CN117634046B - Blade pitch-changing and flap cooperative control load-reducing method based on CFD numerical simulation - Google Patents
Blade pitch-changing and flap cooperative control load-reducing method based on CFD numerical simulation Download PDFInfo
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Abstract
The invention discloses a method for cooperatively controlling load reduction of a variable pitch and a flap of a blade based on CFD numerical simulation, which comprises the following steps: 1) Determining a pitch angle, a tail edge length of a tail edge flap and a deflection angle; 2) Geometric modeling of a two-dimensional airfoil of a blade; 3) Calculating grid division of the drainage basin; 4) Setting boundary conditions and calculation methods; 5) Selecting load reduction performance analysis parameters; 6) And (5) carrying out load reduction effect evaluation by cooperative control of the variable pitch and the trailing edge flap. The invention solves the problems of low response speed, weakening of control effect and the like of the independent variable pitch of the wind turbine under the actual working condition, obviously improves the load reduction performance of the wind turbine blade, provides an optimized control scheme aiming at the variation trend of the wing profile load of the blade under the cooperative control of the variable pitch and the trailing edge flap, and provides a basis for further realizing the design and research of the load reduction of the wind turbine blade under the cooperative control of the variable pitch and the trailing edge flap.
Description
Technical Field
The invention relates to the technical field of blades of new energy wind generating sets, in particular to a method for cooperatively controlling load reduction of variable pitch blades and flaps based on CFD numerical simulation.
Background
The aerodynamic properties of the blades affect the wind energy conversion rate and also determine the economy of the wind turbine. The good blade design can lead the wing profile of the blade to have better aerodynamic performance and good structure and manufacturing process, so that the wind driven generator can stably run and has higher power output.
Currently, wind power generation technology is mature, and single-machine capacity of a wind turbine is larger and larger, so that the diameter size of a wind wheel of the wind turbine is increased. With the large-scale development of flexible blades, the problem of fatigue load generated by the wind turbine blade under the coupling actions of complex aerodynamic force, inertial force, elastic force and the like is not ignored. These problems can lead to breakage of the wind turbine blade or damage of the wind turbine, seriously affect the safe service life of the wind turbine, and cause huge economic loss. Therefore, the method for researching the load problem of the wind turbine has important significance in the aspects of prolonging the service life of the wind turbine and ensuring the safe and stable operation of the wind turbine.
The pitch control is a mature load reduction control technology by controlling the attack angle of the blade to change the aerodynamic characteristics. However, as the blades become larger, the pitch control technology has the limitations of slow response speed, reduced control effect, and the like. Trailing edge flap control is considered an effective complementary technique in the face of limitations of pitch control. Trailing edge flaps are a fluid control technique. The trailing edge flap changes the structural characteristics of the blade airfoil through the change of the length and deflection angle of the trailing edge. When air flows through, the distribution of the flow field near the wing slits and the wing flaps is changed, and the pressure distribution on the surface of the wing profile is affected. The pressure difference across the airfoil surface is the source of airfoil aerodynamic forces, i.e., changes in pressure distribution cause changes in airfoil aerodynamic characteristics. The load of the wind turbine can be effectively reduced by the cooperative control of the pitch control and the trailing edge flap.
Disclosure of Invention
The invention aims to: the limitations of low response speed, reduced control effect and the like of the independent variable pitch of the wind turbine under the actual working condition are overcome, the load reduction performance of the wind turbine blade under the cooperative control of the variable pitch and the trailing edge flap is explored, and the basis is provided for further realizing load reduction design and research through the cooperative control of the variable pitch and the trailing edge flap.
