CN116108574A - Pneumatic design method and model for floating wind power blade model - Google Patents
Pneumatic design method and model for floating wind power blade model Download PDFInfo
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Abstract
The invention provides a pneumatic design method of a floating wind power blade model, which comprises the following steps: s1: determining a relevant scale under a similarity criterion; s2: determining working condition parameters of a prototype and a model; s3: determining airfoil parameters of the blade model; s4: determining an optimization design criterion of a blade model; s5: carrying out optimization calculation according to the working condition parameters obtained in the step S2 and the wing profile information obtained in the step S3, wherein the design criterion of the optimization calculation is obtained in the step S4, the optimization parameters are regulated, and the pneumatic design of the blade model is carried out; s6: and obtaining the final design result of the model blade. The method is based on the similarity criteria that the optimal tip speed ratio mapping relation and the relative tip speed ratio change rate are the same, and the designed model blade can more accurately reflect the load and aerodynamic performance of the prototype unit under static and dynamic conditions.
Description
Technical Field
The invention belongs to the technical field of wind power blade model design, and particularly relates to a pneumatic design method and model of a floating wind power blade model.
Background
The model experiment is an important means for researching dynamic load and aerodynamic performance of the floating wind turbine generator, and mainly comprises the following steps: pool experiments, wind tunnel experiments, hardware in-loop tests, software in-loop tests and the like. The model unit is designed according to a specific similarity criterion to truly and accurately reflect the relevant performance of the prototype unit, so that the design of the large-scale floating offshore wind turbine unit is guided.
The existing floating wind power blade model is usually optimally designed by adopting a traditional thrust coefficient similarity criterion, the optimal variables are usually chord lengths and torsion angles distributed along the spanwise direction, and the optimal targets are usually that the thrust coefficient under a single working condition or multiple working conditions is kept similar to a prototype. When the designed traditional model operates under the optimal or rated working condition of the prototype unit, the traditional model is often at a higher tip speed ratio, and the attack angle of the wing profile of the blade is smaller. As a result, the thrust coefficient satisfies the good similarity, but the power coefficient is significantly reduced. In addition, the complex motion of the floating body platform is mutually interfered with the incoming flow, so that the unit is in a relative incoming flow speed state, meanwhile, the tip speed ratio also fluctuates based on the optimal or rated value of the prototype unit, and is also in a change state of the relative tip speed ratio, and the traditional model can not accurately reflect the dynamic thrust coefficient and the power coefficient of the prototype unit under the motion of the platform.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a pneumatic design method and a pneumatic design model for a floating wind turbine blade model, which are based on the similarity criteria that the optimal blade tip speed ratio mapping relation and the relative blade tip speed ratio change rate are the same, and solve the problems that the traditional thrust coefficient similarity criteria and the model design method in the prior art do not consider the aerodynamic performance similarity of the blade tip speed ratio and the airfoil attack angle of a unit under dynamic change, and the designed traditional model has low power coefficient and unsatisfied dynamic performance similarity.
In order to achieve the purpose, the invention provides the following technical scheme, namely a pneumatic design method for a floating wind power blade model, which comprises the following steps:
s1: determining a relevant scale under a similarity criterion;
s2: determining working condition parameters of a prototype and a model;
s3: determining airfoil parameters of the blade model;
s4: determining an optimization design criterion of a blade model;
s5: carrying out optimization calculation according to the working condition parameters obtained in the step S2 and the wing profile information obtained in the step S3, wherein the design criterion of the optimization calculation is obtained in the step S4, the optimization parameters are regulated, and the pneumatic design of the blade model is carried out;
s6: and obtaining the final design result of the model blade.
The pneumatic design method of the floating wind power blade model provided by the invention has the characteristics that the relevant scale in S1 comprises a length scale, a tip speed ratio scale, a speed scale, a rotating speed scale, a frequency scale, an amplitude scale and an inflow wind speed scale.
