CN113504027A - Method for manufacturing aeroelastic wind tunnel test model of wind turbine blade - Google Patents

Method for manufacturing aeroelastic wind tunnel test model of wind turbine blade Download PDF

Info

Publication number
CN113504027A
CN113504027A CN202110931276.1A CN202110931276A CN113504027A CN 113504027 A CN113504027 A CN 113504027A CN 202110931276 A CN202110931276 A CN 202110931276A CN 113504027 A CN113504027 A CN 113504027A
Authority
CN
China
Prior art keywords
aeroelastic
model
wind turbine
turbine blade
section
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202110931276.1A
Other languages
Chinese (zh)
Other versions
CN113504027B (en
Inventor
柯世堂
吴鸿鑫
陆曼曼
高沐恩
田文鑫
杨杰
任贺贺
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nanjing University of Aeronautics and Astronautics
Original Assignee
Nanjing University of Aeronautics and Astronautics
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nanjing University of Aeronautics and Astronautics filed Critical Nanjing University of Aeronautics and Astronautics
Priority to CN202110931276.1A priority Critical patent/CN113504027B/en
Publication of CN113504027A publication Critical patent/CN113504027A/en
Application granted granted Critical
Publication of CN113504027B publication Critical patent/CN113504027B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/08—Aerodynamic models
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B10/00—Integration of renewable energy sources in buildings
    • Y02B10/30—Wind power

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Physics & Mathematics (AREA)
  • Wind Motors (AREA)

Abstract

The invention discloses a method for manufacturing a wind turbine blade aeroelastic wind tunnel test model, which comprises a reasonable simplified similarity criterion of a wind turbine blade aeroelastic model, a method for designing an equivalent section of the aeroelastic model and a method for manufacturing a frame section/coat of the aeroelastic model. Firstly, deducing a reasonable simplification similarity criterion of a wind turbine blade aeroelastic model based on motion equivalence; then, a variational progressive equivalent section method is provided to design a high-precision equivalent wind power blade model special-shaped section, and the aeroelastic model design of blade aeroelastic model pneumatic-rigidity-quality scale mapping is realized; and finally, obtaining a aeroelastic model frame section by means of high-precision 3D printing, and completing the production of the aeroelastic model frame section/coat by means of connecting rib single-point splicing of the full-length model, filling of a hollow area with a balsa wood piece polishing coat, pasting of a counterweight lead piece at the rear edge, pasting of a rough strip at the front edge and filling of a gap with sponge. The invention makes up the defects of the existing method for designing and manufacturing the aeroelastic model of the wind turbine blade at home and abroad.

