_cell为网格型心坐标；DXi为网格尺寸；ui为叶素点处的速度；ucell是距离该叶素点最近的网格型心速度；gradu为流场速度梯度；dS为该叶素点到最近网格型心的距离。if satisfied
Figure FDA0003422487920000011
Then u i = u cell +gradu*dS, where x i_cell is the grid center coordinate; DX i is the grid size; u i is the velocity at the leaf point; u cell is the grid closest to the leaf point. Grid center velocity; gradu is the velocity gradient of the flow field; dS is the distance from the leaf element point to the nearest grid center. 4.根据权利要求3所述的一种模拟风力机尾流的修正致动线模型方法，其特征在于，所述通过叶素理论计算轴向力和切向力的方法包括：4. The modified actuation line model method for simulating the wake of a wind turbine according to claim 3, wherein the method for calculating the axial force and the tangential force through the blade element theory comprises: 将赋值的叶素点处速度带入公式得到轴向力T和切向力FN，所述公式为Bring the assigned velocity at the element point into the formula to obtain the axial force T and the tangential force F N , the formula is
Figure FDA0003422487920000021
Figure FDA0003422487920000021
 其中，总速度
Figure FDA0003422487920000022
轴向速度
Figure FDA0003422487920000023
切向速度为
Figure FDA0003422487920000024
Among them, the total speed
Figure FDA0003422487920000022
Axial speed
Figure FDA0003422487920000023
The tangential velocity is
Figure FDA0003422487920000024
 式中，ρ是空气密度，
Figure FDA0003422487920000025
是轴向法向量，c是翼型的弦长，入流角
Figure FDA0003422487920000026
Cl是升力系数，Cd是阻力系数，迎角
Figure FDA0003422487920000027
β为所在叶素的扭角，dr为叶素展长，
Figure FDA0003422487920000028
是叶素点处的速度，
Figure FDA0003422487920000029
是角速度，
Figure FDA00034224879200000210
是矢量半径。where ρ is the air density,
Figure FDA0003422487920000025
is the axial normal vector, c is the chord length of the airfoil, and the inflow angle
Figure FDA0003422487920000026
C l is the lift coefficient, C d is the drag coefficient, the angle of attack
Figure FDA0003422487920000027
β is the twist angle of the leaf element, dr is the length of the leaf element,
Figure FDA0003422487920000028
is the velocity at the leaf element point,
Figure FDA0003422487920000029
is the angular velocity,
Figure FDA00034224879200000210
is the vector radius. 5.根据权利要求4所述的一种模拟风力机尾流的修正致动线模型方法，其特征在于，所述计算叶素点上的体积力的步骤包括：5. The modified actuation line model method for simulating the wake of a wind turbine according to claim 4, wherein the step of calculating the body force on the blade element point comprises: fx＝-Tf x = -T
Figure FDA00034224879200000211
Figure FDA00034224879200000211
 式中，fx/fy/fz分别代表叶素点在xyz方向的体积力；γ是风力机顺时针偏航的角度；δ是叶片的旋转角度；B是叶片数；i是所在叶素点的编号；In the formula, f x /f y /f z respectively represent the body force of the blade element point in the xyz direction; γ is the clockwise yaw angle of the wind turbine; δ is the rotation angle of the blade; B is the number of blades; i is the blade where The number of the element point; 采用三维高斯分布函数进行体积力光顺，流场中某一网格型心点受到的体积力fM为：The three-dimensional Gaussian distribution function is used to smooth the body force, and the body force f M received by a grid center point in the flow field is:
Figure FDA00034224879200000212
Figure FDA00034224879200000212
 式中，d为型心点和叶素之间的距离；ε是光顺参数。In the formula, d is the distance between the center point and the leaf element; ε is the smoothing parameter. 6.根据权利要求4所述的一种模拟风力机尾流的修正致动线模型方法，其特征在于，所述通过叶尖叶根损失修正模型进行修正的过程如下：6. The modified actuation line model method for simulating the wake of a wind turbine according to claim 4, characterized in that, the process of modifying through the blade tip and blade root loss correction model is as follows: 带入公式，求得叶尖修正系数F1和叶根修正系数Fhub，所述公式为：Bring in the formula to obtain the tip correction coefficient F 1 and the blade root correction coefficient F hub , and the formula is:
Figure FDA00034224879200000213
Figure FDA00034224879200000213
 式中，g＝exp(-0.125(Bλ-21))+0.1；λ是叶尖速比；R为叶片半径；Rhub为风力机转子叶根处半径；r是叶素展长；B是叶片数；
Figure FDA00034224879200000214