The pneumatic design method of the floating wind power blade model provided by the invention has the characteristics that prototype working condition parameters in the S2 comprise a rotation radius, a tower height, a wind speed, a rotating speed, a frequency, an amplitude, and a complete running curve of a thrust coefficient and a power coefficient which change statically along with a tip speed ratio and dynamically fluctuate along with time, and the working condition parameters of the model are obtained through calculation of a relevant scale of the S1.
The pneumatic design method of the floating wind power blade model provided by the invention also has the characteristics that the S3 comprises the following steps:
s3.1: selecting a low Reynolds number airfoil with good similarity to the airfoil aerodynamic performance of the prototype unit;
s3.2: calculating the lift resistance coefficient of the airfoil profile selected by S3.1 in a small range of attack angles, and expanding the lift resistance coefficient to an attack angle interval of +/-180 degrees;
s3.3: the wing profiles are distributed along the span direction of the blade, circular smooth transition is adopted in the root area of the blade, and wing profile information of the blade model is obtained.
The pneumatic design method of the floating wind power blade model provided by the invention also has the characteristics that the mathematical model of the optimization design criterion in S4 is as follows:
Min
F＝P 1 +P 2
S.t.
therein, F, P, C T 、C P And c and theta are respectively an objective function, a weight function, a thrust coefficient, a power coefficient, a chord length and a torsion angle, k, n, m and delta are respectively the number of the normalized weight coefficients and the power coefficient which are near the set optimal tip speed ratio, the number of the optimized variable chord length or torsion angle and the interval length near the optimal tip speed ratio, and subscripts opt, L and U respectively represent the optimal, lower limit and upper limit.
The pneumatic design method of the floating wind power blade model provided by the invention also has the characteristics that the weight function P comprises a weight function P 1 And weight function two P 2 ，
The first weight function is the absolute value of the difference between the thrust coefficient of the model unit and the thrust coefficient of the prototype unit after the optimal tip speed ratio mapping in the relative tip speed ratio fluctuation interval corresponding to the optimal tip speed ratio working condition and platform movement of the prototype unit, and the second weight function is the difference between the average value of the power coefficient and the Betz theoretical limit value of 0.593 near the optimal tip speed ratio of the model, and then the normalized weight coefficient of the two weight functions is multiplied.
Another object of the present invention is to provide a floating wind power blade model, the design method of which is the aerodynamic design method of the floating wind power blade model as described in any one of the foregoing.
The beneficial effects are that:
the pneumatic design method of the floating wind power blade model provided by the invention has the following beneficial effects compared with the blade model design method with similar thrust coefficient in the prior art based on the similarity criterion that the optimal blade tip speed ratio mapping relation and the relative blade tip speed ratio change rate are the same:
(1) Through the mapping of the optimal tip speed ratio relationship, the similarity can be ensured by the new blade model besides the thrust coefficient, and the power coefficient can also meet the approximation by adding a constant;
(2) Compared with the lower operation attack angle of the blade model under the similar design of the traditional thrust coefficient, the attack angle of the new blade model can be in a relatively normal operation state;
(3) Compared with a blade model under the traditional thrust coefficient similar design, the new blade model can keep dynamic performance which is more similar to a prototype under the platform motion determined by a new similarity criterion, wherein the dynamic performance comprises fluctuation of the thrust coefficient and the power coefficient, and dynamic stall and dynamic inflow performance;
(4) Compared with a blade model with similar design of the traditional thrust coefficient, the new blade model is more suitable for being used for evaluating dynamic load and aerodynamic performance of a unit in an experimental environment, and has important significance for guiding design and load evaluation of large-scale floating wind power equipment.
The model blade provided by the invention can more accurately reflect the load and the aerodynamic performance of the prototype unit under static and dynamic conditions.