Description

Method for manufacturing aeroelastic wind tunnel test model of wind turbine blade
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to a method for manufacturing a wind turbine blade aeroelastic wind tunnel test model.
Background
Under the development of the current wind turbine generator with ultra-high power, the trend of ultra-long flexible refining of the wind turbine blades is remarkable, the problem of blade aeroelastic wind vibration caused by the structure/pneumatic double nonlinearity is prominent, and related wind turbine blade wind damage events occur frequently. The aeroelastic wind tunnel test is an effective mode for researching strong nonlinear aeroelastic motion mechanism and modal energy gathering characteristic, is a well-known, feasible and effective important means in the field of the existing wind engineering, and is mature and applied to large-span bridges, high-rise buildings, large-span space structures and individual special structures. However, the wind turbine blade is limited by structural factors such as a gradual change continuous wing section, a composite laying layer and main beam integrated stress structure, a continuous length change characteristic and pre-bending of a three-center-one shaft (a mass center, a shear center, a geometric center and a neutral axis), and test factors such as difficulty in measuring point arrangement, strong acquisition interference, low measurement precision and the like caused by an exaggerated aspect ratio of a blade model with a large scale ratio.
The aeroelastic wind tunnel test model needs to simulate the structural characteristics of the structure such as mass, rigidity, damping and the like, and simultaneously needs a wind tunnel flow field and an actual wind field to follow the same flow differential equation, so that the fluid motion scale is similar. Due to the complexity of actual flow, it is impossible to realize that the scaled wind tunnel test simultaneously satisfies all similar criteria, and the existing similar theory generally deduces the decisive similar criteria of the structure type based on the main acting force of the actual flow process. The model design and manufacturing method of the prior art capable of checking the aeroelastic wind tunnel test is divided into three methods of single degree of freedom, multiple degrees of freedom and continuous aeroelastic, the existing manufacturing methods of aeroelastic models with different structures have larger difference, and the method for manufacturing the aeroelastic models has not been recognized to take the simplicity, accuracy and universality of model manufacturing into consideration.
Disclosure of Invention
The invention aims to solve the technical problem of providing a wind turbine blade aeroelastic wind tunnel test model manufacturing method aiming at the defects of the prior art, and overcomes the defects of the existing wind turbine blade aeroelastic model design and manufacturing methods at home and abroad.
In order to achieve the technical purpose, the technical scheme adopted by the invention is as follows:
a wind turbine blade aeroelastic wind tunnel test model manufacturing method comprises the following steps: the method comprises the following steps:
step one, deducing a reasonable simplified similarity criterion of a wind turbine blade aeroelastic model based on motion equivalence;
step two, taking the equivalent section design method as the wind turbine blade aeroelastic model equivalent section design method,
and step three, taking the aeroelastic model frame section/coat manufacturing method as a wind turbine blade aeroelastic model manufacturing method, and further manufacturing a wind turbine blade aeroelastic wind tunnel test model.
The further optimization scheme of the invention is as follows:
in the first step, the reasonable simplification similarity criterion comprises wind speed ratio, time ratio and frequency ratio which are derived by fluid motion similarity; density ratio and damping ratio required by the same dimensionless parameter; the structure motion is similar to the derived mass ratio and stiffness ratio.
And in the second step, the wind turbine blade aeroelastic model equivalent section design method comprises the steps of obtaining the waving, swinging and twisting three-way rigidity of the composite material blade based on composite section analysis, and obtaining an aeroelastic wind tunnel test model structure meeting the three-way scale rigidity and three-center-to-one-axis requirements based on topological optimization equivalent section design.
In the third step, the aeroelastic model frame section/coat manufacturing method comprises the steps of 3D printing aeroelastic model frame sections in a segmented mode, completing splicing of full-length structural frame sections through connecting ribs, achieving pneumatic appearance sealing after enclosure filling, and finally completing manufacturing of a wind turbine blade aeroelastic wind tunnel test model after pneumatic compensation measures.
And in the second step, designing an equivalent section by adopting a through long beam frame, a rigid main beam or an enclosure frame section.
The fluid motion is similar to that of the following: the air in the flow field of the wind turbine blade is low-speed, incompressible and Newtonian viscous flow, and the fluid motion equation is as follows:
Figure BDA0003211319220000021
