CN116718343A - Test device and method for measuring aerodynamic characteristics of scaled wind power blade under rotation working condition - Google Patents
Test device and method for measuring aerodynamic characteristics of scaled wind power blade under rotation working condition Download PDFInfo
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Abstract
The invention discloses a test device and a method for measuring aerodynamic characteristics of a scaled wind power blade under a rotating working condition, which adopt the scaled wind power blade, an airflow probe, a surface pressure measuring hole, a six-component balance, a rotating speed torque sensor and a data acquisition and analysis device, wherein the airflow probe directly measures a relative inflow speed vector, and the lift ring induction speed of the blade needs to be removed. And simultaneously, an aerodynamic characteristic and operation characteristic analysis method is provided according to the data calculation result.
Description
Technical Field
The invention belongs to the technical field of aerodynamics of wind power blades, relates to a method and a device for measuring aerodynamic parameters, and particularly relates to a test device and a method for measuring aerodynamic characteristics of scaled wind power blades under a rotating working condition, which can effectively solve the technical problems of aerodynamic characteristics and aerodynamic forces of the scaled wind power blades including blade aerodynamic attack angles and the like measured under a wind tunnel environment.
Background
The wind power blade is an executive component of a wind wheel in a wind generating set and is used for capturing wind energy. The working environment of the wind turbine generator is severe, the wind turbine blades are used as important energy conversion components, the design and the manufacture of the wind turbine generator directly influence the operation efficiency and the reliability of the wind turbine generator, and the aerodynamic performance of the wind turbine generator determines the wind energy utilization efficiency (power coefficient) of the wind turbine generator. Therefore, the research on the dynamic performance and the operation characteristic of the wind power blade can promote the optimal design of the wind power blade and improve the power generation efficiency of the wind turbine generator. The wind power blade is formed by stacking wing sections along the span direction of the blade according to certain torsion angle, chord length and thickness distribution, and the key parameter for evaluating the aerodynamic performance of the wing sections is attack angle and aerodynamic force.
The dynamic aerodynamic characteristics of the rotating blades in the wind tunnel environment are not well verified and evaluated at present, mainly because the complexity of the rotating effect (the dynamic aerodynamic characteristics of the rotating blades need to be considered in the wind tunnel environment, including centrifugal force, coriolis force and the like), the limitation of the testing equipment (the calculation and simulation of the effects are very complex, high-precision numerical simulation methods and calculation resources are needed), the lack of verification of the real environment (the aerodynamic characteristics of the wind blades are evaluated, the test data in the wind tunnel only cannot fully represent the situation in the real wind field environment, the real wind field comprises different factors such as wind speed, wind direction, turbulence intensity and the like, and the influence of the factors on the aerodynamic characteristics of the blades is great, so that the test room data and the real wind field data are combined to obtain accurate evaluation results, the limitation of the testing equipment (the current wind tunnel and testing equipment cannot fully meet the testing requirements of the rotating blades, such as the requirement of higher measurement precision and the larger testing range and the like) is also caused, the limitation of the dynamic aerodynamic characteristics of the rotating blades in the environment exists.
The induction factor in the rotation process of the wind power blade is an unknown quantity closely related to the working condition, the induction factor describes the influence of vortex generated by the rotation blade on surrounding airflow, has high complexity, cannot be directly measured in the test process, and is mainly limited by the following factors: (1) The complex flow field environment is very complex in the process of rotating the wind power blade, and the generated aerodynamic flow field comprises factors such as airflows in different directions and sizes, centrifugal force of the rotating wings, coriolis force and the like, and the flow field generated under the combined action of the factors is difficult to accurately predict and measure; (2) The mutual influence of flow field parameters, the influence of a plurality of flow field parameters, such as air density, angular velocity, blade shape and the like, needs to be considered simultaneously in the calculation of the induction factors. These parameters are mutually influenced, and the influence under different conditions is different, so that the parameters are difficult to accurately separate; (3) The limitation of test equipment is that the current test equipment cannot directly measure the induction factors, but can only be obtained through calculation by other parameters, such as measuring parameters of aerodynamic moment, blade tip deflection and the like to estimate the induction factors. This method can obtain rough data, but the accuracy is not high. Because the induced factor cannot be directly measured in the test process, the aerodynamic attack angle of the blade cannot be obtained only through the incoming wind speed and the rotation speed of the blade (on one hand, vortex generated by the blade during rotation of the wind power blade affects surrounding airflow, so that the actual attack angle is different from the attack angle under the static condition. In summary, the difficulty in verifying and evaluating dynamic aerodynamic characteristics during rotation of wind power blades in a wind tunnel environment is that an effective measurement method for attack angle and aerodynamic force during rotation of wind power blades is lacking.
Disclosure of Invention
Object of the invention
In order to solve the technical problems in the prior art, based on the fact that the aerodynamic attack angle of a wind power blade is related to the wind speed of incoming flow far ahead of a wind wheel, the rotation speed of the wind wheel, the installation torsion angle, the axial direction and the circumferential direction induction factors, the airflow probe can measure the relative inflow speed vector, wherein the relative inflow speed vector comprises the incoming flow far ahead, the axial induction speed, the circumferential induction speed, the rotation speed of the wind wheel and the induction speed of lift ring quantity of the blade to the measured position, so that the effective attack angle of an airfoil can be obtained by removing the lift ring quantity induction speed from the relative inflow speed vector measured by the probe. When the wind condition is non-uniform incoming flow, a corresponding attack angle correction method is also provided. A plurality of aerodynamic characteristic parameters can be further calculated by means of an airflow probe, blade surface pressure measurement and the like, the aerodynamic characteristic parameters comprise, but are not limited to, attack angle, lift coefficient, resistance coefficient, lift-drag ratio and induction factor of the scaled blade, and the operating characteristic parameters comprise, but are not limited to, torque coefficient, thrust coefficient and power coefficient, so that the technical problem of measuring aerodynamic characteristics and aerodynamic force of the scaled wind power blade including blade aerodynamic attack angle and the like in a wind tunnel environment is solved.