Drawings
In order to more clearly illustrate the technical solutions of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a graph of chord length design results of a model designed by a pneumatic design method of a floating wind power blade model provided by an embodiment of the invention;
FIG. 2 is a diagram of the design result of the torsion angle of a model designed by the pneumatic design method of the floating wind power blade model provided by the embodiment of the invention;
FIG. 3 is a graph of the results of calculation of thrust coefficients of a model and prototype units designed by the aerodynamic design method according to the embodiment of the present invention;
FIG. 4 is a graph of power coefficient calculation results of a model and a prototype set designed by the pneumatic design method according to the embodiment of the present invention;
FIG. 5 is a graph showing thrust coefficient fluctuation of a model designed by an aerodynamic design method, a model designed by a traditional method and a prototype unit under planar motion according to an embodiment of the present invention;
FIG. 6 is a graph showing the power coefficient fluctuation of the model designed by the pneumatic design method, the model designed by the traditional method and the prototype set under the plane motion according to the embodiment of the invention.
Detailed Description
In order to make the technical means, creation characteristics, achievement purposes and effects achieved by the present invention easy to understand, the following embodiments specifically describe the flow separation control method based on the bionic concave-convex leading edge structure provided by the present invention with reference to the accompanying drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the drawings, are merely for convenience in describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
The terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art in a specific case.
The invention provides a pneumatic design method of a floating wind power blade model, which comprises the following steps:
s1: determining a relevant scale under a similarity criterion;
s2: determining working condition parameters of a prototype and a model;
s3: determining airfoil parameters of the blade model;
s4: determining an optimization design criterion of a blade model;
s5: carrying out optimization calculation according to the working condition parameters obtained in the step S2 and the wing profile information obtained in the step S3, wherein the design criterion of the optimization calculation is obtained in the step S4, the optimization parameters are regulated, and the pneumatic design of the blade model is carried out;
s6: and obtaining the final design result of the model blade.
In some embodiments, the relevant scales in S1 include a length scale, a tip speed ratio scale, a speed scale, a rotational speed scale, a frequency scale, an amplitude scale, and an inflow wind speed scale.
In some embodiments, the prototype working condition parameters in S2 include a rotation radius, a tower height, a wind speed, a rotation speed, a frequency, an amplitude, and an operation curve of a complete thrust coefficient and a complete power coefficient which change statically with a tip speed ratio and fluctuate dynamically with time, and the working condition parameters of the model are obtained by calculating the relevant scale of S1.
In some embodiments, the step S3 includes the following steps:
s3.1: selecting a low Reynolds number airfoil with good similarity to the airfoil aerodynamic performance of the prototype unit; wherein better similarity means that the aerodynamic performance curve has a good linear segment, the maximum lift-drag ratio is higher,
s3.2: calculating the lift resistance coefficient of the airfoil profile selected by S3.1 in a small range of attack angles, and expanding the lift resistance coefficient to an attack angle interval of +/-180 degrees;
s3.3: the wing profiles are distributed along the span direction of the blade, circular smooth transition is adopted in the root area of the blade, and wing profile information of the blade model is obtained.
In some embodiments, the mathematical model of the optimization design criteria in S4 is as follows:
Min
F＝P 1 +P 2
S.t.
therein, F, P, C T 、C P And c and theta are respectively an objective function, a weight function, a thrust coefficient, a power coefficient, a chord length and a torsion angle, k, n, m and delta are respectively the number of the normalized weight coefficients and the power coefficient which are near the set optimal tip speed ratio, the number of the optimized variable chord length or torsion angle and the interval length near the optimal tip speed ratio, and subscripts opt, L and U respectively represent the optimal, lower limit and upper limit.
In some embodiments, the weight function P includes a weight function P 1 And weight function two P 2 ，
The first weight function is the absolute value of the difference between the thrust coefficient of the model unit and the thrust coefficient of the prototype unit after the optimal tip speed ratio mapping in the relative tip speed ratio fluctuation interval corresponding to the optimal tip speed ratio working condition and platform movement of the prototype unit, and the second weight function is the difference between the average value of the power coefficient and the Betz theoretical limit value of 0.593 near the optimal tip speed ratio of the model, and then the normalized weight coefficient of the two weight functions is multiplied.
