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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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 present invention relates to a kind of large scale wind power machine blade, particularly relate to a kind of fan blade main beam overlay thickness Optimization Design.
Background technology
Global warming problem is day by day serious, and renewable and clean energy resource gets most of the attention.Wind energy, as available a kind of green energy resource, has huge development prospect.Effectively utilizing of wind energy depends on wind energy conversion system, and as the device of Direct Acquisition wind energy, pneumatic equipment blades is the important component part of wind energy conversion system.The trend of wind energy conversion system is towards development of maximizing.Although the power that the increase of blade can increase wind energy conversion system also brings along the burden in a lot of structure simultaneously, leaf weight increases, and causes that vane stress increases.These changes can bring a series of impact, and therefore wind turbine blade structure design is particularly significant for blade design.
For large-scale (MW class) pneumatic equipment blades, the structure of blade is mainly made up of girder and eyelid covering and some other structure, and blade is usually shell structure, and girder part is main force structure.Megawatt wind power machine generally runs under environment complicated and changeable, blade is subject to aerodynamic load, centrifugal force load and gravitational load, the increase of blade dimensions can cause the increase of own wt, not merely makes blade cost increase and also can tie down wind energy conversion system operational efficiency simultaneously.
Therefore, adopt the programming of genetic algorithm binding modulesization that blade design is divided into four parts for large scale wind power machine blade, it is achieved the optimization of blade overlay thickness to be designed, makes blade can realize the reduction of leaf weight under meeting rigidity condition.
Leaf weight can be effectively alleviated by blade optimum design of laminate layup, realize wind energy conversion system further to maximize and improve the power of single wind energy conversion system simultaneously, and alleviating of leaf weight can alleviate himself burden and this means that blade can reduce certain fatigue load and increase the service life.In the long term, blade overlay thickness optimization is designed to effectively save cost.
Summary of the invention
It is an object of the invention to provide a kind of pneumatic equipment blades girder optimum design of laminate layup method.
The present invention is pneumatic equipment blades girder optimum design of laminate layup method, the steps include:
(1) blade aerodynamic formal parameter is determined, blade girder is cell type girder, and blade section is that girder adds stressed-skin construction form, and blade obtains n cross section along exhibition to discretization, and each area of section is divided into three part eyelid covering area A1, main beam cap area A2With shear web area A3, the area of the entire profile is A=A1+A2+A3；
(2) as follows according to eyelid covering areal calculation section product moment formula in step (1):
、；
Further, the section centre of form is equal to:,；
Blade section the moment of inertia is equal to、、, the moment of inertia under main shaft coordinate just can be obtained by coordinate transformation；
(3) calculating blade loading and internal force, under normal operating conditions, blade is subject to aerodynamic force, centrifugal force and self gravitation；
(4) can calculating aerodynamic force moment of flexure and moment of torsion according to sectional properties parameter calculated in step (2), formula is as follows:
,；
；
In formula,Blade aerodynamic center,For the blade section centre of twist；
(5) moment of flexure of gravitational load suffered by blade and moment of torsion can be calculated as follows:
,
；
Wherein、The respectively reduced density of blade and the area of section,For acceleration of gravity,For blade rotational orientation angle,For blade center of gravity coordinate；
(6) moment of flexure of centrifugal force load suffered by blade and torque arithmetic formula are as follows:
,；
；
Wherein,、For bladeSection place center of gravity；
(7) in step (3), step (4) and step (5), calculated moment of flexure moment of torsion is corresponding section coordinate system, further, section internal force is transformed into section position of form center coordinate system, including the first main shaftWith the second main shaft, blade bending normal stresses computing formula is:
,；
Wherein, M is moment of flexure I is correspondenceAxle, the i.e. the moment of inertia of the first main shaft,Represent the maximum of cross section discrete point off-axis；
(8) each blade profile is divided into three parts: eyelid covering, main beam cap and shear web；Employings etc. are for designing and calculating blade overlay thickness, and eyelid covering adopts two-way cloth laying, and the laying of the two-way cloth of eyelid covering provides enough shear strengths, and computing formula is:
；
In formula,It isIndividual withThe width of panel between individual web；For two-way cloth thickness in monolayer；For the minimum number of layers that two-way cloth monolayer is laid；
(9) girder unidirectional cloth laying, unidirectional cloth overlay thickness can calculate according to criterion of strength, and specific formula for calculation is as follows:
；
Above formula shows to obtain different calculated rigidity according to different overlay thickness, and when the different overlay thickness substitution calculated rigidity of above formula disclosure satisfy that maximum stress demand, vane thickness then meets requirement；
(10) according to genetic algorithm, blade overlay thickness is set to variable, according to above-mentioned steps and order, reference section geometrical property parameter, section stress, stress suffered by blade, is met the overlay thickness of condition finally according to criterion of strength；
When iterative computation blade overlay thickness, choose and meet requirement of strength and the overlay thickness that makes leaf quality minimum as output result.