(II) technical scheme
The technical scheme adopted by the invention for realizing the aim and solving the technical problems is as follows:
the test device for measuring the aerodynamic characteristics of the scaled wind power blade under the rotating working condition at least comprises a wind tunnel, a scaled wind power unit which is arranged in a wind tunnel test section and is matched with the wind tunnel in size, and a data acquisition controller, and is characterized in that,
the scaled wind turbine generator at least comprises a foundation fixedly arranged on the bottom surface of the wind tunnel test section, a scaled tower arranged on the foundation and extending along the height direction, a scaled cabin arranged at the top end of the scaled tower and a scaled wind wheel arranged at the front end of the scaled cabin,
the scaling wind wheel at least comprises a scaling hub, a plurality of scaling wind power blades uniformly distributed on the scaling hub along the circumferential direction and a fairing fixedly arranged at the front end of the scaling hub,
a plurality of airflow probes extending along the radial direction are uniformly distributed on the radial outer edge of the fairing along the circumferential direction, the arrangement position of each airflow probe along the circumferential direction is positioned on the symmetrical axis of two adjacent scaled wind power blades,
each scaled wind power blade is provided with a plurality of pressure measuring sections distributed at intervals along the expanding direction, each pressure measuring section forms a blade airfoil to be tested, a plurality of pressure measuring holes penetrating through the surface of the blade and communicated with the inner cavity of the blade are respectively arranged from the front edge to the tail edge on the pressure surface and the suction surface of each blade airfoil to be tested, a plurality of pressure measuring pipes communicated with the pressure measuring holes on the surface of the blade in a one-to-one correspondence manner are arranged in the inner cavity of the blade of each scaled wind power blade,
A pressure scanning valve is fixedly arranged in the inner cavity of the scaling hub, the tail end of a pressure measuring pipe in the blade inner cavity of each scaling wind power blade is communicated with the pressure scanning valve, the pressure scanning valve measures the surface pressure distribution of the blade airfoil to be measured of each scaling wind power blade through each pressure measuring pipe and each pressure measuring hole which are communicated with the pressure scanning valve,
the data acquisition controller is in communication connection with each air flow probe and the pressure scanning valve so as to acquire the surface pressure distribution of the airfoil of the blade to be measured of each scaled wind power blade and the pneumatic pressure data of each air flow probe in real time.
In a preferred embodiment of the invention, at least one load motor is arranged in the scaling cabin, the load motor is in transmission connection with a scaling hub arranged outside the scaling cabin through a main shaft of the wind turbine, and the load motor is in communication connection with the data acquisition controller.
In a preferred embodiment of the present invention, the air flow probes at least include a supporting seat, a variable length probe fixedly disposed on the supporting seat and extending in a radial direction, and a probe disposed at a front end of the variable length probe, and each of the air flow probes is fixedly disposed on a radially outer edge of the fairing through the supporting seat thereof and is uniformly distributed in a circumferential direction. In practice, when selecting the airflow probe, an air flow velocity vector sensor with compact volume and less interference to downstream flow, such as a porous airflow probe or a multi-component hot wire wind speed probe, can be adopted. The measurement and calculation of the relative inflow velocity vector adopts an off-line precalibration and on-line table look-up fitting method of the airflow probe.
In a further example of the present invention, the airflow probes are porous airflow probes or multi-component hot wire wind speed probes, each scaled wind power blade is provided with at least two blade airfoils to be tested which are distributed at intervals in the spanwise direction, and the extending length of each airflow probe in the radial direction is located near the position of the blade airfoil to be tested in the spanwise direction, so that the rotating plane of the airflow probe which rotates synchronously with each scaled wind power blade corresponds to the blade airfoil to be tested on the scaled wind power blade.
In the test device for measuring aerodynamic characteristics of the scaled wind power blade under the rotating working condition, an airflow probe, pressure measuring holes arranged on the surfaces of the scaled wind power blades and a pressure scanning valve are used for measuring surface pressure distribution of wing profiles of the blades to be measured of the scaled wind power blades and relative inflow velocity vectors of the front edges of cross sections, and the test device comprises a synthetic velocity value V p Angle alpha of direction p Etc.
In a preferred embodiment of the invention, the foundation is a fixed base or a six-degree-of-freedom motion platform arranged on the bottom surface of the wind tunnel test section, and is used for providing fixed support for the scaled wind turbine to simulate the motion response of the land fixed wind turbine when the fixed base is selected, and is used for providing six-degree-of-freedom motion support for the scaled wind turbine to simulate the six-degree-of-freedom motion response of the floating wind turbine in the ocean when the six-degree-of-freedom motion platform is selected.
In a preferred embodiment of the invention, the scaling tower at least comprises a tower body, a yaw motor and two six-component force sensors, wherein the lower end of the tower body is arranged on the foundation through the yaw motor, the yaw motor and the two six-component force sensors are both in communication connection with the data acquisition controller, one six-component force sensor is arranged in a connection area between the scaling cabin and the upper end of the tower body, the other six-component force sensor is arranged in a connection area between the lower end of the tower body and the yaw motor, and the two six-component force sensors are used for measuring pneumatic loads applied to the scaling wind turbine in a wind tunnel environment, and the pneumatic loads comprise aerodynamic forces in three directions of transverse oscillation, pitching oscillation and heaving and aerodynamic moments in three directions of transverse oscillation, pitching oscillation and heaving.
In the preferred example of the invention, a plurality of pitch-variable motors in one-to-one corresponding transmission connection with the scaled wind power blades are also arranged in the inner cavity of the scaled hub, each pitch-variable motor is respectively used for driving the correspondingly connected scaled wind power blade to realize pitch adjustment, and a rotating speed torque sensor in communication connection with the data acquisition controller is arranged on the main shaft of the wind turbine.
In a preferred embodiment of the present invention, the data acquisition controller at least includes a model control module and a data acquisition module, wherein,
the model control module is in communication connection with the scaled wind turbine generator and is used for controlling the running state of the wind turbine generator and at least comprises a yaw motor driver which is in communication connection with the yaw motor and sends out control instructions, a load motor driver which is in communication connection with the load motor and sends out control instructions, and a pitch drive which is in communication connection with each pitch motor and sends out control instructions;
the data acquisition module at least comprises a rotating speed and torque data acquisition card in communication connection with the rotating speed and torque sensor, a six-component force data acquisition card in communication connection with each six-component force sensor, a blade surface pressure data acquisition card in communication connection with the pressure scanning valve, and an incoming flow pneumatic pressure data acquisition card in communication connection with each airflow probe, and the data acquisition card is respectively used for acquiring load power data of the load motor, six-component pneumatic load data of the scaling tower, surface pressure distribution data of each blade airfoil to be tested in each scaled wind power blade and incoming flow pneumatic data.