The technical scheme is as follows: the invention discloses a method for cooperatively controlling load shedding of a variable pitch and a flap of a blade based on CFD numerical simulation, which comprises the following steps:
s1: determination of a pitch angle alpha of a blade of a wind generating set, a tail edge length nC of a tail edge flap and a deflection angle beta: in simulation, the change of the pitch angle alpha is realized by controlling the wind direction of simulated inflow wind so as to change the attack angle, and the change of the tail edge flap length nC and the deflection angle beta is realized by changing the structure of the wing-shaped tail edge flap during modeling;
S2: geometric modeling of a two-dimensional airfoil of a blade: establishing a geometric model of a two-dimensional blade airfoil according to aerodynamic parameters of the blade tip airfoil of the large wind generating set and the length nC and deflection angle beta of the trailing edge flap determined in the step S1;
s3: grid division of a two-dimensional airfoil calculation basin: grid division is carried out on the basis of the geometric model of the two-dimensional blade airfoil in the step S2, cross grid refinement treatment is carried out on the airfoil by taking a rotating shaft as a center, and structural grid topology is adopted as a whole;
s4: boundary conditions and calculation method are set: setting boundary conditions according to rated working conditions of operation of a wind turbine blade, adopting an SST k-omega turbulence model, setting the boundary conditions as a speed inlet and an automatic outflow outlet, wherein the speed inlet changes wind direction by setting component sizes of wind speed in x and y directions, so that change of attack angle alpha is realized, taking the gravity action in the vertical direction into consideration, starting steady-state flow, adopting a finite volume method, adopting a SIMPLEC solution pressure-speed coupling method, and adopting a first-order windward format to carry out dispersion on a control equation;
S5: selection of load shedding performance analysis parameters: the load born by the wing section is divided into a flapping bending moment load M x and a shimmy bending moment load M y, and the normal force coefficient C N and the tangential force coefficient C T respectively correspond to the following relation: m x＝0.5CNρAv2,My＝0.5CTρAv2, wherein ρ is the air density; a is the airfoil area; v is wind speed; when the length of the trailing edge flap is fixed through simulation, the normal force coefficient C N and the tangential force coefficient C T of the airfoil under the deflection angle beta and the attack angle alpha are changed, and parameters with obvious change are selected as load reduction performance analysis objects;
S6: and (3) carrying out load reduction effect evaluation by cooperative control of variable pitch and trailing edge flaps: and (3) adopting a single variable method to simulate and obtain the variation conditions of the selected load reduction analysis parameters under different attack angles alpha, tail edge lengths nC and deflection angles beta, and comprehensively evaluating the load reduction effect realized by the cooperative control of the variable pitch and the tail edge flaps according to the results.
Further, step S1 selects a pitch angle, i.e., a change range of attack angle alpha, of 0-20 degrees, a change range of tail edge length nC of 0.1-0.3C, and a change range of deflection angle beta of-15 degrees.
Further, when grid division is performed in step S3, the first layer of the grid thickness of the airfoil is set to be 10 -5 m, so that the first layer of the grid thickness meets the condition of y + ≡1.
Further, when the load reduction performance analysis parameter is selected in step S5, simulation simulates that when the trailing edge flap length nC is fixed, the airfoil profile changes in normal force coefficient C N and tangential force coefficient C T under different deflection angles β and different attack angles α, wherein the normal force coefficient C N changes obviously, and the tangential force coefficient C T does not change basically, so that the main influence direction of each influence factor on the load is the waving direction, and therefore, the normal force coefficient C N is selected as the load reduction performance analysis parameter.
Further, the step S6 specifically includes the following sub-steps:
S61: influence of tail edge flap length nC on blade airfoil load shedding performance;
When the deflection angle beta is fixed, under the same attack angle alpha, the original airfoil C N is the largest, and the longer the tail edge flap length is, the smaller the C N value is;
s62: the influence of the deflection angle beta of the tail edge flap on the load reduction performance of the wing profile of the blade;
When the tail edge length nC is fixed, under the same attack angle alpha, the C N value is increased along with the increase of the deflection angle, and the increasing trend is gradually reduced along with the increase of the pitch angle alpha;
s63: the influence of the attack angle alpha on the load reduction performance of the blade airfoil;
When the tail edge length nC is fixed, under the same deflection angle beta, the C N value presents bell-shaped change along with the attack angle alpha, and reaches the maximum value at the critical attack angle, namely load reduction can be realized by adjusting the increase or decrease of the attack angle near the critical attack angle, and the larger the deflection angle beta is, the smaller the corresponding attack angle alpha of the maximum value of C N is; thus, the deflection angle β affects the airfoil critical angle of attack variation, and the corresponding critical angle of attack position advances as the deflection angle β increases.