in the formula ui(i is 1, 2, 3) in a rectangular coordinate system x (x), respectively1)，y(x2)，z(x3) A directional fluid motion velocity component; f. ofiIn a rectangular coordinate system x (x)1)，y(x2)，z(x3) A directional fluid force; ρ is the air density; p is the pressure intensity; v is the dynamic viscosity of air, and v is mu/rho; x (x)1)，y(x2)，z(x3) Respectively, the three main axial directions of the rectangular coordinate system.
Reference symbol λXX representing a modelmOf the same entity as XaRatio of (i.e.. lambda.)X＝Xm/XaVariables with x are model variables, prototype variables without x, λt、λ1、λu、λf、λvAnd λρThe ratios of time, geometry, speed, additional external force, dynamic viscosity and density are constant respectively. The relationship between the prototype and model physical quantities and the equation of motion of the fluid can be expressed by the following equation:
Figure BDA0003211319220000022
Figure BDA0003211319220000023
multiply all terms of the equation by
Figure BDA0003211319220000024
Obtaining:
Figure BDA0003211319220000025
to ensure the similarity of the prototype and model fluid movements, the ratio of the physical quantities should satisfy:
Figure BDA0003211319220000031
therefore, dimensionless parameters of wind turbine blade aeroelastic wind tunnel test fluid motion similarity criteria are as follows:
Figure BDA0003211319220000032
namely, it is
Figure BDA0003211319220000033
St is the Strahaha number, and if the Straha numbers of the two flows are equal, the unsteady inertial force of the fluid is similar; for periodic unsteady flow, reflecting the similarity of the periodicity;
Figure BDA0003211319220000034
namely, it is
Figure BDA0003211319220000035
Re is Reynolds number; if the Reynolds numbers of the two flows are equal, the viscous forces of the fluids are similar; for turbulent flow with large Reynolds number, the inertia force plays a leading role, and the viscous force is relatively small;
Figure BDA0003211319220000036
namely, it is
Figure BDA0003211319220000037
Fr is Froude number; if the Froude numbers of the two flows are equal, the flowing gravity effects are similar, and the effect of gravity on the fluid is reflected; if the fluid is subjected to only gravity, and f is g, then
Figure BDA0003211319220000038
Namely, it is
Figure BDA0003211319220000039
Eu is Euler number.
In the second step, on the basis of obtaining the three-dimensional rigidity of waving, swinging and twisting of the composite material blade based on the composite section analysis, the wind turbine blade equivalent section design method establishes a wind turbine blade full-scale finite element model considering anisotropic composite laying materials, pre-bending of the blade, main beams, webs and special-shaped gluing and bonding details, and accurately solves the section characteristics of the wind turbine blade. And then, scaling conversion of the target section characteristics of the aeroelastic model of the wind turbine blade is carried out on the basis of the reasonable simplification similarity criterion of the aeroelastic model of the wind turbine blade. On the basis, the outer contour of a model target and the characteristics of the target section are taken as section design targets, the local size of the section and the component division are iteratively adjusted through a section topology optimization design method, and the gradual variation equivalent section of the aeroelastic model along the spanwise direction is obtained.
The invention has the following beneficial effects:
1) the method is suitable for designing and manufacturing the high-precision model for the wind turbine blade aeroelastic wind tunnel test.
2) The method can consider the similarity of the aeroelastic model reduced scales of the multi-order modes of the wind turbine blades, and accurately acquire the overall and local wind vibration characteristics.
3) The wind turbine blade aeroelastic model is manufactured by adopting wind turbine blade equivalent section topological optimization design and 3D high-precision printing, and has the advantages of short period, low manufacturing cost and higher precision.
Drawings
FIG. 1 is a schematic flow chart of a method for designing and manufacturing a gas bomb model according to the present invention;
FIG. 2 is a schematic diagram of the structural design of a model case of a gas bomb according to the present invention;
FIG. 3 is a schematic diagram comparing the structural rigidity distribution of the aeroelastic model case of the present invention;
FIG. 4 is a schematic diagram of a process for making a model case of a gas bomb in accordance with the present invention;
fig. 5 is a schematic diagram of a variation progressive equivalent cross-section method.
Wherein the reference numerals are: nylon leading edge 1, nylon trailing edge 2, nylon purlin 3, nylon connecting element 4, sponge gap 5, counterweight lead strip 6, frame section connecting rib 7 and rigid coupling base 8.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings.