The invention further aims to provide a test method for measuring aerodynamic characteristics of the scaled wind power blade under a rotation working condition, which is based on aerodynamic response simulation of the scaled wind power blade model in a wind tunnel of the test device, and at least comprises four steps of test working condition design, initial parameter setting, operation control and data synchronous acquisition and data analysis,
SS1 design of test conditions
Analyzing key parameters affecting aerodynamic characteristics of the blade according to specific test purposes, and designing different test conditions based on at least the determined key parameters, wherein the key parameters at least comprise aerodynamic attack angle, turbulence, incoming flow condition and lift coefficient C l Coefficient of resistance C d ；
SS2 initial parameter setting
Presetting initial operation parameters which at least comprise wind speed of a wind tunnel, rotating speed of a scaled wind turbine, test duration, control time step length and load parameters, and starting the wind tunnel and the scaled wind turbine according to the preset operation parameters until the operation state is stable;
SS3 synchronous data acquisition and operation control
The method at least comprises two sub-steps of triggering the data acquisition controller to acquire synchronous data and carrying out load regulation based on PID control when in implementation, wherein,
The SS3.1 triggers the data acquisition controller to acquire synchronous data
Each data acquisition card of the data acquisition module in the data acquisition controller acquires load power data of the load motor, surface pressure distribution data of wing profiles of blades to be measured in each scaled wind power blade, incoming flow pneumatic data measured by each airflow probe and six-component pneumatic load data measured by each six-component force sensor in real time; the incoming flow pneumatic data measured by the airflow probe is the relative inflow velocity vector of the airfoil leading edge of the blade to be measured, and the relative inflow velocity vector comprises a synthetic velocity value V p Angle alpha of direction p The method comprises the steps of carrying out a first treatment on the surface of the Respectively integrating according to the collected surface pressure distribution data of each blade airfoil to be tested and the chord line coordinate system of the blade airfoil to be tested to obtain tangential force A and normal force N along the chord line of the airfoil;
SS3.2 load regulation and control based on PID control
According to the load power data of the load motor collected by the data collection module in the data collection controller, the load motor driver controls the load parameters of the load motor in real time based on PID, wherein the PID control parameters comprise a proportional adjustment coefficient, an integral adjustment coefficient and a differential adjustment coefficient, and the PID scheduling control strategy is realized through a formula Determining, wherein u (t) is the load factor of the target load motor at the time t, e (t) is the deviation value calculated at the time t, and K p For the proportional adjustment factor, K i To integrate the adjustment coefficient, K d Is a differential adjustment coefficient;
SS4 data analysis
The step mainly comprises aerodynamic characteristic analysis and operation characteristic analysis when being implemented, wherein the aerodynamic characteristic analysis at least comprises attack angle calculation based on lift annular quantity correction and blade lift coefficient C l And coefficient of resistance C d Calculation ofThe operation characteristic analysis comprises at least calculation of thrust coefficient, torque coefficient and power coefficient, and at least comprises the following steps:
SS4.1 calculation of angle of attack based on lift-loop correction
Because the airflow probes are arranged on the symmetry axis of the adjacent blades, when the wind condition is uniform incoming flow, the induced speeds of the adjacent wind power blades to the airflow probes are equal in magnitude and opposite in direction, so that the influence of the induced speeds of lift force circulation can be mutually offset, and the direction angle alpha in the relative inflow speed vector of the wing profile front edge of the blade to be measured is measured according to the airflow probes p Synthesis speed value V p Obtaining the attack angle alpha of the relative inflow 0 Inflow velocity value V 0 And relative inflow angle of attack alpha 0 Inflow velocity value V 0 No correction is needed, at this time, alpha 0 ＝α p ，V 0 ＝V p ；
When the wind condition is non-uniform, the relative inflow attack angle alpha is required to be based on the lift annular quantity gamma 0 Inflow velocity value V p Performing correction iteration to obtain a corrected and updated relative inflow attack angle alpha e Correcting the updated relative inflow velocity value V e At this time, α 0 ＝α e ，V 0 ＝V e ；
SS4.2 blade lift coefficient C l And coefficient of resistance C d Calculation of
First, tangential force A and normal force N along the airfoil chord line, integrated according to substep SS3.1, and relative inflow angle of attack α, obtained according to substep SS4.1 0 The lift force L and the resistance D of the wing profile of the blade to be measured are obtained through calculation, and the calculation formulas are respectively as follows:
L＝N·cosα 0 -A·sinα 0 ，D＝N·sinα 0 +A·cosα 0 ；
next, based on the calculated lift force L, drag force D, and relative inflow velocity value V 0 Can calculate the lift coefficient C of the blade l And coefficient of resistance C d The calculation formulas are respectively as follows:
wherein c is the chord length of the wing profile of the blade to be tested, and ρ is the air flow density;
SS4.3 axial and circumferential inducer a and b calculations
Updated relative inflow velocity value V calculated according to step SS4.1 e Updated direction angle alpha e And according to the measured incoming wind speed V 0 The wind wheel angular velocity omega is calculated to obtain an axial induction factor a and an axial induction factor b, and the calculation formulas are respectively as follows And->r is the spanwise length of the wing shape of the blade to be tested;
ss.4.4 operational characteristic parameter calculation
The operation characteristic parameter calculation of the step at least comprises calculation of a thrust coefficient, a torque coefficient and a power coefficient, wherein:
calculating a thrust coefficient C according to the axial induction factor a and the circumferential induction factor b calculated in the step SS.4.4 T The calculation formula is thatWherein T is the thrust force exerted by the wind wheel, A is the swept area of the wind wheel, and V 0 For the measured incoming wind speed;
from torque T measured by a rotational speed torque sensor o Calculating a torque coefficient C q The calculation formula is thatWherein R is the radius of the wind wheel;
from torque T measured by a rotational speed torque sensor o Calculating the rotation speed omega of the wind turbine to obtain a power coefficient C P The calculation formula is thatWherein P is the extraction power of the wind wheel.