S64: analyzing the influence trend of each factor on the load reduction performance of the blade airfoil;
When the tail edge length nC is fixed, the increasing trend of the C N value gradually slows down along with the increase of the attack angle alpha of 10-20 degrees and the deflection angle beta; analysis shows that if the deflection angle beta of the wing section is 0-15 degrees and the attack angle alpha is 10-20 degrees, the control of the trailing edge flap should be selected preferentially; and the load reduction is realized under other working conditions, and the pitch control should be selected preferentially.
The beneficial effects are that: compared with the prior art, the method for cooperatively controlling the load reduction of the variable pitch and the flap of the blade based on CFD numerical simulation has the following beneficial effects:
1) The invention overcomes the limitation of independent pitch control, and adds an effective load reduction technology of trailing edge flap control on the basis of pitch control. And obtaining the change rule of the airfoil load under each factor according to the load change conditions under different pitch angles alpha, tail edge lengths nC and deflection angles beta. The result shows that the larger the tail edge length nC is, the smaller the deflection angle beta is, the farther the pitch angle alpha is from the critical attack angle, and the better the load shedding performance is. The deflection angle beta affects the critical angle of attack, and its increase results in an advance in the critical angle of attack position. The load reduction can be more effectively realized by the cooperative control of the tail edge flap and the variable pitch.
2) According to the change trend of the load under the deflection angle beta and the attack angle alpha, the wing profile under the cooperative control of the trailing edge flap and the pitch control is required to be preferentially selected when the deflection angle is 0-15 degrees and the attack angle is 10-20 degrees in order to realize the rapid load reduction, and the pitch control is required to be preferentially selected under other conditions.
3) The conclusion of the invention is beneficial to the optimization design of the wind turbine blade under the cooperative control of the variable pitch and the tail edge flap in the follow-up experiment and the actual production.
Drawings
FIG. 1 is a schematic illustration of a geometric model of a two-dimensional blade airfoil;
FIG. 2 is a diagram of a computational drainage basin mesh topology;
FIG. 3 is a graph of load performance analysis parameter C N、CT as a function of pitch angle versus yaw angle;
FIG. 4 is a graph of normal force coefficient C N as a function of trailing edge length nC;
FIG. 5 is a graph of normal force coefficient C N as a function of deflection angle β;
fig. 6 is a graph of normal force coefficient C N as a function of angle of attack α.
Detailed Description
The specific embodiment discloses a method for cooperatively controlling down load of a variable pitch and trailing edge flap of a blade based on CFD numerical simulation, which comprises the following steps:
S1: determination of a pitch angle alpha of a blade of a wind generating set, a tail edge length nC of a tail edge flap and a deflection angle beta:
the pitch angle alpha is controlled by the included angle between the wing profile and the wind direction, namely the attack angle, under the actual condition, so that aerodynamic characteristics such as the rising resistance of the wing profile are changed to realize load reduction; the trailing edge length nC and the deflection angle β of the trailing edge flap actually achieve load shedding by changing the airfoil structure such that it causes a change in aerodynamic properties as air flows through. Therefore, in the simulation, the change of the pitch angle is realized by controlling the wind direction of simulated inflow wind so as to change the attack angle, and the change of the length and deflection angle of the trailing edge flap is realized by changing the structure of the airfoil trailing edge flap during modeling.
The range of the blade pitch angle alpha of the wind generating set is generally 0-90 degrees, but the stall phenomenon can be generated after the critical pitch angle is reached due to the pitch angle, so that the power of the wind generating set is greatly reduced, the accuracy and the precision of a result of simulation software under the stall condition are insufficient, the aerodynamic characteristic problem is generally focused near the critical pitch angle, and the maximum value of the pitch angle finally selected is near the critical pitch angle. In practical situations, the longer the tail edge length is, the larger the deflection angle is, the larger the stress of the connecting member between the tail edge and the front airfoil is, and the control difficulty is increased. Because the pitch angle alpha, the tail edge length nC and the deflection angle beta are limited due to the factors such as material structure problems, control technology and the like in actual situations, according to the research results of a large number of documents, the change range of the pitch angle alpha, namely the attack angle alpha, is finally selected to be 0-20 degrees, the change range of the tail edge length nC is 0.1-0.3 degrees, and the change range of the deflection angle beta is-15 degrees.
