CN105760629A - Lamination optimum design method of wind turbine blade main beam - Google Patents
Lamination optimum design method of wind turbine blade main beam Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000003475 lamination Methods 0.000 title abstract 6
- 238000005457 optimization Methods 0.000 claims abstract description 18
- 230000002068 genetic effect Effects 0.000 claims abstract description 6
- 239000010410 layer Substances 0.000 claims description 42
- 238000005452 bending Methods 0.000 claims description 19
- 238000004364 calculation method Methods 0.000 claims description 19
- 230000005484 gravity Effects 0.000 claims description 17
- 230000002457 bidirectional effect Effects 0.000 claims description 12
- 239000004744 fabric Substances 0.000 claims description 12
- 230000001133 acceleration Effects 0.000 claims description 3
- 238000010008 shearing Methods 0.000 claims description 3
- 239000002356 single layer Substances 0.000 claims description 3
- 230000009466 transformation Effects 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
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Abstract
The invention discloses a lamination optimum design method of a wind turbine blade main beam. The method comprises blade structure analysis: simplifying a blade into cantilever beam based on a beam and casing theory, and computing the blade sectional properties, load internal force, stress-strain and blade lamination thickness according to given blade parameters; genetic algorithm optimization: performing optimum design of wind turbine blade lamination thicknesses, determining lamination thickness of the blade in different positions by taking the minimum mass of the blade as a target according to the rigidity and the strength of the wind turbine blade. The method, aiming at specific environment, computes the lamination thickness of the blade through a written optimum design program. A computed result shows that the mass of the blade is reduced in the condition that the rigidity and strength of the blade are met, and an optimum model has practicability and effectiveness.
Description
Technical Field
The invention relates to a large-scale wind turbine blade, in particular to a layer thickness optimization design method for a main beam of a fan blade.
Background
The global warming problem is becoming more serious, and renewable clean energy sources are attracting attention. The wind energy is an available green energy and has great development prospect. The effective utilization of wind energy relies on wind turbines, the blades of which are important components, as a means of directly capturing wind energy. The trend of wind turbines is toward upsizing. The increase of the blades can increase the power of the wind turbine and bring a lot of structural burden, the weight of the blades is increased, and the stress of the blades is increased. These changes have a series of effects, so that the structural design of the wind turbine blade is very important for the blade design.
For a large (megawatt-level) wind turbine blade, the structure of the blade mainly comprises a main beam, a skin and other structures, the blade is generally a shell structure, and the main beam part is a main stressed structure. Megawatt wind turbines generally operate in complex and variable environments, blades are subjected to aerodynamic load, centrifugal load and gravity load, the increase of the size of the blades can lead to the increase of the weight of the blades, and the operating efficiency of the wind turbines can be affected while the cost of the blades is increased.
Therefore, the blade design is divided into four parts by combining genetic algorithm and modular programming aiming at the large wind turbine blade, the optimized design of the blade layer thickness is realized, and the weight of the blade can be reduced under the condition of meeting the rigidity requirement of the blade.
The weight of the blade can be effectively reduced through the optimized design of the blade layering, the large-scale wind turbine is further realized, the power of a single wind turbine is improved, the load of the blade can be reduced through the reduction of the weight of the blade, and the service life of the blade can be prolonged by reducing a certain fatigue load. In the long run, the cost can be effectively saved by optimally designing the thickness of the blade layer.
Disclosure of Invention
The invention aims to provide a wind turbine blade main beam laying layer optimization design method.