In the preferred embodiment of the invention, in the step SS4.1, when the wind condition is non-uniform, the inflow attack angle alpha is calculated according to the following substeps based on the lift ring 0 And (3) performing correction iteration:
SS4.1.1 obtaining tangential force A of the airfoil of the jth blade to be tested of the ith blade ij And normal force N ij And measuring by an airflow probe a direction angle alpha in a relative inflow velocity vector of a jth blade airfoil to be measured of the ith blade pij Synthesis speed value V pij ；
SS4.1.2 angle of attack for inflow based on lift annulus 0 Let alpha be the same as before correction 0 ＝α pij ；
SS4.1.3 calculating the lift force L of the airfoil of the n blades to be tested of the ith blade i1 、L i2 、…、L in The calculation formulas are respectively as follows:
L i1 ＝N i1 ·cosα 0 -A i1 ·sinα 0 、…、L in ＝N in ·cosα 0 -A in ·sinα 0 ；
SS4.1.4 calculating lift annular quantity Γ of n blade airfoils to be tested of ith blade i1 、Γ i2 、…、Γ in And the total lift annulus of the ith bladeThe calculation formula is as follows:
SS4.1.5 calculating the induced velocity vector of the ith blade to the position measured by the airflow probeThe calculation formula is as follows:
SS4.1.6 the relative inflow velocity vector of the airfoil correction update of the jth blade to be tested of the ith blade is calculated as follows
SS4.1.7 judging alpha 0 And alpha is eij Whether or not the relation |alpha is satisfied 0 -α eij |＞α max If this relation is satisfied, steps SS4.1.2 to SS4.1.6 are repeated, and if this relation is not satisfied, a corrected inflow attack angle α is obtained eij ；
Wherein m is the number of blades of the wind turbine generator, n is the number of airfoils to be tested of each blade of the wind turbine generator, and alpha pij For the direction angle alpha of the front edge of the airfoil of the jth blade to be tested of the ith scaled wind power blade relative to the inflow velocity vector measured by the airflow probe in the step SS3 0 To scale the initial value of the wind power blade section inflow angle, N ij And A ij Tangential force and normal force along airfoil chord line of the jth section of the ith scaled wind power blade calculated in step SS3 of the wind power blade are respectively L ij Mounting lift force of jth airfoil of ith blade at position corresponding to rotating surface for variable length airflow probe, Γ ij The lift annular quantity at the jth section position of the ith scaled wind power blade is represented by rho, which is inflow density, V pij For the resultant velocity value of the jth section of the ith blade relative to the inflow velocity vector at the leading edge, R l R is the radius of the airflow probe from the rotation center of the wind wheel b Is the radius of the blade tip from the center of rotation, l b For the length of the blade root from the blade tip,induced velocity vector generated at the air flow probe measurement for the linear vortex of the ith scaled wind blade,/->The relative inflow velocity vector after updating the airfoil of the jth blade to be tested for the ith blade, V eij For the updated relative inflow velocity value alpha of the airfoil of the jth blade to be tested of the ith blade eij The updated direction angle alpha of the wing profile of the jth blade to be tested is the ith blade max Is the set maximum difference.
According to the test device and the method for measuring aerodynamic characteristics of the scaled wind power blade under the rotating working condition, provided by the invention, the airflow probe is arranged on the hub, the scaled wind power blade synchronously rotates, the relative inflow velocity vector of the cross section of the same rotating surface blade is measured, the attack angle calculation method which is used for uniformly flowing down and is not required to be corrected is provided, and meanwhile, the aerodynamic characteristic parameters and the operation characteristic parameters of the blade, including a lift coefficient, a resistance coefficient, an axial induction factor, a circumferential induction factor, a thrust coefficient, a torque coefficient, a power coefficient and the like, are calculated by the attack angle calculation method which is used for non-uniform inflow such as shearing inflow and is corrected based on the lift annular quantity of the blade.
(III) technical effects
Compared with the prior art, the test device and the method for measuring the aerodynamic characteristics of the scaled wind power blade under the rotating working condition have the remarkable technical effects that:
(1) According to the test device and the test method for measuring aerodynamic characteristics of the scaled wind power blades under the rotating working condition, the air flow probe is arranged on the symmetry axis of the adjacent wind power blades, so that the method and the device for measuring attack angle and aerodynamic force in the rotating process of the scaled wind power blades under the uniform incoming flow and the non-uniform incoming flow are provided, and an effective test means is provided for the research of the aerodynamic characteristics of the rotating blades.
(2) According to the test device and the method for measuring the aerodynamic characteristics of the scaled wind power blade under the rotating working condition, a plurality of aerodynamic characteristic parameters can be further calculated by means of an airflow probe, blade surface pressure measurement and the like, the aerodynamic characteristic parameters comprise, but are not limited to, attack angles, lift coefficients, resistance coefficients, lift-drag ratios and induction factors of the scaled wind power blade, and the operating characteristic parameters comprise, but are not limited to, torque coefficients, thrust coefficients and power coefficients, so that the technical problems of aerodynamic characteristics and aerodynamic forces of the scaled wind power blade including the blade aerodynamic attack angles and the like in the wind tunnel environment are solved.
Drawings
FIG. 1 is a schematic diagram of a wind tunnel test device for aerodynamic characteristics of scaled wind turbine blades of a land wind turbine;
FIG. 2 is a schematic diagram of a wind tunnel test device for the aerodynamic characteristics of scaled wind blades of a floating wind turbine generator;
FIG. 3 is a schematic diagram of the scaled wind blade operational parameter measurement principle of the present invention;
FIG. 4 is a schematic diagram of a test for measuring aerodynamic characteristics of scaled wind blades under rotational conditions according to the present invention;
FIG. 5 is a schematic diagram of a data analysis flow in the present invention;
FIG. 6 is a schematic diagram of an iterative process for correcting an incoming flow attack angle based on lift-loop quantity in the present invention;
wherein the meanings of the reference numerals are as follows:
the wind power generation system comprises a 1-scaling wind power blade, two blade wing profiles to be tested on a 2-scaling blade, a pressure measuring hole, a 3-airflow probe, a 4-cabin, a 5-tower, a 6-fixed foundation, a 7-six-component force sensor, an 8-yaw motor and a 9-six-degree-of-freedom motion platform.
Detailed Description
The invention will be described in further detail below with reference to the accompanying drawings, the content of which is for explanation rather than limitation of the invention, in order to make the objects and technical solutions of the invention more apparent. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are intended to be illustrative of the invention and should not be construed as limiting the invention in any way. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1 and 2, the model test device for measuring aerodynamic characteristics of a scaled wind turbine blade section at least comprises a wind tunnel (not shown in the drawing), a scaled wind turbine generator set which is arranged in a wind tunnel test section and is matched with the wind tunnel test section in size, and a data acquisition controller (not shown in the drawing), wherein the scaled wind turbine generator set comprises a scaled wind turbine blade 1, a surface pressure measuring point 2, an airflow probe 3, a scaled cabin 4, a scaled tower 5, a fixed base 6, a six-component force sensor 7, a yaw motor 8 and a six-degree-of-freedom motion platform 9. The fixed base 6 is fixedly arranged on the bottom surface of the wind tunnel test section, the scaling tower 5 is arranged on the fixed base 6 or the six-degree-of-freedom moving platform 9 and extends along the height direction, the scaling cabin 4 is arranged at the top end of the scaling tower 5, and the scaling wind wheel is arranged at the front end of the scaling cabin 4.