S2: geometric modeling of a two-dimensional airfoil of a blade:
Since the trailing edge flaps of the blades are typically mounted close to the blade tips, the airfoil profile at the tip of the wind turbine blade is selected for investigation. In addition, the split trailing edge flap can be divided into a straight slot and a curved slot according to the shape of the slot, and in practical situations, the joint of the slot is mostly the curved slot, so that the curved slot is selected. And establishing a geometric model of the two-dimensional blade airfoil according to aerodynamic parameters of the blade tip airfoil of the large wind generating set, parameters of the length nC of the tail edge flap, the deflection angle beta and the like.
S3: grid division of a two-dimensional airfoil calculation basin:
And (3) carrying out grid division on the basis of the geometric model of the two-dimensional blade airfoil in the step (S2). In order to capture the flow state of the watershed near and downstream of the airfoil, the airfoil is subjected to cross grid refinement treatment by taking a rotating shaft as a center. The whole adopts a structural grid topology. The first layer of mesh of the airfoil is set to a thickness of 10 -5 m so that it meets the condition y + ≡1.
S4: boundary conditions and calculation method are set:
And setting boundary conditions according to the rated working conditions of the operation of the wind turbine blade. According to the research results of a large number of documents, the SST k-omega turbulence model is better in calculating the trailing edge flap, so that the SST k-omega turbulence model is adopted. The boundary condition is set as a speed inlet and an automatic outflow outlet, wherein the speed inlet changes the wind direction by setting the component magnitude of the wind speed in the x and y directions, so that the change of the attack angle alpha is realized. The gravity action in the vertical direction is considered, steady-state flow is started, a finite volume method is adopted, a simple EC (computer aided design) solution pressure and speed coupling method is utilized, and a control equation is discretized by adopting a first-order windward format.
S5: selecting load reduction performance analysis parameters;
The load born by the wing profile can be divided into a flapping bending moment load M x and a shimmy bending moment load M y, and the normal force coefficient C N and the tangential force coefficient C T respectively correspond to the load. The relation is as follows:
Mx＝0.5CNρAv2
My＝0.5CTρAv2
wherein ρ is the air density; a is the airfoil area; v is wind speed.
Simulation simulates the variation of the normal force coefficient C N and tangential force coefficient C T of the airfoil at deflection angle beta and angle of attack alpha when the trailing edge flap length is fixed. Wherein the normal force coefficient C N varies significantly and the tangential force coefficient C T does not substantially vary. The main direction of influence of each influence factor on the load is the waving direction. Therefore, the normal force coefficient C N is selected as the load-shedding performance analysis parameter.
S6: the load reduction effect evaluation is carried out by cooperative control of the variable pitch and the trailing edge flap;
and adopting a single variable method to simulate and obtain the change conditions of the selected load reduction analysis parameters under different attack angles alpha, tail edge lengths nC and deflection angles beta. And comprehensively evaluating the effect of realizing load reduction by cooperatively controlling the variable pitch and the tail edge flap according to the result.
S61: influence of tail edge flap length nC on blade airfoil load shedding performance;
When the deflection angle β is fixed, at the same angle of attack α, where the original airfoil C N value is the largest, the longer the trailing edge flap length the smaller the C N value. Therefore, the tail edge flap structure has obvious load reducing effect, and the longer the flap length is, the better the load reducing performance is. Wherein, the standard deviation of the difference between the C N value and the original airfoil at the tail edge lengths of 0.1C, 0.2C and 0.3C is about 18.1%, 20.1% and 25.5% respectively.