The invention relates to a wind turbine blade main beam laying layer optimization design method, which comprises the following steps:
(1) determining aerodynamic shape parameters of the blade, wherein a blade girder is a box-shaped girder, the blade section is in a girder and skin structure form, the blade is discretized in the spanwise direction to obtain n cross sections, and each section area is divided into three skin areas A1Area of main girder cap A2And shear web area A3The area of the whole cross section is A = A1+A2+A3；
(2) Calculating the sectional area moment formula according to the skin area in the step (1) as follows:
、；
further, the cross-sectional centroid is equal to:，；
blade section moment of inertia equal to、、The inertia moment under the main shaft coordinate can be obtained through coordinate transformation;
(3) calculating the load and the internal force of the blade, wherein the blade is subjected to aerodynamic force, centrifugal force and self gravity in a normal working state;
(4) and (3) calculating the aerodynamic bending moment and the aerodynamic torque according to the section geometric characteristic parameters calculated in the step (2), wherein the formula is as follows:
，；
；
in the formula,the aerodynamic center of the blade is provided with a plurality of blades,is the blade section torsion center;
(5) the bending moment and the torque of the gravity load borne by the blade can be calculated according to the following formulas:
，
；
wherein、Respectively the reduced density and the cross-sectional area of the blade,in order to be the acceleration of the gravity,in the form of the blade rotation azimuth angle,the coordinates of the gravity center of the blade are taken;
(6) the calculation formula of the bending moment and the torque of the centrifugal force load borne by the blade is as follows:
，；
；
wherein,、is a bladeThe center of gravity at the section;
(7) the bending moment and the torque obtained by calculation in the step (3), the step (4) and the step (5) correspond to a section coordinate system, and further, the section internal force is converted into a section centroid position coordinate system comprising a first main shaftAnd a second main shaftThe positive bending stress calculation formula of the blade is as follows:
，；
wherein M is bending moment I corresponding toThe moment of inertia of the shaft, i.e. the first main shaft,represents the maximum value of deviation of the discrete points of the cross section from the axis;
(8) the section of each blade is divided into three parts: skin, spar caps, and shear webs; the blade layer thickness is calculated by adopting an equal generation design, the covering adopts a bidirectional cloth layer, the covering bidirectional cloth layer provides enough shearing strength, and the calculation formula is as follows:
；
in the formula,is as followsIs first and secondThe width of the panel between webs;is the thickness of the bidirectional drape layer;the minimum number of layers for laying bidirectional cloth single layers;
(9) the thickness of the unidirectional cloth laying layer for the girder can be calculated according to the strength criterion, and the specific calculation formula is as follows:
；
the above formula shows that different calculated stiffness can be obtained according to different layer thicknesses, and when the stiffness obtained by substituting different layer thicknesses into the above formula can meet the maximum stress requirement, the blade thickness meets the requirement;
(10) according to a genetic algorithm, the thickness of the layering of the blade is set as a variable, according to the steps and the sequence, the geometric characteristic parameters of the section, the stress of the section and the stress of the blade are calculated, and finally the layering thickness meeting the conditions is obtained according to the strength criterion;
and when the thickness of the blade layer is calculated in an iterative manner, selecting the layer thickness which meets the strength requirement and enables the blade mass to be minimum as an output result.
Compared with the prior art, the method adopts the complicated parameter calculation in the process of modularizing the blade structure design, and divides the blade structure design part into four parts. And setting appropriate rigidity and strength conditions by combining a genetic algorithm, and carrying out blade layer thickness optimization design by taking the weight of the blade as a target. The optimization design program of the invention designs the thickness of the layer of the cross section aiming at the specific operating condition. The calculation result shows that the weight of the optimized blade is reduced on the premise of not losing the original rigidity and strength, and the practicability and effectiveness of the optimization model are proved.
Drawings
FIG. 1 is a flow chart of calculation of a blade layering thickness optimization model, FIG. 2 is a schematic view of a blade section structure, FIG. 3 shows comparison before and after optimization of blade girder layering thickness, and FIG. 4 shows comparison before and after optimization of blade leading and trailing edge layering thickness.
Detailed Description
The invention adopts the following technical scheme:
firstly, selecting proper aerodynamic configuration parameters, equidistantly dispersing blades into n segments to obtain your cross section, giving an initial main beam layer thickness parameter, and calculating the area of each section;
second, calculating the area moment S of the cross sectionx,SyCentroid Xc,YcAnd the moment of inertia Ix,Iy,Ixy；
Thirdly, calculating the bending moment and the torque of aerodynamic force, gravity and centrifugal force applied to the blade;
and fourthly, calculating the mass linear density of the blade as a fitness value and rigidity of the given layer thickness, and comparing the fitness value with the maximum stress to eliminate the layer thickness which does not meet the requirement.
And fifthly, obtaining an optimization result by iterating a certain number of steps and selecting an optimal value to output.
Based on the method, a certain 1.5MW wind turbine blade is taken as an example for optimization design, a blade layering thickness optimization calculation flow chart is given in figure 1, a blade section layering structure schematic diagram is given in figure 2, the blade main beam layering thickness optimization front-back comparison is given in figure 3, the blade front-back edge layering thickness optimization front-back comparison is given in figure 4, and the invention belongs to the common knowledge of technicians in the field for detailed description.