Compared with prior art, the present invention adopts parameter numerous and diverse in modularized processing blade construction design process to calculate to the present invention, and blade construction design part is divided into four parts.In conjunction with genetic algorithm, set suitable rigidity and strength condition, carry out blade overlay thickness optimization design with the weight of blade for target.The Optimized Program of the present invention, for the overlay thickness in specific run operating condition design cross section.Result of calculation shows, the blade after optimization is not under losing the premise of original rigidity and intensity, and leaf weight declines to some extent, it was demonstrated that the practicality of Optimized model and effectiveness.
Accompanying drawing explanation
Fig. 1 blade overlay thickness seismic responses calculated flow chart, Fig. 2 blade section structural representation, Fig. 3 gives blade girder overlay thickness and optimizes front and back contrast, and Fig. 4 gives blade front and rear edge overlay thickness and optimizes front and back contrast.
Detailed description of the invention
The present invention adopts the following technical scheme that
The first step, selected suitable aerodynamic configuration parameter, become n fragment to obtain your cross section equidistant for blade dispersion, given initial girder overlay thickness parameter, calculate the area of each section；
Second step, reference section area moment Sx,Sy, centre of form Xc,Yc, and the moment of inertia Ix,Iy,Ixy；
3rd step, calculates moment of flexure and the moment of torsion of aerodynamic force, gravity and centrifugal force suffered by blade；
4th step, calculates the leaf quality line density rigidity as fitness value and given overlay thickness, and compares the superseded overlay thickness being unsatisfactory for and requiring with maximum stress.
5th step, obtains optimum results by the certain step number of iteration and chooses optimal value output.
Based on above method, it is optimized design for a certain 1.5MW pneumatic equipment blades, Fig. 1 gives blade overlay thickness and optimizes calculation flow chart, Fig. 2 gives blade section ply angles schematic diagram, Fig. 3 gives blade girder overlay thickness and optimizes front and back contrast, Fig. 4 gives blade front and rear edge overlay thickness and optimizes front and back contrast, and the present invention is that detailed description partly belongs to general knowledge as well known to those skilled in the art.
As it is shown in figure 1, the present invention is pneumatic equipment blades girder optimum design of laminate layup method, the steps include:
(1) blade aerodynamic formal parameter is determined, blade girder is cell type girder, and blade section is that girder adds stressed-skin construction form, and blade obtains n cross section along exhibition to discretization, and each area of section is divided into three part eyelid covering area A1, main beam cap area A2With shear web area A3, the area of the entire profile is A=A1+A2+A3；
(2) as follows according to eyelid covering areal calculation section product moment formula in step (1):
、；
Further, the section centre of form is equal to:,；
Blade section the moment of inertia is equal to、、, the moment of inertia under main shaft coordinate just can be obtained by coordinate transformation；
(3) calculating blade loading and internal force, under normal operating conditions, blade is subject to aerodynamic force, centrifugal force and self gravitation；
(4) can calculating aerodynamic force moment of flexure and moment of torsion according to sectional properties parameter calculated in step (2), formula is as follows:
,；
；
In formula,Blade aerodynamic center,For the blade section centre of twist；
(5) moment of flexure of gravitational load suffered by blade and moment of torsion can be calculated as follows:
,
；
Wherein、The respectively reduced density of blade and the area of section,For acceleration of gravity,For blade rotational orientation angle,For blade center of gravity coordinate；
(6) moment of flexure of centrifugal force load suffered by blade and torque arithmetic formula are as follows:
,；
；
Wherein,、For bladeSection place center of gravity；
(7) in step (3), step (4) and step (5), calculated moment of flexure moment of torsion is corresponding section coordinate system, further, section internal force is transformed into section position of form center coordinate system, including the first main shaftWith the second main shaft, blade bending normal stresses computing formula is:
,；
Wherein, M is moment of flexure I is correspondenceAxle, the i.e. the moment of inertia of the first main shaft,Represent the maximum of cross section discrete point off-axis；
(8) each blade profile is divided into three parts: eyelid covering, main beam cap and shear web；Employings etc. are for designing and calculating blade overlay thickness, and eyelid covering adopts two-way cloth laying, and the laying of the two-way cloth of eyelid covering provides enough shear strengths, and computing formula is:
；
In formula,It isIndividual withThe width of panel between individual web；For two-way cloth thickness in monolayer；For the minimum number of layers that two-way cloth monolayer is laid；
(9) girder unidirectional cloth laying, unidirectional cloth overlay thickness can calculate according to criterion of strength, and specific formula for calculation is as follows:
；
Above formula shows to obtain different calculated rigidity according to different overlay thickness, and when the different overlay thickness substitution calculated rigidity of above formula disclosure satisfy that maximum stress demand, vane thickness then meets requirement；
(10) according to genetic algorithm, blade overlay thickness is set to variable, according to above-mentioned steps and order, reference section geometrical property parameter, section stress, stress suffered by blade, is met the overlay thickness of condition finally according to criterion of strength；
When iterative computation blade overlay thickness, choose and meet requirement of strength and the overlay thickness that makes leaf quality minimum as output result.
Claims (1)
1. pneumatic equipment blades girder optimum design of laminate layup method, it is characterised in that the steps include:
(1) blade aerodynamic formal parameter is determined, blade girder is cell type girder, and blade section is that girder adds stressed-skin construction form, and blade obtains n cross section along exhibition to discretization, and each area of section is divided into three part eyelid covering area A1, main beam cap area A2With shear web area A3, the area of the entire profile is A=A1+A2+A3；
(2) as follows according to eyelid covering areal calculation section product moment formula in step (1):
、；
Further, the section centre of form is equal to:,；
Blade section the moment of inertia is equal to、、, the moment of inertia under main shaft coordinate just can be obtained by coordinate transformation；
(3) calculating blade loading and internal force, under normal operating conditions, blade is subject to aerodynamic force, centrifugal force and self gravitation；
(4) can calculating aerodynamic force moment of flexure and moment of torsion according to sectional properties parameter calculated in step (2), formula is as follows:
,；
；
In formula,Blade aerodynamic center,For the blade section centre of twist；
(5) moment of flexure of gravitational load suffered by blade and moment of torsion can be calculated as follows:
,
；
Wherein、The respectively reduced density of blade and the area of section,For acceleration of gravity,For blade rotational orientation angle,For blade center of gravity coordinate；
(6) moment of flexure of centrifugal force load suffered by blade and torque arithmetic formula are as follows:
,；
；
Wherein,、For bladeSection place center of gravity；
(7) in step (3), step (4) and step (5), calculated moment of flexure moment of torsion is corresponding section coordinate system, further, section internal force is transformed into section position of form center coordinate system, including the first main shaftWith the second main shaft, blade bending normal stresses computing formula is:
,；
Wherein, M is moment of flexure I is correspondenceAxle, the i.e. the moment of inertia of the first main shaft,Represent the maximum of cross section discrete point off-axis；
(8) each blade profile is divided into three parts: eyelid covering, main beam cap and shear web；Employings etc. are for designing and calculating blade overlay thickness, and eyelid covering adopts two-way cloth laying, and the laying of the two-way cloth of eyelid covering provides enough shear strengths, and computing formula is:
；
In formula,It isIndividual withThe width of panel between individual web；For two-way cloth thickness in monolayer；For the minimum number of layers that two-way cloth monolayer is laid；
(9) girder unidirectional cloth laying, unidirectional cloth overlay thickness can calculate according to criterion of strength, and specific formula for calculation is as follows:
；
Above formula shows to obtain different calculated rigidity according to different overlay thickness, and when the different overlay thickness substitution calculated rigidity of above formula disclosure satisfy that maximum stress demand, vane thickness then meets requirement；
(10) according to genetic algorithm, blade overlay thickness is set to variable, according to above-mentioned steps and order, reference section geometrical property parameter, section stress, stress suffered by blade, is met the overlay thickness of condition finally according to criterion of strength；
When iterative computation blade overlay thickness, choose and meet requirement of strength and the overlay thickness that makes leaf quality minimum as output result.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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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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