The invention discloses a wind turbine blade aeroelastic wind tunnel test model and a manufacturing method thereof. Firstly, deducing a reasonable simplification similarity criterion of a wind turbine blade aeroelastic model based on motion equivalence; then, a variational progressive equivalent section method (VPES) is provided to design a high-precision equivalent wind power blade model special-shaped section, and the aeroelastic model design of the blade aeroelastic model pneumatic-rigidity-quality scale mapping is realized; and finally, obtaining a aeroelastic model frame section by means of high-precision 3D printing, splicing the full-length model by connecting ribs, filling a pneumatic coat in the hollow area, pasting a balance weight lead sheet on the rear edge, pasting a rough strip on the front edge and filling a gap to finish the production of the aeroelastic model frame section/coat.
The wind turbine blade aeroelastic model reasonably simplifies the similarity criterion: the design and the manufacture of the aeroelastic model of the wind turbine blade are very difficult, the requirements of similar aerodynamic appearance, similar structural inherent modes and same damping characteristics are met, and the consistent similarity of dimensionless parameters such as Storehal number (St), Reynolds number (Re), Froude number (Fr), Cauchi number (Ca), density ratio, damping ratio and the like is generally required. Reynolds number similarity in actual scale test is difficult to satisfy, and the existing research finds that due to the self-modulus characteristic of the flow field, when Re of the aeroelasticity test is larger than 4 multiplied by 105Then, the turbulence degree and the flow velocity distribution of the flow field are not changed along with the increase of Re, and an artificial transition can be performed to meet the Reynolds number effect equivalence. In the structural wind vibration motion equation, the elastic modulus and the structural section characteristic are combined to be embodied by rigidity, so that the structural wind vibration motion equation is equivalent to the structural wind vibration motion equation by the similarity of the rigidity. Similar gravity action of Floude number reaction flow due to vertical wind power blade under shutdown conditionThe effects of gravity in the sheet fluid-solid coupling response are only of minor importance, and the Froude numbers can be neglected to be similar when difficult to satisfy. The wind power blade aeroelastic model is designed based on the simplified similarity criterion, only the reduced scale similarity of the geometric parameters, the mass, the rigidity and the damping ratio of the appearance needs to be met, and the model overall rigidity distribution similarity design method adopts the natural vibration frequency, the modal vibration mode and the mass distribution of a simulation structure. Considering wind power blade aeroelastic wind tunnel test working condition and boundary layer wind tunnel blockage filtering requirement, selecting the geometric scale ratio of the model as CLAnd (3) calculating the rest dimensionless parameters by using a similarity criterion, wherein the rest dimensionless parameters are obtained by calculating, and a reasonable simplified similarity criterion list of the specific wind turbine blade aeroelastic model is given in the table 1.
TABLE 1 reasonable simplified similarity criterion list of aeroelastic model of wind turbine blade
Figure BDA0003211319220000051
The method for designing the equivalent section of the aeroelastic model comprises the following steps: the bearing capacity of the real wind turbine blade is provided by an integrated structure of the composite laying layer and the main beam, and the wind turbine blade aeroelastic model cannot adopt a rigid main beam-airfoil frame section aeroelastic model manufacturing method of the traditional wing due to the structural characteristics of the three-core shaft (the mass center, the shear center, the geometric center and the neutral shaft) such as the continuous change characteristic of the span length and the pre-bending. Considering the similarity accuracy and the manufacturing difficulty comprehensively, the present embodiment provides a Variable Progressive Equivalent Section (VPES) method for the aeroelastic model manufacturing of the wind turbine blade. The method is characterized in that a variational progressive beam section method (VABS) is introduced to aeroelastic model design, the three-way (waving, swinging and twisting) rigidity spanwise distribution rule of a real composite layer wind power blade is extracted, then rigidity scaling is carried out, and then the aeroelastic model sectional design with the most consistent three-way rigidity is completed through iterative optimization.
The method for manufacturing the aeroelastic model frame section/coat comprises the following steps: the model making is based on polyamide fiber materials (nylon) and adopts 3D printing to make a frame section of the aeroelastic model, and connecting rib insertion piers are preset at two ends of the frame section for segmented embedded connection. When the section of the aeroelastic model of the wind turbine blade is designed into a beam frame consisting of a front edge and a rear edge which are encircled to form an airfoil shape and upper and lower purlins, wherein the bearing capacity of the aeroelastic model of the blade is provided by a full-length front edge and the upper and lower purlins, the specific size and the airfoil position are determined by iterative design, the rear edge of a frame section is paved with lead sheets to complete the adjustment of the centroid and the rotational inertia of the section, and high-density foam is filled in a subsection gap to perform damping compensation and prevent collision in the vibration process to increase additional rigidity; for the model subsection that the tip tail end is limited by the thickness and the section design cannot be realized, the model subsection is formed by connecting a rigidity force section and an appearance wing section, and high-density foam is filled in gaps. The hollow area between the front and rear edges of the wing-shaped frame section nylon and the upper and lower purlines is filled with light wood chips and polished, so that the pneumatic appearance is closed.