As shown in FIG. 1, the invention relates to a wind turbine blade main beam laying layer optimization design method, which comprises the following steps:
(1) determining aerodynamic shape parameters of the blade, wherein a blade girder is a box-shaped girder, the blade section is in a girder and skin structure form, the blade is discretized in the spanwise direction to obtain n cross sections, and each section surfaceIntegrated into three parts of skin area A1Area of main girder cap A2And shear web area A3The area of the whole cross section is A = A1+A2+A3；
(2) Calculating the sectional area moment formula according to the skin area in the step (1) as follows:
、；
further, the cross-sectional centroid is equal to:，；
blade section moment of inertia equal to、、The inertia moment under the main shaft coordinate can be obtained through coordinate transformation;
(3) calculating the load and the internal force of the blade, wherein the blade is subjected to aerodynamic force, centrifugal force and self gravity in a normal working state;
(4) and (3) calculating the aerodynamic bending moment and the aerodynamic torque according to the section geometric characteristic parameters calculated in the step (2), wherein the formula is as follows:
，；
；
in the formula,the aerodynamic center of the blade is provided with a plurality of blades,is the blade section torsion center;
(5) the bending moment and the torque of the gravity load borne by the blade can be calculated according to the following formulas:
，
；
wherein、Respectively the reduced density and the cross-sectional area of the blade,in order to be the acceleration of the gravity,in the form of the blade rotation azimuth angle,the coordinates of the gravity center of the blade are taken;
(6) the calculation formula of the bending moment and the torque of the centrifugal force load borne by the blade is as follows:
，；
；
wherein,、is a bladeThe center of gravity at the section;
(7) the bending moment and the torque obtained by calculation in the step (3), the step (4) and the step (5) correspond to a section coordinate system, and further, the section internal force is converted into a section centroid position coordinate system comprising a first main shaftAnd a second main shaftThe positive bending stress calculation formula of the blade is as follows:
，；
wherein M is bending moment I corresponding toThe moment of inertia of the shaft, i.e. the first main shaft,represents the maximum value of deviation of the discrete points of the cross section from the axis;
(8) the section of each blade is divided into three parts: skin, spar caps, and shear webs; the blade layer thickness is calculated by adopting an equal generation design, the covering adopts a bidirectional cloth layer, the covering bidirectional cloth layer provides enough shearing strength, and the calculation formula is as follows:
；
in the formula,is as followsIs first and secondThe width of the panel between webs;is the thickness of the bidirectional drape layer;the minimum number of layers for laying bidirectional cloth single layers;
(9) the thickness of the unidirectional cloth laying layer for the girder can be calculated according to the strength criterion, and the specific calculation formula is as follows:
；
the above formula shows that different calculated stiffness can be obtained according to different layer thicknesses, and when the stiffness obtained by substituting different layer thicknesses into the above formula can meet the maximum stress requirement, the blade thickness meets the requirement;
(10) according to a genetic algorithm, the thickness of the layering of the blade is set as a variable, according to the steps and the sequence, the geometric characteristic parameters of the section, the stress of the section and the stress of the blade are calculated, and finally the layering thickness meeting the conditions is obtained according to the strength criterion;
and when the thickness of the blade layer is calculated in an iterative manner, selecting the layer thickness which meets the strength requirement and enables the blade mass to be minimum as an output result.
Claims (1)
1. The wind turbine blade main beam laying optimization design method is characterized by comprising the following steps:
(1) determining aerodynamic shape parameters of the blade, wherein a blade girder is a box-shaped girder, the blade section is in a girder and skin structure form, the blade is discretized in the spanwise direction to obtain n cross sections, and each section area is divided into three skin areas A1Area of main girder cap A2And shear web area A3The area of the whole cross section is A = A1+A2+A3；
(2) Calculating the sectional area moment formula according to the skin area in the step (1) as follows:
、；
further, the cross-sectional centroid is equal to:，；
blade section moment of inertia equal to、、The inertia moment under the main shaft coordinate can be obtained through coordinate transformation;
(3) calculating the load and the internal force of the blade, wherein the blade is subjected to aerodynamic force, centrifugal force and self gravity in a normal working state;
(4) and (3) calculating the aerodynamic bending moment and the aerodynamic torque according to the section geometric characteristic parameters calculated in the step (2), wherein the formula is as follows:
，；
；
in the formula,the aerodynamic center of the blade is provided with a plurality of blades,is the blade section torsion center;
(5) the bending moment and the torque of the gravity load borne by the blade can be calculated according to the following formulas:
，
；
wherein、Respectively the reduced density and the cross-sectional area of the blade,in order to be the acceleration of the gravity,in the form of the blade rotation azimuth angle,the coordinates of the gravity center of the blade are taken;
(6) the calculation formula of the bending moment and the torque of the centrifugal force load borne by the blade is as follows:
，；
；
wherein,、is a bladeThe center of gravity at the section;
(7) the bending moment and the torque obtained by calculation in the step (3), the step (4) and the step (5) correspond to a section coordinate system, and further, the section internal force is converted into a section centroid position coordinate system comprising a first main shaftAnd a second main shaftThe positive bending stress calculation formula of the blade is as follows:
，；
wherein M is bending moment I corresponding toThe moment of inertia of the shaft, i.e. the first main shaft,represents the maximum value of deviation of the discrete points of the cross section from the axis;
(8) the section of each blade is divided into three parts: skin, spar caps, and shear webs; the blade layer thickness is calculated by adopting an equal generation design, the covering adopts a bidirectional cloth layer, the covering bidirectional cloth layer provides enough shearing strength, and the calculation formula is as follows:
；
in the formula,is as followsIs first and secondThe width of the panel between webs;is the thickness of the bidirectional drape layer;the minimum number of layers for laying bidirectional cloth single layers;
(9) the thickness of the unidirectional cloth laying layer for the girder can be calculated according to the strength criterion, and the specific calculation formula is as follows:
；
the above formula shows that different calculated stiffness can be obtained according to different layer thicknesses, and when the stiffness obtained by substituting different layer thicknesses into the above formula can meet the maximum stress requirement, the blade thickness meets the requirement;
(10) according to a genetic algorithm, the thickness of the layering of the blade is set as a variable, according to the steps and the sequence, the geometric characteristic parameters of the section, the stress of the section and the stress of the blade are calculated, and finally the layering thickness meeting the conditions is obtained according to the strength criterion;
and when the thickness of the blade layer is calculated in an iterative manner, selecting the layer thickness which meets the strength requirement and enables the blade mass to be minimum as an output result.