为入流角。In the formula, g=exp(-0.125(Bλ-21))+0.1; λ is the tip speed ratio; R is the blade radius; R hub is the radius of the rotor blade root of the wind turbine; r is the blade element length; B is the number of blades ;
Figure FDA00034224879200000214
is the inflow angle. 7.根据权利要求1所述的一种模拟风力机尾流的修正致动线模型方法，其特征在于，所述采用三维延迟失速模型对二维翼型升力系数进行修正过程如下：7. the modified actuation line model method of a kind of simulated wind turbine wake according to claim 1, is characterized in that, described adopting three-dimensional delayed stall model to carry out the correction process to two-dimensional airfoil lift coefficient as follows: 对叶片3/4展长以下的部分进行修正，带入公式求三维翼型升力系数Cl,3d和迎角变化度数Δα，所述公式为：Modify the part below the 3/4 span of the blade, and bring in the formula to obtain the three-dimensional airfoil lift coefficient C l,3d and the angle of attack change degree Δα, the formula is:
Figure FDA0003422487920000031
Figure FDA0003422487920000031
 式中，
Figure FDA0003422487920000032
为升力系数直线段斜率；Δα为迎角变化度数；Cl,3d为三维翼型升力系数；Cl,2d为二维翼型升力系数；αmax为最大升力系数对应的迎角；α0为升力系数为零时对应的迎角；c为叶片弦长；n为经验公式一般取为1.0；k为冯卡门常数。In the formula,
Figure FDA0003422487920000032
is the slope of the straight line segment of the lift coefficient; Δα is the degree of change in the angle of attack; C l,3d is the three-dimensional airfoil lift coefficient; C l,2d is the two-dimensional airfoil lift coefficient; α max is the angle of attack corresponding to the maximum lift coefficient; α 0 is the corresponding angle of attack when the lift coefficient is zero; c is the chord length of the blade; n is the empirical formula generally taken as 1.0; k is the von Karman constant. 8.根据权利要求1所述的一种模拟风力机尾流的修正致动线模型方法，其特征在于，所述致动线区域添加体积力的方法包括：8 . The modified actuation line model method for simulating a wind turbine wake according to claim 1 , wherein the method for adding body force to the actuation line region comprises: 带入公式，求得一个塔筒微元的气流轴向阻力dfx,tow和机舱阻力Fnac，所述公式为：Bring in the formula to obtain the airflow axial resistance df x, tow and the nacelle resistance F nac of a tower cell, the formula is:
Figure FDA0003422487920000033
Figure FDA0003422487920000033
 式中，utow为该塔筒微元中心来流风速；ρ是空气密度；dtow为该塔筒微元中心圆形截面直径；dh为该塔筒微元高度；CD,tow为塔筒阻力系数取值1.0；Anac为机舱截面积；CD,nac为机舱阻力系数取值1.0；轴向速度
Figure FDA0003422487920000034
Figure FDA0003422487920000035
是轴向法向量，
Figure FDA0003422487920000036
是叶素点处的速度。In the formula, u tow is the incoming wind speed of the micro-element center of the tower; ρ is the air density; d tow is the diameter of the circular section of the tower's micro-element center; dh is the height of the tower's micro-element; C D, tow is the tower Drum resistance coefficient is 1.0; A nac is the cross-sectional area of the engine room; C D, nac is the resistance coefficient of the engine room, which is 1.0; axial velocity
Figure FDA0003422487920000034
Figure FDA0003422487920000035
is the axial normal vector,
Figure FDA0003422487920000036
is the velocity at the leaf element point.
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CN115544667A (en) * 2022-10-31 2022-12-30 南京航空航天大学 An Equivalent Disk Method Based on Blade Momentum Source Coupled CFD
CN117436322A (en) * 2023-12-21 2024-01-23 浙江远算科技有限公司 Aeroelastic simulation method and medium for wind turbine blades based on blade element theory
CN118690687A (en) * 2024-08-23 2024-09-24 华南理工大学 A new calculation model method for fan engineering

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Publication number Priority date Publication date Assignee Title
CN115544667A (en) * 2022-10-31 2022-12-30 南京航空航天大学 An Equivalent Disk Method Based on Blade Momentum Source Coupled CFD
CN115544667B (en) * 2022-10-31 2024-05-10 南京航空航天大学 An equivalent disk method based on blade element momentum source coupled CFD
CN117436322A (en) * 2023-12-21 2024-01-23 浙江远算科技有限公司 Aeroelastic simulation method and medium for wind turbine blades based on blade element theory
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