The airflow probe 3 can be a porous airflow probe or a multi-component hot wire wind speed probe, and is arranged on a hub, and synchronously rotates with the blade, the rotating plane of the probe corresponds to the section airfoil to be measured on the scaled wind power blade 1, a plurality of surface pressure measuring points 2 are respectively arranged on the pressure surface and the suction surface of each blade airfoil to be measured from the front edge to the tail edge, each surface pressure measuring point 2 is in communication connection with a pressure scanning valve, and the surface pressure measuring points 2 are used for measuring the surface pressure distribution of the blade airfoil to be measured. For measuring the relative inflow velocity vector of the front edge of the section of the scaled wind power blade, comprising the resultant velocity value V p Angle alpha of direction p . The data collection and analysis unit respectively integrates the pressure value fed back by each surface pressure measurement point 2 and the chord line coordinate system of each blade airfoil to be tested according to the pressure value acquired by the data collection and analysis unit to obtain tangential force and normal force along the chord line of the airfoil, and takes the average value of the tangential force and the normal force of each blade airfoil to be tested as the tangential force A and the normal force N of the blade airfoil at the installation position of the airflow probe 3.
The six-component force sensor 7 is arranged on the lower end face of the tower 5 and the upper end face of the yaw motor 8 and is used for measuring pneumatic load of the scaling wind turbine generator in a wind tunnel environment, wherein the pneumatic load comprises aerodynamic forces in three directions of transverse oscillation, longitudinal oscillation and vertical oscillation and aerodynamic moments in three directions of transverse oscillation, longitudinal oscillation and vertical oscillation.
The foundation may be a fixed base 6 or a six degree of freedom motion platform 9. The six-degree-of-freedom motion platform 9 is used for providing six-degree-of-freedom motion support for the scaled wind turbine and simulating six-degree-of-freedom motion response of the floating wind turbine in the ocean.
The data acquisition controller comprises a model control module and a data acquisition module, wherein the model control module comprises a yaw motor driver, a load motor driver, a motor control card and synchronous measurement control integrated software, is in communication connection with the model unit and is used for controlling the running state of the model unit; the data acquisition module comprises a rotating speed and torque acquisition card, a six-component force sensor acquisition card and a pressure measurement system, and is in communication connection with the model unit, the six-component sensor 7 and the pressure scanning valve to respectively acquire parameters such as rotating speed and torque, six-component pneumatic load, blade surface pressure distribution and the like.
When the device of the invention is used for experimental study, the device at least comprises four steps of experimental working condition design, initial parameter setting, operation control and data synchronous acquisition, data analysis and the like, taking the experimental study of the pneumatic characteristics of the floating wind turbine generator with two blades and two pressure measurement wing profiles arranged on each blade as an example,
1. test working condition design, in order to explore the influence of working conditions such as different incoming flow conditions, different platform movements, different load rates and the like of a wind turbine on the aerodynamic characteristics of a blade and the operation characteristics of a wind turbine, the following working condition table 1 can be designed, but is not limited to:
TABLE 1
2. Initial parameter setting, taking dynamic test, load, uniform incoming flow (10 m/s) and simulated turbulence working condition as examples, setting operation parameters such as wind tunnel wind speed of 10m/s, scaling wind turbine generator set rotating speed of 900r/min, test duration of 10min, control time step of 0.1s and the like, and starting the wind tunnel and scaling wind turbine generator set according to preset parameters until the operation state is stable.
3. And the operation control and the data synchronous acquisition comprise load PID regulation and control and triggering synchronous acquisition.
Load motor and data in PID control load regulation methodThe acquisition controller is in communication connection and is used for controlling the load parameters in real time according to the acquired load power data so as to achieve the target torque. The PID parameters comprise a proportional adjustment coefficient, an integral adjustment coefficient and a differential adjustment coefficient, and the PID scheduling strategy is realized by a formula Determining an initial scaling factor K p Set to 20, integrate the adjustment coefficient K i Set to 0.1, differential adjustment coefficient K d Set to 0.1, the PID parameters were modified gradually as the experiment proceeded to achieve faster convergence.
The data acquisition controller acquires the pneumatic pressure data of the pressure measuring holes 2 and the air flow probes 3 of the two sections of the blade in real time, reads the six-component pneumatic load data of the six-component force sensor 7, and synchronously processes and analyzes the data; the blade airfoil leading edge relative inflow velocity vector measurement, the velocity measured directly by the airflow probe 3 is the blade cross-section leading edge relative inflow velocity vector, including the resultant velocity value V p Angle alpha of direction p Specifically, the measurement and calculation of the relative inflow velocity vector can adopt an offline precalibration and online table look-up fitting method of the airflow probe 3; and (3) measuring aerodynamic force of the blade airfoil, selecting two blade airfoils to be measured on the blade, arranging a plurality of pressure measuring holes from the front edge to the tail edge on the pressure surface and the suction surface of the blade airfoil respectively to measure pressure distribution on the surface of the blade, and integrating according to a chord line coordinate system of the blade airfoil to be measured to obtain tangential force A and normal force N along the chord line of the airfoil.