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Cited By (8)
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| CN109409013A (en) * | 2018-12-10 | 2019-03-01 | 国电联合动力技术有限公司 | A kind of low wind speed Wind turbines wind wheel intelligent optimized design method |
| CN110298097A (en) * | 2019-06-21 | 2019-10-01 | 中科国风科技有限公司 | A kind of fan blade of wind generating set Lay up design method |
| CN110500242A (en) * | 2019-08-26 | 2019-11-26 | 上海电气风电集团有限公司 | The girder and its core material of wind electricity blade and the laying method of plate |
| CN111832211A (en) * | 2020-07-27 | 2020-10-27 | 内蒙古工业大学 | Rigidity optimization method for composite fiber wind turbine blade |
| CN112329278A (en) * | 2019-07-16 | 2021-02-05 | 内蒙古工业大学 | Method for optimizing layering parameters of wind turbine blade skin |
| CN112966351A (en) * | 2021-03-08 | 2021-06-15 | 三一重能股份有限公司 | Wind power blade root layering design method and wind power blade root structure |
| CN114770977A (en) * | 2022-06-17 | 2022-07-22 | 成都飞机工业（集团）有限责任公司 | Design method, device and equipment of automatic wire laying tool and storage medium |
| CN117436344A (en) * | 2023-11-10 | 2024-01-23 | 沈阳工业大学 | Wind turbine blade structure optimization design method based on parameterization description |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109409013A (en) * | 2018-12-10 | 2019-03-01 | 国电联合动力技术有限公司 | A kind of low wind speed Wind turbines wind wheel intelligent optimized design method |
| CN109409013B (en) * | 2018-12-10 | 2023-02-24 | 国电联合动力技术有限公司 | Intelligent optimization design method for wind wheel of low-wind-speed wind turbine generator |
| CN110298097A (en) * | 2019-06-21 | 2019-10-01 | 中科国风科技有限公司 | A kind of fan blade of wind generating set Lay up design method |
| CN110298097B (en) * | 2019-06-21 | 2023-07-18 | 中科国风科技有限公司 | Wind turbine blade layering design method of wind generating set |
| CN112329278A (en) * | 2019-07-16 | 2021-02-05 | 内蒙古工业大学 | Method for optimizing layering parameters of wind turbine blade skin |
| CN112329278B (en) * | 2019-07-16 | 2022-09-02 | 内蒙古工业大学 | Method for optimizing layering parameters of wind turbine blade skin |
| CN110500242A (en) * | 2019-08-26 | 2019-11-26 | 上海电气风电集团有限公司 | The girder and its core material of wind electricity blade and the laying method of plate |
| CN111832211B (en) * | 2020-07-27 | 2023-07-07 | 内蒙古工业大学 | Rigidity optimization method for composite fiber wind turbine blade |
| CN111832211A (en) * | 2020-07-27 | 2020-10-27 | 内蒙古工业大学 | Rigidity optimization method for composite fiber wind turbine blade |
| CN112966351A (en) * | 2021-03-08 | 2021-06-15 | 三一重能股份有限公司 | Wind power blade root layering design method and wind power blade root structure |
| WO2022188372A1 (en) * | 2021-03-08 | 2022-09-15 | 三一重能股份有限公司 | Wind power blade root layering design method and wind power blade root structure |
| CN114770977A (en) * | 2022-06-17 | 2022-07-22 | 成都飞机工业（集团）有限责任公司 | Design method, device and equipment of automatic wire laying tool and storage medium |
| CN114770977B (en) * | 2022-06-17 | 2022-10-25 | 成都飞机工业（集团）有限责任公司 | Design method, device and equipment of automatic fiber laying tool and storage medium |
| CN117436344A (en) * | 2023-11-10 | 2024-01-23 | 沈阳工业大学 | Wind turbine blade structure optimization design method based on parameterization description |
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