The wind turbine blade aeroelastic model reasonably simplifies dimensionless parameters of a similarity criterion: the motion similarity of the aeroelastic wind tunnel test needs to simultaneously meet the similarity of fluid motion and structure motion.
1) The fluid motion is similar, the air in the flow field of the wind turbine blade is low-speed, incompressible and Newtonian viscous flow, and the fluid motion equation is
Figure BDA0003211319220000061
In the formula ui(i is 1, 2, 3) in a rectangular coordinate system x (x), respectively1)，y(x2)，z(x3) A directional fluid motion velocity component; f. ofiIn a rectangular coordinate system x (x)1)，y(x2)，z(x3) A directional fluid force; ρ is the air density; p is the pressure intensity; v is the dynamic viscosity of air, and v is mu/rho; x (x)1)，y(x2)，z(x3) Respectively, the three main axial directions of the rectangular coordinate system.
Reference symbol λXX representing a modelmOf the same entity as XaRatio of (i.e.. lambda.)x＝Xm/XaVariables with x are model variables, prototype variables without x, λt、λ1、λu、λf、λvAnd λρRespectively time, geometry, speed, additional external force and powerThe ratio of viscosity to density is constant. The relationship between the prototype and model physical quantities and the equation of motion of the fluid can be expressed by the following equation:
Figure BDA0003211319220000062
Figure BDA0003211319220000063
multiply all terms of the equation by
Figure BDA0003211319220000064
Obtaining:
Figure BDA0003211319220000065
to ensure the similarity of the prototype and model fluid movements, the ratio of the physical quantities should satisfy:
Figure BDA0003211319220000066
therefore, dimensionless parameters of wind turbine blade aeroelastic wind tunnel test fluid motion similarity criteria are as follows:
Figure BDA0003211319220000067
namely, it is
Figure BDA0003211319220000068
St is the strora-haar number, and if the strora-haar numbers of the two flows are equal, the unsteady inertial forces of the fluids are similar. For periodic unsteady flows, the similarity of their periodicity is reflected.
Figure BDA0003211319220000069
Namely, it is
Figure BDA00032113192200000610
Re is Reynolds number. If the reynolds numbers of the two flows are equal, the viscous forces of the fluids are similar. For turbulent flows with large reynolds numbers, inertial forces dominate, viscous forces are relatively small, and the requirement for equal reynolds numbers can be relatively low.
Figure BDA0003211319220000071
Namely, it is
Figure BDA0003211319220000072
Fr is Froude number. If the Froude numbers of the two flows are equal, the flowing gravity effects are similar, and the effect of gravity on the fluid is reflected. If the fluid is subjected to only gravity, f ═ f*When the result is g, then
Figure BDA0003211319220000073
Namely, it is
Figure BDA0003211319220000074
Eu is Euler number. The pressure in the fluid is not an inherent physical property of the fluid and its value depends on other parameters and therefore is not a similar norm but a function of other similar norms, i.e. the euler number is not a similar condition but a similar result.
2) The structure motion is similar, and the flutter motion equation of the aeroelastic model structure of the wind turbine blade is as follows:
[-ω2M+(1+ig)K-1/2ρV2bA]q＝0
in the formula (I); omega is the flutter frequency, unit 1/s; m is generalized mass in kg; k is generalized stiffness, in N/m; g is a damping coefficient, dimensionless; rho is the atmospheric density in kg/m2(ii) a V is the flying speed, unit m/s; b is a reference length, in m; a is a generalized aerodynamic coefficient and is dimensionless; q is the generalized coordinate, m.
Reference symbol λXX representing a modelmOf the same entity as XaRatio of (i.e.. lambda.)x＝Xm/XaThen the equation of motion of the model can be written as:
Figure BDA0003211319220000075
in order to ensure the similarity of the prototype and model structure motions, the ratio of the physical quantities needs to satisfy:
Figure BDA0003211319220000076
to satisfy the above formula, λ is requiredg1 is ═ 1; if the flow field of the model and the object meets the condition that the flow motion is similar, lambda is determinedA＝1。
Figure BDA0003211319220000077
Considering that the reduction frequency is the same, λbλω/λV1, so that the dimensionless parameters of the aeroelastic wind tunnel test structure motion similarity criterion of the wind turbine blade are as follows:
the mass ratio is as follows:
Figure BDA0003211319220000078
the stiffness ratio is:
Figure BDA0003211319220000079