In some embodiments, a floating wind power blade model is provided, the design method of the model is the pneumatic design method of the floating wind power blade model.
Examples:
the NREL 5-MW unit is taken as a prototype, the design process and the design result of the whole blade model are given in detail, the prototype and the model unit are taken as a group of embodiments, the thrust and the power coefficients of the model unit under static and platform movement are calculated, and the model unit is compared with the blade model under the similar design of the traditional thrust coefficients.
The following gives the process of optimizing the design of the new blade model:
first, the relevant scale under the similarity criteria is determined. Three basic scales of length, tip speed ratio and speed are first determined as shown in equations 1, 2 and 3, and then the rotational speed scale can be calculated from the three basic scales as shown in equation 4. In addition, the dynamic performance of the unit is mainly caused by airfoil attack angle changes caused by relative tip speed ratio fluctuations. Thus, to ensure similar aerodynamic performance, particularly dynamic stall and dynamic inflow, the relative tip speed ratio change rates of the model and prototype should be the same as shown in equation 5. Therefore, the period scale of the platform motion is equal to the tip speed ratio scale, as shown in formula 6, and the frequency scale is equal to the reciprocal of the period scale, as shown in formula 7. The amplitude scale may then be determined from the frequency and speed scale as shown in equation 8.
Wherein lambda is (*) The L, TSR, V, omega, T, f and A are respectively length, tip speed ratio, speed, rotating speed, period, frequency and amplitude, R, U w U, t are radius of rotation, inflow wind speed, associated speed, time, subscripts p and m represent prototype and model, respectively.
And secondly, determining working condition parameters of the prototype and the model. The prototype unit is an NREL 5-MW unit, and parameters such as rotation radius, tower height, wind speed, rotation speed, frequency, amplitude and the like are known; in addition, the blade model has a complete running curve of static change of thrust and power coefficient along with the tip speed ratio and dynamic fluctuation along with time so as to compare the calculated results of the thrust and power coefficient of the blade model. The parameters of the model set are calculated by the relevant scale determined in the first step, and in the embodiment, the rotating radius of the model is 0.55m, and the value can be determined according to the actual experimental environment scale; the inflow wind speed of the model is 6.5m/s, and the value can be determined according to the optimal wind speed range of actual experimental wind making equipment; the optimal tip speed ratio of the model is 4.4, and the value is obtained by the reverse calculation of the optimal design result of the model; in addition, the rotation speed, the frequency and the amplitude of the motion and the like of the model are calculated by the relevant scale respectively.
And thirdly, determining airfoil information of the blade model. In the design of the floating wind power blade model, a single-wing type design, a double-wing type design or a multi-wing type design can be adopted. Among them, the low Reynolds number airfoils with better similarity to the aerodynamics of the prototype unit, such as NACA4412, AG01, AG04, SD7032, etc. are preferred. In this embodiment, a single wing design of NACA4412 is used. The lift-drag coefficient of NACA4412 airfoil over a small range of angles of attack is calculated and analyzed by Xfoil, rfoil or CFD methods, and is extended to an angle of attack interval of + -180 DEG by Airfoil Prep, and finally the airfoil is arranged along the spanwise direction of the blade, and a circular smooth transition is adopted at the root of the blade.
And fourthly, determining the optimization design criterion of the blade model. The optimization variables are chord lengths and torsion angles distributed along the spanwise direction, and the objective function is the minimum value of the sum of two weight functions comprehensively considering the similarity of thrust coefficients and the approximation of power coefficients. Wherein, the weight function one is: in the tip speed ratio interval of the prototype unit 6.3-9.3, the absolute value of the difference between the model unit thrust coefficient and the prototype unit thrust coefficient after the optimal tip speed ratio mapping; the weight function II is as follows: and in the 3.4-5.4 interval near the optimal tip speed ratio of 4.4 of the model, the difference between the average value of the power coefficient and the Betz theoretical limit value of 0.593 is multiplied by a weight coefficient value which is normalized by considering two weight functions of 0.04. At the same time, the values of chord length and torsion angle should meet the upper and lower limits set. Therefore, after the thrust coefficient curve of the blade model is mapped by the optimal tip speed ratio relationship, the thrust coefficient curve and the prototype unit are required to be similar, and after the power coefficient curve is mapped, the thrust coefficient curve and the prototype unit are expected to be kept in a similar shape. In addition, compared with a model under the traditional thrust coefficient similar design, the blade model operates in a state with a relatively optimal attack angle, and the dynamic aerodynamic performance of the blade model is better matched. The mathematical model of the overall optimization design criteria is as follows:
Min
F＝P 1 +P 2
S.t.