4. Data analysis, including aerodynamic and operational characteristics analysis
4.1. The attack angle calculation based on lift loop quantity correction is carried out, because the airflow probes are arranged on the symmetry axes of the adjacent blades, when the wind conditions are uniform incoming flow, the induced speeds of the adjacent wind power blades on the airflow probes are equal in magnitude and opposite in direction, so that the influence of the lift loop quantity induced speeds can be mutually offset, and the measured attack angle does not need to be corrected; when the wind condition is non-uniform incoming flow, the attack angle correction iteration steps are as follows:
4.1.1 obtaining the blade Airfoil to be tested for two blades of the same bladeTangential force A 1 、A′ 1 And normal force N 1 、N′ 1 And the direction angle alpha in the relative inflow velocity vector measured by the airflow probe p1 Synthesis speed value V p1 、V′ p1 ；
4.1.2 incidence angle alpha to the flow based on lift-loop quantity 0 Let alpha be the same as before correction 0 ＝α p1 ；
4.1.3 calculating the Lift force L of the wing profiles of two blades to be tested of the same blade 1 、L′ 1 The calculation formulas are respectively as follows: l (L) 1 ＝N 1 ·cosα 0 -A 1 ·sinα 0 ，L′ 1 ＝N′ 1 ·cosα 0 -A′ 1 ·sinα 0 ；
4.1.4 calculating the lift annular quantity Γ of the wing sections of two blades to be tested of the same blade 1 、Γ′ 1 The calculation formulas are respectively as follows:
4.1.5 calculating the induced velocity vector of the two blades to the measurement position of the airflow probe, respectivelyThe calculation formula is as follows:
4.1.6 calculating a corrected updated relative inflow velocity vector of the formula
4.1.7 determination of alpha 0 And alpha is e Whether or not the relation |alpha is satisfied 0 -α e |＞α max If this relation is satisfied, repeating steps 4.1.2 to 4.1.6, and if this relation is not satisfied, obtaining a corrected inflow attack angle α e ；
Wherein alpha is pi Alpha is the direction angle of the leading edge of the ith scaled wind power blade relative to the inflow velocity vector measured by the airflow probe in step SS3 0 To scale the initial value of the inflow angle of two sections of the wind power blade, N 1 、N′ 1 And A 1 、A′ 1 Respectively the tangential force and the normal force along the chord line of the airfoil profile of two different sections of the same scaled wind power blade calculated in the step 3, L 1 、L′ 1 The lift force of the wing section of the blade at the position corresponding to the rotating surface is arranged for the variable-length airflow probe, and the gamma is 1 、Γ′ 1 For the lift annular quantity of the two section positions of the first scaled wind power blade, Γ 2 、Γ′ 2 The lift annular quantity of the two section positions of the second scaled wind power blade is represented by rho, which is the inflow density, V p1 、V′ p1 The combined velocity values of the relative inflow velocity vectors of the two sections of the blade at the front edge are respectively R l The radius R of the airflow probe from the rotation center of the wind wheel b Is the radius of the blade tip from the center of rotation, l b For the length of the blade root from the blade tip,for the induced velocity vector generated by the linear vortices of the first scaled wind blade and the second scaled wind blade,for the updated relative inflow velocity vector, V e For updated relative inflow velocity value, alpha e For updated direction angle, α max Is the set maximum difference;
4.2. calculated lift force L and drag force D according to step 4.1, and measured inflow velocity V 0 Can calculate the lift coefficient C of the blade l And coefficient of resistance C d The calculation formulas are respectively as follows:
4.3. calculating axial induction factor based on She Sudong quantity theorya and a circumferential induction factor b, according to step 4.1. The updated relative inflow velocity value V calculated e Updated direction angle alpha e And according to the measured incoming wind speed V 0 The angular velocity omega of the wind wheel can be calculated to obtain the axial induction factorAnd axial induction factor->
4.4. And calculating operation characteristic parameters, including calculation of thrust coefficient, torque coefficient and power coefficient. According to the wind wheel thrust T calculated by the six-component pneumatic load data acquired in the step 3, a thrust coefficient can be calculatedFrom the torque To and the wind turbine speed Ω measured by the speed torque sensor, a torque coefficient +.>And power coefficient->
4.5. And controlling the load motor to rotate to the next time step according to the preset torque rotating speed, repeatedly monitoring and recording data by using a six-degree-of-freedom platform, a six-component balance, a rotating speed torque sensor, an airflow probe and other sensors until the preset test time is reached for 10min, gradually stopping rotating the wind wheel, closing the load motor, closing the wind tunnel, deriving test data, obtaining the time history of the pneumatic parameters and the motion characteristic parameters of the scaled wind power blade, and analyzing the test data.
The object of the present invention is fully effectively achieved by the above-described embodiments. All equivalent or simple changes of the structure, characteristics and principle according to the inventive concept are included in the protection scope of the present invention. Those skilled in the art may make various modifications or additions to the described embodiments or substitutions in a similar manner without departing from the scope of the invention as defined in the accompanying claims.
Claims (10)
1. The test device for measuring the aerodynamic characteristics of the scaled wind power blade under the rotating working condition at least comprises a wind tunnel, a scaled wind power unit which is arranged in a wind tunnel test section and is matched with the wind tunnel in size, and a data acquisition controller, and is characterized in that,
the scaled wind turbine generator at least comprises a foundation fixedly arranged on the bottom surface of the wind tunnel test section, a scaled tower arranged on the foundation and extending along the height direction, a scaled cabin arranged at the top end of the scaled tower and a scaled wind wheel arranged at the front end of the scaled cabin,
the scaling wind wheel at least comprises a scaling hub, a plurality of scaling wind power blades uniformly distributed on the scaling hub along the circumferential direction and a fairing fixedly arranged at the front end of the scaling hub,
A plurality of airflow probes extending along the radial direction are uniformly distributed on the radial outer edge of the fairing along the circumferential direction, the arrangement position of each airflow probe along the circumferential direction is positioned on the symmetrical axis of two adjacent scaled wind power blades,
each scaled wind power blade is provided with a plurality of pressure measuring sections distributed at intervals along the expanding direction, each pressure measuring section forms a blade airfoil to be tested, a plurality of pressure measuring holes penetrating through the surface of the blade and communicated with the inner cavity of the blade are respectively arranged from the front edge to the tail edge on the pressure surface and the suction surface of each blade airfoil to be tested, a plurality of pressure measuring pipes communicated with the pressure measuring holes on the surface of the blade in a one-to-one correspondence manner are arranged in the inner cavity of the blade of each scaled wind power blade,
a pressure scanning valve is fixedly arranged in the inner cavity of the scaling hub, the tail end of a pressure measuring pipe in the blade inner cavity of each scaling wind power blade is communicated with the pressure scanning valve, the pressure scanning valve measures the surface pressure distribution of the blade airfoil to be measured of each scaling wind power blade through each pressure measuring pipe and each pressure measuring hole which are communicated with the pressure scanning valve,
the data acquisition controller is in communication connection with each air flow probe and the pressure scanning valve so as to acquire the surface pressure distribution of the airfoil of the blade to be measured of each scaled wind power blade and the pneumatic pressure data of each air flow probe in real time.
2. The test device for measuring aerodynamic characteristics of scaled wind power blades under a rotating condition according to claim 1, wherein at least one load motor is arranged in a scaled cabin, the load motor is in transmission connection with a scaled hub arranged outside the scaled cabin through a main shaft of the wind power machine, and the load motor is in communication connection with the data acquisition controller.
3. The test device for measuring aerodynamic characteristics of scaled wind power blades under a rotating condition according to claim 1, wherein the airflow probes at least comprise a supporting seat, a variable-length probe rod fixedly arranged on the supporting seat and extending along a radial direction, and a probe arranged at the front end of the variable-length probe rod, and each airflow probe is fixedly arranged on the radial outer edge of the fairing through the supporting seat thereof and is uniformly distributed along the circumferential direction.