S62: the influence of the deflection angle beta of the tail edge flap on the load reduction performance of the wing profile of the blade;
When the trailing edge length nC is fixed, the value of C N increases with increasing deflection angle at the same angle of attack α, but the increasing trend gradually decreases with increasing pitch angle α. This means that the smaller the deflection angle β is, the better the load shedding characteristic is. Wherein the standard deviation of the difference between the C N value and the 0 deflection angle at-5 DEG, -10 DEG and-15 DEG deflection angles is about 5.0%, 10.2% and 15.3% respectively.
S63: the influence of the attack angle alpha on the load reduction performance of the blade airfoil;
When the tail edge length nC is fixed, under the same deflection angle beta, the value of C N shows a bell-shaped change along with the attack angle alpha, and reaches the maximum value at the critical attack angle, namely, the load reduction can be realized by adjusting the increase or decrease of the attack angle near the critical attack angle. Wherein the larger the deflection angle beta, the smaller the maximum value of C N corresponds to the angle of attack alpha. It is thus shown that the deflection angle β affects the airfoil critical angle of attack variation, and that the corresponding critical angle of attack position advances as the deflection angle β increases.
S64: analyzing the influence trend of each factor on the load reduction performance of the blade airfoil;
When the tail edge length nC is fixed, the change trend of the value of C N under the deflection angle β and the attack angle α is different, and the increase trend of the value of C N gradually slows down as the attack angle α is 10-20 ° and the deflection angle β increases. Analysis shows that if the deflection angle beta of the wing section is reduced when the deflection angle beta is 0-15 degrees and the attack angle alpha is 10-20 degrees, the deflection angle beta is controlled to be reduced by the trailing edge flap, and then the pitch control is carried out to reduce the attack angle alpha, so that the condition that the waving bending moment load M x caused by the preferential pitch is increased can be prevented; and under other working conditions, the load reduction is realized, the pitch control is preferably selected to reduce the attack angle alpha, and the load reduction effect is obviously better than that of trailing edge flap control which reduces the deflection angle beta.
In conclusion, the load reduction can be effectively realized through the cooperative control of the trailing edge flap and the variable pitch.
Claims (5)
1. The method for cooperatively controlling the load reduction of the variable pitch and the flap of the blade based on CFD numerical simulation is characterized by comprising the following steps of:
s1: determination of a pitch angle alpha of a blade of a wind generating set, a tail edge length nC of a tail edge flap and a deflection angle beta: in simulation, the change of the pitch angle alpha is realized by controlling the wind direction of simulated inflow wind so as to change the attack angle, and the change of the tail edge flap length nC and the deflection angle beta is realized by changing the structure of the wing-shaped tail edge flap during modeling;
S2: geometric modeling of a two-dimensional airfoil of a blade: establishing a geometric model of a two-dimensional blade airfoil according to aerodynamic parameters of the blade tip airfoil of the large wind generating set and the length nC and deflection angle beta of the trailing edge flap determined in the step S1;
s3: grid division of a two-dimensional airfoil calculation basin: grid division is carried out on the basis of the geometric model of the two-dimensional blade airfoil in the step S2, cross grid refinement treatment is carried out on the airfoil by taking a rotating shaft as a center, and structural grid topology is adopted as a whole;
s4: boundary conditions and calculation method are set: setting boundary conditions according to rated working conditions of operation of a wind turbine blade, adopting an SST k-omega turbulence model, setting the boundary conditions as a speed inlet and an automatic outflow outlet, wherein the speed inlet changes wind direction by setting component sizes of wind speed in x and y directions, so that change of attack angle alpha is realized, taking the gravity action in the vertical direction into consideration, starting steady-state flow, adopting a finite volume method, adopting a SIMPLEC solution pressure-speed coupling method, and adopting a first-order windward format to carry out dispersion on a control equation;
S5: selection of load shedding performance analysis parameters: the load born by the wing section is divided into a flapping bending moment load M x and a shimmy bending moment load M y, and the normal force coefficient C N and the tangential force coefficient C T respectively correspond to the following relation: m x＝0.5CNρAv2,My＝0.5CTρAv2, wherein ρ is the air density; a is the airfoil area; v is wind speed; when the length of the trailing edge flap is fixed through simulation, the normal force coefficient C N and the tangential force coefficient C T of the airfoil under the deflection angle beta and the attack angle alpha are changed, and parameters with obvious change are selected as load reduction performance analysis objects;
S6: and (3) carrying out load reduction effect evaluation by cooperative control of variable pitch and trailing edge flaps: and (3) adopting a single variable method to simulate and obtain the variation conditions of the selected load reduction analysis parameters under different attack angles alpha, tail edge lengths nC and deflection angles beta, and comprehensively evaluating the load reduction effect realized by the cooperative control of the variable pitch and the tail edge flaps according to the results.