therein, F, P, C T 、C P And c and theta are respectively an optimization target, a weight function, a thrust coefficient, a power coefficient, a chord length and a torsion angle, n is the number of the power coefficient in a 3.4-5.4 interval near the optimal tip speed ratio, and subscripts opt, L and U respectively represent an optimal, a lower limit and an upper limit.
And fifthly, selecting an optimization algorithm to design the blade. In the embodiment, a genetic algorithm is selected to carry out blade optimization design, model parameters and wing profile information determined in the second step and the third step are input, the optimization design criterion determined in the fourth step is set, and the optimization parameters are adjusted to carry out the pneumatic design process of the blade model.
And sixthly, obtaining the final design result of the model blade. And after the fifth step of optimization is finished, obtaining the design result of the chord length and the torsion angle of the model blade distributed along the spanwise direction, as shown in figures 1-2. The model blade can accurately reproduce the dynamic thrust coefficient and the power coefficient performance of the prototype unit under the static and platform motion.
The calculation results of the thrust coefficient and the power coefficient of the blade model designed in the embodiment under static state are shown in fig. 3-4, wherein gray lines represent the NREL 5-MW prototype unit, black lines represent the new blade model and the thrust coefficient and power coefficient curves thereof after being linearly mapped by the tip speed ratio scale 1.716, and gray bands are corresponding intervals of the mapping relation. It can be seen that the thrust coefficient of the blade model maintains high similarity with the prototype after mapping, and the power coefficient can also meet a better approximation after mapping and upward translation. The pneumatic design method for the floating wind power blade model provided by the invention is verified to enable the model design result and the prototype to meet the similarity of static thrust coefficient and power coefficient.
Fig. 5-6 show the power coefficient and thrust coefficient fluctuations over time of the new blade model designed in this example in a periodic sinusoidal pitching motion, and compared to the blade model in a similar design to the NREL 5-MW prototype and conventional thrust coefficient, wherein the gray dotted line, black dotted circle line, and black triangle line represent the NREL 5-MW machine set, conventional blade model, and new blade model, respectively. In thrust coefficient fluctuations, the conventional blade model shows a large deviation in the first half period compared to the prototype, while the new blade model remains highly similar throughout the heave period. In power coefficient fluctuations, the traditional blade model drops sharply in the first half of the cycle, even negative values occur, while the new blade model curve can be approximated by translating upward to the prototype. The pneumatic design method for the floating wind power blade model provided by the invention can further prove that the dynamic thrust coefficient and power coefficient similarity can be met between the model design result and the prototype.
In the floating wind power blade model designed by the embodiment, under the working conditions of the optimal tip speed ratio of the prototype unit of 7.55 and the relative tip speed ratio of 6.3-9.3 caused by platform movement, the thrust coefficient is linearly mapped by the tip speed ratio scale 1.716, and the power coefficient is linearly mapped by the tip speed ratio scale 1.716 and increased by a constant of 0.145, so that the power coefficient can be equivalent to the static and dynamic performances of the prototype unit. The corresponding relation of the working conditions between the model and the prototype is shown in the following formula:
C Tp (TSR m ×1.716)＝C Tm (TSR m ) (10)
C Pp (TSR m ×1.716)＝C Pm (TSR m )+0.145 (11)
the foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention. The foregoing is merely a preferred embodiment of the present invention, and it should be noted that it will be apparent to those skilled in the art that modifications and variations can be made without departing from the technical principles of the present invention, and these modifications and variations should also be regarded as the scope of the invention.