4. A test device for measuring aerodynamic characteristics of scaled wind power blades under a rotation condition according to claim 3, wherein the airflow probes are porous airflow probes or multi-component hot wire wind speed probes, each scaled wind power blade is provided with at least two blade airfoils to be measured which are distributed at intervals in a spanwise direction of the airflow probes, and an extension length of each airflow probe in a radial direction is located near a position of the blade airfoil to be measured in the spanwise direction, so that a rotation plane of the airflow probe which rotates synchronously with each scaled wind power blade corresponds to the blade airfoil to be measured on the scaled wind power blade.
5. The test device for measuring aerodynamic characteristics of a scaled wind turbine blade under a rotation condition as claimed in claim 1, wherein the foundation is a fixed base or a six-degree-of-freedom motion platform arranged on the bottom surface of the wind tunnel test section, and is used for providing fixed support for the scaled wind turbine to simulate a motion response of a land fixed wind turbine when the fixed base is selected, and is used for providing six-degree-of-freedom motion support for the scaled wind turbine to simulate a six-degree-of-freedom motion response of a floating wind turbine in the ocean when the six-degree-of-freedom motion platform is selected.
6. The test device for measuring aerodynamic characteristics of scaled wind power blades under a rotating condition according to claim 1, wherein the scaled tower at least comprises a tower body, a yaw motor and two six-component force sensors, the lower end of the tower body is arranged on the foundation through the yaw motor, the yaw motor and the two six-component force sensors are all in communication connection with the data acquisition controller, one six-component force sensor is arranged in a connection area between the scaled nacelle and the upper end of the tower body, the other six-component force sensor is arranged in a connection area between the lower end of the tower body and the yaw motor, and the two six-component force sensors are used for measuring aerodynamic loads applied to the scaled wind power unit in a wind tunnel environment, and the aerodynamic loads comprise aerodynamic forces in three directions of transverse oscillation, longitudinal oscillation and heave oscillation and aerodynamic moments in three directions of transverse oscillation, longitudinal oscillation and heave oscillation.
7. The test device for measuring aerodynamic characteristics of scaled wind power blades under a rotating condition according to claim 1, wherein a plurality of pitch-variable motors in one-to-one transmission connection with the scaled wind power blades are further arranged in an inner cavity of the scaled hub, each pitch-variable motor is respectively used for driving the correspondingly connected scaled wind power blade to realize pitch adjustment, and a rotating speed torque sensor in communication connection with the data acquisition controller is arranged on a main shaft of the wind power machine.
8. The test device for measuring aerodynamic characteristics of scaled wind power blades under rotation conditions as claimed in claim 1, wherein the data acquisition controller comprises at least a model control module and a data acquisition module, wherein,
the model control module is in communication connection with the scaled wind turbine generator and is used for controlling the running state of the wind turbine generator and at least comprises a yaw motor driver which is in communication connection with the yaw motor and sends out control instructions, a load motor driver which is in communication connection with the load motor and sends out control instructions, and a pitch drive which is in communication connection with each pitch motor and sends out control instructions;
The data acquisition module at least comprises a rotating speed and torque data acquisition card in communication connection with the rotating speed and torque sensor, a six-component force data acquisition card in communication connection with each six-component force sensor, a blade surface pressure data acquisition card in communication connection with the pressure scanning valve, and an incoming flow pneumatic pressure data acquisition card in communication connection with each airflow probe, and the data acquisition card is respectively used for acquiring load power data of the load motor, six-component pneumatic load data of the scaling tower, surface pressure distribution data of each blade airfoil to be tested in each scaled wind power blade and incoming flow pneumatic data.
9. The method for measuring aerodynamic characteristics of the scaled wind power blade under the rotation working condition is characterized by adopting the test device of any one of the claims 1-8 to open aerodynamic response simulation of the scaled wind power blade model in the wind tunnel, and specifically comprises the following steps:
SS1 design of test conditions
Analyzing key parameters affecting aerodynamic characteristics of the blade according to specific test purposes, and designing different test conditions based on at least the determined key parameters, wherein the key parameters at least comprise aerodynamic attack angle, turbulence, incoming flow condition and lift coefficient C l Coefficient of resistance C d ；
SS2 initial parameter setting
Presetting initial operation parameters which at least comprise wind speed of a wind tunnel, rotating speed of a scaled wind turbine, test duration, control time step length and load parameters, and starting the wind tunnel and the scaled wind turbine according to the preset operation parameters until the operation state is stable;
SS3 synchronous data acquisition and operation control
The method at least comprises two sub-steps of triggering the data acquisition controller to acquire synchronous data and carrying out load regulation based on PID control when in implementation, wherein,
the SS3.1 triggers the data acquisition controller to acquire synchronous data
Each data acquisition card of the data acquisition module in the data acquisition controller acquires load power data of the load motor, surface pressure distribution data of wing profiles of blades to be measured in each scaled wind power blade, incoming flow pneumatic data measured by each airflow probe and six-component pneumatic load data measured by each six-component force sensor in real time; the incoming flow pneumatic data measured by the airflow probe is the relative inflow velocity vector of the airfoil leading edge of the blade to be measured, and the relative inflow velocity vector comprises a synthetic velocity value V p Angle alpha of direction p The method comprises the steps of carrying out a first treatment on the surface of the Respectively integrating according to the collected surface pressure distribution data of each blade airfoil to be tested and the chord line coordinate system of the blade airfoil to be tested to obtain tangential force A and normal force N along the chord line of the airfoil;
SS3.2 load regulation and control based on PID control
According to the load power data of the load motor collected by the data collection module in the data collection controller, the load motor driver controls the load parameters of the load motor in real time based on PID, wherein the PID control parameters comprise a proportional adjustment coefficient, an integral adjustment coefficient and a differential adjustment coefficient, and the PID scheduling control strategy is realized through a formulaDetermining, wherein u (t) is the load factor of the target load motor at the time t, e (t) is the deviation value calculated at the time t, and K p For the proportional adjustment factor, K i To integrate the adjustment coefficient, K d Is a differential adjustment coefficient;