a Variational progressive equivalent section method (VPES) of the method for designing an equivalent section of a gas-bomb model: based on the existing section characteristic calculation method (variational progressive beam section analysis method, VABS method) of the composite material blade of the large wind turbine, a wind turbine blade aeroelastic model design method (variational progressive equivalent section method, VPES) is provided. Firstly, establishing a wind turbine blade full-scale finite element model considering all details of anisotropic composite layer materials, prebending of blades, main beams, webs, special-shaped gluing and bonding and the like by means of a VABS method, and accurately solving the section characteristics of the wind turbine blade. And then, scaling conversion of the target section characteristics of the aeroelastic model of the wind turbine blade is carried out on the basis of the reasonable simplification similarity criterion of the aeroelastic model of the wind turbine blade. On the basis, the outer contour of a model target and the characteristics of the target section are taken as section design targets, the local size of the section and the component division are iteratively adjusted through a section topology optimization design method, and the gradual variation equivalent section of the aeroelastic model along the spanwise direction is obtained. Fig. 5 shows a schematic diagram of the variation progressive equivalent section method (VPES).
The following is explained with a specific example:
in the embodiment, a 15 MW-level ultra-long flexible wind power blade pre-researched by the American renewable energy laboratory (NREL) is taken as a research object. The power generated by the concept level wind turbine is 15MW, and the concept level wind turbine is a world maximum power wind turbine which can be found at present. The diameter of a wind wheel is 240m, the height of a hub is 150m, the total length of a blade is 117m, the maximum chord length is 5.77m, the length is 27.2m (23.3%) of the extension, the blade is pre-bent by 4m, and the blade is designed by adopting a DTU FFA-W3 airfoil family. The blade mass 65.252t, the blade centroid at 26.8m, and Table 2 gives a short profile of the geometry of the ultra-long compliant blade.
Table 215 MW level wind turbine blade geometric parameter list
Figure BDA0003211319220000081
The method for designing and manufacturing the aeroelastic model shown in the figure 1 is adopted, and the section design of the equivalent beam is carried out according to the reasonable simplified similarity criterion of the aeroelastic model of the wind turbine blade and the aeroelastic model equivalent section design method.
The schematic structural design diagram of the aeroelastic model case shown in fig. 2 is that the scale ratio is 1: 70. the adopted section design types are a beam frame mode and a wind turbine blade aeroelastic wind tunnel test model with the height of 1.67m printed by nylon 3D segmentation. The aeroelastic model of the wind turbine blade comprises a nylon front edge 1, a nylon rear edge 2, nylon purlines 3, nylon connecting elements 4, sponge gaps 5, counterweight lead strips 6, frame section connecting ribs 7 and a fixedly connected base 8.
According to the thickness of the blade, the aeroelastic model of the wind turbine blade is divided into two parts along the spanwise direction, namely a beam frame section part and a blade tip connecting element part. In the beam frame section, the thickness of the blade is divided into three parts of a front edge 1, a rear edge 2 and a purline 3, the front edge and the purline are used as stress beam frames to provide flapping, swinging and torsional rigidity, and a torsional center is determined. The blade tip connecting element part is not limited by thickness to realize the section design, and is formed by connecting a front edge 1, a rear edge 2 and a connecting element 4, wherein high-density foam is filled in the gap of the connecting element, and the connecting element is used as a stress section to provide swinging, swinging and torsion rigidity and determine a torsion center. Wherein the leading edge shape size, the purlin shape size and its position are determined by iterative optimization. And a counterweight lead strip 6 is laid on the rear edge 2 of each frame section to complete the adjustment of the mass center and the rotational inertia of the section, and a high-density sponge is filled in the segmented sponge gap 5 to perform damping compensation and prevent collision in the vibration process so as to increase the additional rigidity.
A comparative illustration of structural rigidity distribution of a aeroelastic model case as depicted in fig. 3.
The schematic diagram of the process for making the aeroelastic model case is shown in fig. 4. The model making is based on polyamide fiber materials (nylon) and adopts 3D printing to make the aeroelastic model frame section, and frame section splicing is realized by inserting piers for frame section connecting ribs 7 preset at two ends of the frame section to perform segmented embedding and connecting. The hollow area between the front and rear edges of the wing-shaped frame section nylon and the upper and lower purlines is filled with light wood chips and polished, so that the pneumatic appearance is closed. And finally, completing the aeroelastic wind tunnel test model manufacture of the wind turbine blade after the compensation measure of the rough strip at the front edge and the paint spraying.
The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may be made by those skilled in the art without departing from the principle of the invention.