Claims (7)
1. The pneumatic design method of the floating wind power blade model is characterized by comprising the following steps of:
s1: determining a relevant scale under a similarity criterion;
s2: determining working condition parameters of a prototype and a model;
s3: determining airfoil parameters of the blade model;
s4: determining an optimization design criterion of a blade model;
s5: carrying out optimization calculation according to the working condition parameters obtained in the step S2 and the wing profile information obtained in the step S3, wherein the design criterion of the optimization calculation is obtained in the step S4, the optimization parameters are regulated, and the pneumatic design of the blade model is carried out;
s6: and obtaining the final design result of the model blade.
2. The method according to claim 1, wherein the relevant scales in S1 include a length scale, a tip speed ratio scale, a speed scale, a rotation speed scale, a frequency scale, an amplitude scale, and an inflow wind speed scale.
3. The method according to claim 1, wherein the prototype working condition parameters in S2 include a rotation radius, a tower height, a wind speed, a rotation speed, a frequency, an amplitude, and an operation curve of complete thrust coefficient and power coefficient with static change of a tip speed ratio and dynamic fluctuation with time,
the working condition parameters of the model are obtained through calculation of the relevant scale of the S1.
4. The method for aerodynamic design of a floating wind turbine blade model of claim 1, wherein S3 comprises the steps of:
s3.1: selecting a low Reynolds number airfoil with good aerodynamic performance at a low Reynolds number;
s3.2: calculating the lift resistance coefficient of the airfoil profile selected by S3.1 in a small range of attack angles, and expanding the lift resistance coefficient to an attack angle interval of +/-180 degrees;
s3.3: the wing profiles are distributed along the span direction of the blade, circular smooth transition is adopted in the root area of the blade, and wing profile information of the blade model is obtained.
5. The method for aerodynamic design of a floating wind turbine blade model according to claim 1, characterized in that the mathematical model of the optimization design criteria in S4 is as follows:
Min
F＝P 1 +P 2
S.t.
therein, F, P, C T 、C P And c and theta are respectively an objective function, a weight function, a thrust coefficient, a power coefficient, a chord length and a torsion angle, k, n, m and delta are respectively the number of the normalized weight coefficients and the power coefficient which are near the set optimal tip speed ratio, the number of the optimized variable chord length or torsion angle and the interval length near the optimal tip speed ratio, and subscripts opt, L and U respectively represent the optimal, lower limit and upper limit.
6. The method for aerodynamic design of a floating wind turbine blade model of claim 5, wherein the weight function P comprises a weight function P 1 And weight function two P 2 ，
The first weight function is the absolute value of the difference between the thrust coefficient of the model unit and the thrust coefficient of the prototype unit after the optimal tip speed ratio mapping in the relative tip speed ratio fluctuation interval corresponding to the optimal tip speed ratio working condition and platform movement of the prototype unit,
and the second weight function is the difference between the average value of the power coefficient and the Betz theoretical limit value of 0.593 near the optimal tip speed ratio of the model, and then the normalized weight coefficient of the two weight functions is multiplied.
7. A floating wind power blade model, characterized in that the design method of the model is a pneumatic design method of the floating wind power blade model according to any one of claims 1-6.
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| CN117195576A (en) * | 2023-09-18 | 2023-12-08 | 上海勘测设计研究院有限公司 | Floating type offshore wind power system integrated design verification method |
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| US20060140760A1 (en) * | 2004-12-23 | 2006-06-29 | Saddoughi Seyed G | Active flow modifications on wind turbine blades |
| CN113742861A (en) * | 2021-08-24 | 2021-12-03 | 重庆大学 | Blade model optimization design method suitable for wind tunnel test of wind driven generator |
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| CN117195576A (en) * | 2023-09-18 | 2023-12-08 | 上海勘测设计研究院有限公司 | Floating type offshore wind power system integrated design verification method |
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