SS4 data analysis
The step mainly comprises aerodynamic characteristic analysis and operation characteristic analysis when being implemented, wherein the aerodynamic characteristic analysis at least comprises attack angle calculation based on lift annular quantity correction and blade lift coefficient C l And coefficient of resistance C d Calculating an axial induction factor a and a circumferential induction factor b, wherein the operation characteristic analysis at least comprises calculation of a thrust coefficient, a torque coefficient and a power coefficient, and at least comprises the following steps:
SS4.1 calculation of angle of attack based on lift-loop correction
Because the airflow probes are arranged on the symmetry axis of the adjacent blades, when the wind condition is uniform incoming flow, the induced speeds of the adjacent wind power blades to the airflow probes are equal in magnitude and opposite in direction, so that the influence of the induced speeds of lift force circulation can be mutually offset, and the direction angle alpha in the relative inflow speed vector of the wing profile front edge of the blade to be measured is measured according to the airflow probes p Synthesis speed value V p Obtaining the attack angle alpha of the relative inflow 0 Inflow velocity value V 0 And relative inflow angle of attack alpha 0 Inflow velocity value V 0 No correction is needed, at this time, alpha 0 ＝α p ，V 0 ＝V p ；
When the wind condition is non-uniform, the relative inflow attack angle alpha is required to be based on the lift annular quantity gamma 0 Inflow velocity value V p Performing correction iteration to obtain a corrected and updated relative inflow attack angle alpha e Correcting the updated relative inflow velocity value V e At this time, α 0 ＝α e ，V 0 ＝V e ；
SS4.2 blade lift coefficient C l And coefficient of resistance C d Calculation of
First, tangential force A and normal force N along the airfoil chord line, integrated according to substep SS3.1, and relative inflow angle of attack α, obtained according to substep SS4.1 0 The lift force L and the resistance D of the wing profile of the blade to be measured are obtained through calculation, and the calculation formulas are respectively as follows:
L＝N·cosα 0 -A·sinα 0 ，D＝N·sinα 0 +A·cosα 0 ；
Next, based on the calculated lift force L, drag force D, and relative inflow velocity value V 0 Can calculate the lift coefficient C of the blade l And coefficient of resistance C d The calculation formulas are respectively as follows:
wherein c is the chord length of the wing profile of the blade to be tested, and ρ is the air flow density;
SS4.3 axial and circumferential inducer a and b calculations
Updated relative inflow velocity value V calculated according to step SS4.1 e Updated direction angle alpha e And according to the measured incoming wind speed V 0 The wind wheel angular velocity omega is calculated to obtain an axial induction factor a and an axial induction factor b, and the calculation formulas are respectively as followsAnd->r is the spanwise length of the wing shape of the blade to be tested;
ss.4.4 operational characteristic parameter calculation
The operation characteristic parameter calculation of the step at least comprises calculation of a thrust coefficient, a torque coefficient and a power coefficient, wherein:
calculating a thrust coefficient C according to the axial induction factor a and the circumferential induction factor b calculated in the step SS.4.4 T The calculation formula is thatWherein T is the thrust force exerted by the wind wheel, A is the swept area of the wind wheel, and V 0 For the measured incoming wind speed;
from torque T measured by a rotational speed torque sensor o Calculating a torque coefficient C q The calculation formula is thatWherein R is the radius of the wind wheel;
From torque T measured by a rotational speed torque sensor o Calculating the rotation speed omega of the wind turbine to obtain a power coefficient C P The calculation formula is thatWherein P is the extraction power of the wind wheel.
10. The method for measuring aerodynamic characteristics of a scaled wind turbine blade according to claim 9, wherein in step SS4.1, when the wind condition is a non-uniform incoming flow, the incoming flow attack angle α is calculated based on the lift ring number according to the following sub-steps 0 And (3) performing correction iteration:
SS4.1.1 obtaining tangential force A of the airfoil of the jth blade to be tested of the ith blade ij And normal force N ij And measuring by an airflow probe a direction angle alpha in a relative inflow velocity vector of a jth blade airfoil to be measured of the ith blade pij Synthesis speed value V pij ；
SS4.1.2 angle of attack for inflow based on lift annulus 0 Let alpha be the same as before correction 0 ＝α pij ；
SS4.1.3 calculating the lift force L of the airfoil of the n blades to be tested of the ith blade i1 、L i2 、…、L in The calculation formulas are respectively as follows:
L i1 ＝N i1 ·cosα 0 -A i1 ·sinα 0 、…、L in ＝N in ·cosα 0 -A in ·sinα 0 ；
SS4.1.4 calculating lift annular quantity Γ of n blade airfoils to be tested of ith blade i1 、Γ i2 、…、Γ in And the total lift annulus of the ith bladeThe calculation formula is as follows:
SS4.1.5 calculating the induced velocity vector of the ith blade to the position measured by the airflow probeThe calculation formula is as follows:
SS4.1.6 the relative inflow velocity vector of the airfoil correction update of the jth blade to be tested of the ith blade is calculated as follows
SS4.1.7 judging alpha 0 And alpha is eij Whether or not the relation alpha is satisfied 0 -α eij ＞α max If the relation is satisfied, repeating steps SS4.1.2 to SS4.1.6, and if the relation is not satisfied, obtaining the inflow attack angle alpha after the airfoil correction of the jth blade to be tested of the ith blade eij ；
Wherein m is the number of blades of the wind turbine generator, n is the number of airfoils to be tested of each blade of the wind turbine generator, and alpha pij For the direction angle alpha of the front edge of the airfoil of the jth blade to be tested of the ith scaled wind power blade relative to the inflow velocity vector measured by the airflow probe in the step SS3 0 To scale the initial value of the wind power blade section inflow angle, N ij And A ij Tangential force and normal force along airfoil chord line of the jth section of the ith scaled wind power blade calculated in step SS3 of the wind power blade are respectively L ij The lift force of the jth wing section of the ith blade at the position corresponding to the rotating surface is installed for the variable-length airflow probe, Γij is the lift force annular quantity of the jth section position of the ith scaled wind power blade,ρ is the inflow density, V pij For the composite velocity value of the jth cross section of the ith blade relative to the inflow velocity vector at the leading edge, rl is the radius of the airflow probe from the center of rotation of the wind wheel, R b Is the radius of the blade tip from the center of rotation, l b For the length of the blade root from the blade tip,induced velocity vector generated at the air flow probe measurement for the linear vortex of the ith scaled wind blade,/->The relative inflow velocity vector after updating the airfoil of the jth blade to be tested for the ith blade, V eij For the updated relative inflow velocity value alpha of the airfoil of the jth blade to be tested of the ith blade eij The updated direction angle alpha of the wing profile of the jth blade to be tested is the ith blade max Is the set maximum difference.
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