Claims (7)

1. A method for manufacturing a wind turbine blade aeroelastic wind tunnel test model is characterized by comprising the following steps: the method comprises the following steps:
step one, deducing a reasonable simplified similarity criterion of a wind turbine blade aeroelastic model based on motion equivalence;
step two, taking the equivalent section design method as the wind turbine blade aeroelastic model equivalent section design method,
and step three, taking the aeroelastic model frame section/coat manufacturing method as a wind turbine blade aeroelastic model manufacturing method, and further manufacturing a wind turbine blade aeroelastic wind tunnel test model.
2. The method for manufacturing the aeroelastic wind tunnel test model of the wind turbine blade according to claim 1, which is characterized in that: in the first step, the reasonable simplification similarity criterion comprises wind speed ratio, time ratio and frequency ratio which are derived by fluid motion similarity; density ratio and damping ratio required by the same dimensionless parameter; the structure motion is similar to the derived mass ratio and stiffness ratio.
3. The method for manufacturing the aeroelastic wind tunnel test model of the wind turbine blade according to claim 1, which is characterized in that: and in the second step, the wind turbine blade aeroelastic model equivalent section design method comprises the steps of obtaining the waving, swinging and twisting three-way rigidity of the composite material blade based on composite section analysis, and obtaining an aeroelastic wind tunnel test model structure meeting the three-way scale rigidity and three-center-to-one-axis requirements based on topological optimization equivalent section design.
4. The method for manufacturing the aeroelastic wind tunnel test model of the wind turbine blade according to claim 1, which is characterized in that: in the third step, the aeroelastic model frame section/coat manufacturing method comprises the steps of 3D printing aeroelastic model frame sections in a segmented mode, completing splicing of full-length structural frame sections through connecting ribs, achieving pneumatic appearance sealing after enclosure filling, and finally completing manufacturing of a wind turbine blade aeroelastic wind tunnel test model after pneumatic compensation measures.
5. The method for manufacturing the aeroelastic wind tunnel test model of the wind turbine blade according to claim 1, which is characterized in that: and in the second step, designing an equivalent section by adopting a through long beam frame, a rigid main beam or an enclosure frame section.
6. The method for manufacturing the aeroelastic wind tunnel test model of the wind turbine blade as claimed in claim 2, wherein the method comprises the following steps: the fluid motion is similar to that of the prior art, specifically: the air in the flow field of the wind turbine blade is low-speed, incompressible and Newtonian viscous flow, and the fluid motion equation is as follows:
Figure FDA0003211319210000011
in the formula ui(i is 1, 2, 3) in a rectangular coordinate system x (x), respectively1),y(x2),z(x3) A directional fluid motion velocity component; f. ofiIn a rectangular coordinate system x (x)1),y(x2),z(x3) A directional fluid force; ρ is the air density; p is the pressure intensity; nu is the dynamic viscosity of air, and nu is mu/rho; x (x)1),y(x2),z(x3) Are respectively a three-principal axial direction of a rectangular coordinate system;
reference symbol λXX representing a modelmOf the same entity as XaRatio of (i.e.. lambda.)X＝Xm/XaVariables with x are model variables, prototype variables without x, λt、λl、λu、λf、λvAnd λρThe ratios of time, geometry, speed, additional external force, dynamic viscosity and density are constant respectively; the relationship between the prototype and the model physical quantities and the equation of motion of the fluid can be expressed by
t＝λtt*，
Figure FDA0003211319210000021
p＝λpp*，f＝λff*，v＝λvv*，ρ＝λρρ*
Figure FDA0003211319210000022
Multiply all terms of the equation by
Figure FDA0003211319210000023
Obtaining:
Figure FDA0003211319210000024
to ensure the similarity of the prototype and model fluid movements, the ratio of the physical quantities should satisfy:
Figure FDA0003211319210000025
therefore, dimensionless parameters of wind turbine blade aeroelastic wind tunnel test fluid motion similarity criteria are as follows:
Figure FDA0003211319210000026
namely, it is
Figure FDA0003211319210000027
St is the Strahaha number, and if the Straha numbers of the two flows are equal, the unsteady inertial force of the fluid is similar; for periodic unsteady flow, reflecting the similarity of the periodicity;
Figure FDA0003211319210000028
namely, it is
Figure FDA0003211319210000029
Re is Reynolds number; if the Reynolds numbers of the two flows are equal, the viscous forces of the fluids are similar; for turbulent flow with large Reynolds number, the inertia force plays a leading role, and the viscous force is relatively small;
Figure FDA00032113192100000210
namely, it is
Figure FDA00032113192100000211
Fr is Froude number; if the Froude numbers of the two flows are equal, the flowing gravity effects are similar, and the effect of gravity on the fluid is reflected; if the fluid is subjected to only gravity, and f is g, then
Figure FDA00032113192100000212
Namely, it is
Figure FDA00032113192100000213
Eu is Euler number.
7. The method for manufacturing the aeroelastic wind tunnel test model of the wind turbine blade as claimed in claim 3, wherein the method comprises the following steps: in the second step, on the basis of obtaining the three-dimensional rigidity of waving, swinging and twisting of the composite material blade based on the composite section analysis, the wind turbine blade equivalent section design method establishes a wind turbine blade full-scale finite element model considering anisotropic composite laying materials, pre-bending of the blade, main beams, webs and special-shaped gluing and bonding details, and accurately solves the section characteristics of the wind turbine blade; then, scaling conversion of the target section characteristics of the aeroelastic model of the wind turbine blade is carried out on the basis of the reasonable simplified similarity criterion of the aeroelastic model of the wind turbine blade; on the basis, the outer contour of a model target and the characteristics of the target section are taken as section design targets, the local size of the section and the component division are iteratively adjusted through a section topology optimization design method, and the gradual variation equivalent section of the aeroelastic model along the spanwise direction is obtained.
CN202110931276.1A 2021-08-13 2021-08-13 Method for manufacturing aeroelastic wind tunnel test model of wind turbine blade Active CN113504027B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110931276.1A CN113504027B (en) 2021-08-13 2021-08-13 Method for manufacturing aeroelastic wind tunnel test model of wind turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110931276.1A CN113504027B (en) 2021-08-13 2021-08-13 Method for manufacturing aeroelastic wind tunnel test model of wind turbine blade