2. The method for cooperatively controlling load shedding of a blade pitch and flap based on CFD numerical simulation according to claim 1, wherein the step S1 is to select a pitch angle, namely, a change range of an attack angle alpha, to be 0-20 degrees, a change range of a tail edge length nC to be 0.1-0.3 degrees, and a change range of a deflection angle beta to be-15 degrees.
3. The method for cooperatively controlling and reducing load of a blade pitch and flap based on CFD numerical simulation according to claim 1, wherein when grid division is performed in step S3, the thickness of the first layer of grid of the airfoil is set to be 10 -5 m, so that the first layer of grid meets the condition of y + approximately equal to 1.
4. The method for cooperatively controlling load shedding of a blade pitch and flap based on CFD numerical simulation according to claim 1, wherein when the load shedding performance analysis parameter is selected in step S5, simulation simulates the changes of a normal force coefficient C N and a tangential force coefficient C T of an airfoil under different deflection angles beta and different attack angles alpha when the tail edge flap length nC is fixed, wherein the normal force coefficient C N changes obviously, and the tangential force coefficient C T does not change basically, so that the main influence direction of each influence factor on the load is the waving direction, and the normal force coefficient C N is selected as the load shedding performance analysis parameter.
5. The method for cooperatively controlling load shedding of a blade pitch and flap based on CFD numerical simulation of claim 1, wherein step S6 specifically comprises the following sub-steps:
S61: influence of tail edge flap length nC on blade airfoil load shedding performance;
When the deflection angle beta is fixed, under the same attack angle alpha, the original airfoil C N is the largest, and the longer the tail edge flap length is, the smaller the C N value is;
s62: the influence of the deflection angle beta of the tail edge flap on the load reduction performance of the wing profile of the blade;
When the tail edge length nC is fixed, under the same attack angle alpha, the C N value is increased along with the increase of the deflection angle, and the increasing trend is gradually reduced along with the increase of the pitch angle alpha;
s63: the influence of the attack angle alpha on the load reduction performance of the blade airfoil;
When the tail edge length nC is fixed, under the same deflection angle beta, the C N value presents bell-shaped change along with the attack angle alpha, and reaches the maximum value at the critical attack angle, namely load reduction can be realized by adjusting the increase or decrease of the attack angle near the critical attack angle; the deflection angle beta affects the critical attack angle change of the airfoil, and the critical attack angle position moves forward along with the increase of the deflection angle beta;
S64: analyzing the influence trend of each factor on the load reduction performance of the blade airfoil;
When the tail edge length nC is fixed, the increasing trend of the C N value gradually slows down along with the increase of the attack angle alpha of 10-20 degrees and the deflection angle beta, so that the blade airfoil realizes load reduction under different working conditions, and different priority control methods are needed to be selected.
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| CN107559143A (en) * | 2017-07-27 | 2018-01-09 | 华北电力大学 | A kind of large scale wind power machine trailing edge flaps structural parameters optimizing and multiple target wing flap optimal control method |
| EP3517773A1 (en) * | 2018-01-29 | 2019-07-31 | Siemens Gamesa Renewable Energy A/S | Trailing edge assembly |
| 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 |
| CN114154270A (en) * | 2021-12-08 | 2022-03-08 | 华能湖北新能源有限责任公司 | Design method for power-increasing trailing edge flap of blade |
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