Publications (2)

Publication Number Publication Date
CN113504027A true CN113504027A (en) 2021-10-15
CN113504027B CN113504027B (en) 2022-07-08

Family

ID=78016119

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110931276.1A Active CN113504027B (en) 2021-08-13 2021-08-13 Method for manufacturing aeroelastic wind tunnel test model of wind turbine blade

Country Status (1)

Country Link
CN (1) CN113504027B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113945357A (en) * 2021-10-28 2022-01-18 南京航空航天大学 Method and device for predicting flutter critical wind speed of wind turbine blade

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3791207A (en) * 1972-06-19 1974-02-12 Nasa Wind tunnel model and method
CN105653763A (en) * 2015-12-22 2016-06-08 中国航天空气动力技术研究院 Design method of static aeroelasticity test model
CN206387558U (en) * 2017-01-18 2017-08-08 武汉大学 A kind of multiple degrees of freedom air spring pole skeleton for high-rise building wind tunnel experiment
CN109902384A (en) * 2019-02-28 2019-06-18 上海交通大学 A kind of wind energy conversion system flexible blade pre-bending pre-twist design method based on air spring pole
CN110298093A (en) * 2019-06-19 2019-10-01 上海交通大学 A kind of floating blower scale model performance similar vanes design method
CN110717217A (en) * 2019-09-11 2020-01-21 安徽省艺凌模型设计有限公司 Static aeroelastic test model design method
CN111783325A (en) * 2020-05-28 2020-10-16 东南大学 Method for manufacturing cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation
CN112197936A (en) * 2020-10-30 2021-01-08 中国商用飞机有限责任公司北京民用飞机技术研究中心 Flutter wind tunnel model of airplane winglet and manufacturing method thereof

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3791207A (en) * 1972-06-19 1974-02-12 Nasa Wind tunnel model and method
CN105653763A (en) * 2015-12-22 2016-06-08 中国航天空气动力技术研究院 Design method of static aeroelasticity test model
CN206387558U (en) * 2017-01-18 2017-08-08 武汉大学 A kind of multiple degrees of freedom air spring pole skeleton for high-rise building wind tunnel experiment
CN109902384A (en) * 2019-02-28 2019-06-18 上海交通大学 A kind of wind energy conversion system flexible blade pre-bending pre-twist design method based on air spring pole
CN110298093A (en) * 2019-06-19 2019-10-01 上海交通大学 A kind of floating blower scale model performance similar vanes design method
CN110717217A (en) * 2019-09-11 2020-01-21 安徽省艺凌模型设计有限公司 Static aeroelastic test model design method
CN111783325A (en) * 2020-05-28 2020-10-16 东南大学 Method for manufacturing cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation
CN112197936A (en) * 2020-10-30 2021-01-08 中国商用飞机有限责任公司北京民用飞机技术研究中心 Flutter wind tunnel model of airplane winglet and manufacturing method thereof

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
柯世堂等: "大型双曲冷却塔气弹模型风洞试验和响应特性", 《建筑结构学报》 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113945357A (en) * 2021-10-28 2022-01-18 南京航空航天大学 Method and device for predicting flutter critical wind speed of wind turbine blade

Also Published As

Publication number Publication date
CN113504027B (en) 2022-07-08

Similar Documents

Publication Publication Date Title
EP3509944B1 (en) Blade or wing
Armstrong et al. Flow separation on a high Reynolds number, high solidity vertical axis wind turbine with straight and canted blades and canted blades with fences
CN102012953B (en) CFD (computational fluid dynamics)/CSD (circuit switch data) coupled solving nonlinear aeroelasticity simulation method
CN106840572B (en) A kind of near space high aspect ratio flexible flier wind tunnel test data correcting method
CN109885908B (en) Novel feather wing bionic ventilation flapping wing system and multi-vortex interference mechanism analysis method
Communier et al. Experimental validation of a new morphing trailing edge system using Price–Païdoussis wind tunnel tests
El Mouhsine et al. Aerodynamics and structural analysis of wind turbine blade
CN108052772A (en) A kind of geometrical non-linearity static aeroelastic analysis method based on structure reduced-order model
Tang et al. Gust response for flexibly suspended high-aspect ratio wings
Boorsma et al. Rotor experiments in controlled conditions continued: New Mexico
Meng et al. Aerodynamic effects of corrugation in flapping insect wings in forward flight
De Gregorio Flow field characterization and interactional aerodynamics analysis of a complete helicopter
CN113504027B (en) Method for manufacturing aeroelastic wind tunnel test model of wind turbine blade
Modaress-Aval et al. A comparative study of nonlinear aeroelastic models for high aspect ratio wings
Dehaeze et al. Hovering rotor computations using an aeroelastic blade model
Alulema et al. Degree of deformation and power consumption of compliant and rigid-linked mechanisms for variable-camber morphing wing UAVs
CN112580241A (en) Nonlinear aeroelastic dynamic response analysis method based on structure reduced order model
Xie et al. Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High‐Aspect‐Ratio Wing
Park et al. Loosely coupled multibody dynamics–CFD analysis for a rotor in descending flight
Rajakumar et al. Computational fluid dynamics of wind turbine blade at various angles of attack and low Reynolds number
Park et al. Comprehensive multibody dynamics analysis for rotor aeromechanics predictions in descending flight
Lee et al. Damping mechanism model for fatigue testing of a full-scale composite wind turbine blade, Part 1: Modeling
Yoon et al. Control reversal and torsional divergence analysis for a high-aspect-ratio wing
Keye Fluid-structure-coupled analysis of a transport aircraft and comparison to flight data
Sitorus et al. Hydrodynamic characteristics of cambered NACA0012 for flexible-wing application of a flapping-type tidal stream energy harvesting system

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant