CN102004838A - Method for determining wind turbine blade structure based on finite difference method - Google Patents

Method for determining wind turbine blade structure based on finite difference method Download PDF

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CN102004838A
CN102004838A CN2010105931938A CN201010593193A CN102004838A CN 102004838 A CN102004838 A CN 102004838A CN 2010105931938 A CN2010105931938 A CN 2010105931938A CN 201010593193 A CN201010593193 A CN 201010593193A CN 102004838 A CN102004838 A CN 102004838A
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pneumatic equipment
blades made
equipment blades
blade
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康传明
张卫民
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China Academy of Aerospace Aerodynamics CAAA
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Abstract

The invention discloses a method for determining a wind turbine blade structure based on a finite difference method. The structure design by the finite difference method is coincident with the design process of the blade. Pneumatic profile of the blade is designed firstly and then the structural design is carried out on the premise of determining the pneumatic profile so as to ensure the pneumatic efficiency and structural strength of the blade. By using the finite difference method, three-dimensional design is changed into two-dimensional design so as to simplify the design complexity. Due to the adoption of a reverse finite difference method, the deformation control design of the blade is realized. By taking theoretical section flexural rigidity as a design target, the section area is restrained so as to realize the light-weight design of the blade.

Description

A kind of wind turbine blade structure based on method of finite difference is determined method
Technical field
The present invention relates to a kind of wind turbine blade structure and determine method, belong to the wind turbine blade structure design field, be used for the glass fibre/carbon fiber composite structure design of large scale wind power machine blade or large span based on method of finite difference.
Background technology
Along with developing rapidly of the The Enlargement Tendency of pneumatic equipment blades made, set up a kind of fast, blade design method is very necessary reliably.At present, in the structured design process blade is reduced to the multi-cavity semi-girder with aerofoil section, the deviser will consider that the material thickness of blade distributes, and will guarantee to satisfy the strength and stiffness requirement simultaneously, difficulty is bigger, often needs iteration repeatedly just can finish satisfactory structural design scheme.According to glass fibre the high characteristics of carbon fiber strength, the rigidity of structure is the design consideration of composite structure often.Still blade is reduced to semi-girder in the design of modern large scale wind power machine blade, finishes the structural design of blade by iterating, this traditional design method not only needs the long design cycle, and is also very high to the requirement of design experiences.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provide a kind of design cycle weak point, the wind turbine blade structure based on method of finite difference simple to operate to determine method.
Technical solution of the present invention is: a kind of wind turbine blade structure based on method of finite difference is determined method, realizes by following steps:
The first step according to the ply sequence of pneumatic equipment blades made, utilizes blanket formula curve method to obtain the longitudinal elasticity constant E of pneumatic equipment blades made;
Second step was divided into the n five equilibrium with pneumatic equipment blades made by length, obtained n xsect, and every part of length is h;
In the 3rd step, according to the aerodynamic configuration of pneumatic equipment blades made, obtain the aerodynamic loading of n xsect of pneumatic equipment blades made, and obtain the moment M of n xsect according to aerodynamic loading i, i=1,2 ... n;
In the 4th step,, utilize polynomial curve to obtain the deflection v of a pneumatic equipment blades made n xsect according to the distortion of pneumatic equipment blades made i, i=1,2 ... n;
In the 5th step, go on foot the moment M that obtains according to the 3rd iWith the 4th deflection v that obtains of step i, utilize the method for finite difference of formula (1) to obtain the bendind rigidity EI of a pneumatic equipment blades made n xsect i, i=1,2 ... n,
v i + 1 - 2 v i + v i - 1 = h 2 M i EI i - - - ( 1 ) ;
In the 6th step, utilized for the 5th step obtained bendind rigidity EI i, the theoretical inertia that calculates n xsect of pneumatic equipment blades made is apart from I i, i=1,2 ... n;
The 7th step, according to the theoretical inertia of n xsect apart from I iThe two-dimensional structure of determining a pneumatic equipment blades made n xsect is that material thickness distributes,
A7.1, if pneumatic equipment blades made be the straight blade structure, then utilize formula (2) to obtain the thickness y of a pneumatic equipment blades made n xsect i, i=1,2 ... n,
I i＝∫∫y i 2dx idy i (2)
X wherein iBe the two-dimensional section width of i pneumatic equipment blades made xsect, y iThe material thickness of i pneumatic equipment blades made xsect;
A7.2, if pneumatic equipment blades made is the box beam blade construction, the material thickness distribution that then utilizes formula (3) to obtain a pneumatic equipment blades made n xsect is y Ij,
I i = Σ i = 1 n Σ j = 1 J ∫ ∫ y ij 2 dx ij dy ij - - - ( 3 )
I=1 wherein, 2 ... n, j=1,2 ... J, J are the number of different materials thickness on the single xsect, x IjBe the two-dimensional section width of j material thickness of i pneumatic equipment blades made xsect, y IjBe j material thickness of i pneumatic equipment blades made xsect;
In the 8th step,, determine the three-dimensional structure of pneumatic equipment blades made according to the two-dimensional structure of the 7th pneumatic equipment blades made n xsect that obtain of step.
The described second step n is not less than 20.
Number J 〉=3 of different materials thickness on the single xsect in the described steps A 7.2.
The present invention compared with prior art beneficial effect is:
(1) the present invention utilizes the structural design of method of finite difference to meet the design process of blade, promptly at first designs the aerodynamic configuration of blade, secondly carries out structural design under the prerequisite that aerodynamic configuration is determined, thereby has guaranteed the pneumatic efficiency and the structural strength of blade;
(2) the present invention adopts method of finite difference, has realized the conversion from the three-dimensional design to the two-dimensional design, has simplified the design complexity;
(3) the present invention has adopted reverse method of finite difference, has realized the controlled design of deformable blade;
(4) the present invention adopts theoretical cross section bendind rigidity as design object, and area of section can be used as constraint, helps realizing the blade light-weight design.
Description of drawings
Fig. 1 is a process flow diagram of the present invention;
Fig. 2 is the cross sectional representation at the embodiment of the invention 25% blade radius place;
Fig. 3 is the cross sectional representation at the embodiment of the invention 50% blade radius place.
Embodiment
The present invention realizes by following steps as shown in Figure 1:
1,, utilize blanket formula curve method to obtain the longitudinal elasticity constant E of pneumatic equipment blades made according to the ply sequence of given pneumatic equipment blades made.
Pneumatic equipment blades made is a composite structure, at first determines a kind of layering type when designing earlier, presses [60/20/20] ply sequence for 0 °/90 °/± 45 ° as comparing tradition, tries to achieve the longitudinal elasticity constant E of shop layer according to blanket formula curve method.
Blanket formula curve method principle is referring to Wang Yaoxian, " composite structure design ", Chemical Industry Press, September calendar year 2001.
2, pneumatic equipment blades made is divided into the n five equilibrium by length, obtains n xsect, every part of length is h.
For large-scale MW class pneumatic equipment blades made, more reasonable in order to make design, n is generally greater than 20.
3,, obtain the aerodynamic loading of n xsect of pneumatic equipment blades made, and obtain the moment M of n xsect according to aerodynamic loading according to the aerodynamic configuration of given pneumatic equipment blades made i, i=1,2 ... n.
Aerodynamic loading obtains according to momentum foline theory, and concrete principle is referring to document: He Dexin " Wind Engineering and aerodynamics ", National Defense Industry Press, in January, 2006.
4,, utilize polynomial curve to obtain the deflection v of a pneumatic equipment blades made n xsect according to the distortion of known pneumatic equipment blades made i, i=1,2 ... n.
Vane design of wind turbines becomes beam of uniform strength structure, and the deformation curve of blade elastic shaft can be represented with quadratic polynomial, all is 0 in conjunction with blade original position corner and distortion, so the deformation curve of blade elastic shaft can be expressed as v=ax 2Wherein a is a coefficient, according to the length of blade and blade tip deflection determine (the blade tip distortion determines according to the wind energy conversion system overall design, perhaps according under the static situation of blade with the tower span from 40% determine), v is a deflection, and x is that the blade exhibition is to length (dividing the length direction in cross section).
The polynomial curve principle is referring to document: Liu Hongwen, " mechanics of materials ", Higher Education Publishing House, in January, 2004.
5, according to moment M iWith deflection v i, utilize the method for finite difference of formula (1) to obtain the bendind rigidity EI of a pneumatic equipment blades made n xsect i, i=1,2 ... n,
v i + 1 - 2 v i + v i - 1 = h 2 M i EI i - - - ( 1 ) .
The method of finite difference that the present invention uses be a kind of fast, the blade construction method for designing of half value, this method for designing is design criteria with rigidity, intensity is for checking criterion, and this method is at first according to the bending load and the deformation condition of blade, obtain along the blade exhibition to moment of inertia distribute; Secondly, apart from distribution, the material thickness of design blade profile distributes according to the geometric shape design proposal of blade and inertia; At last, according to the design in each cross section, form the structural design scheme of blade.The design proposal of utilizing method of finite difference to form meets beam of uniform strength theory, make the blade exhibition to stress evenly distribute, the blade light for designing quality, that fatigue lifetime good, viability is strong provides technological approaches.
6, utilize bendind rigidity EI i, the theoretical inertia that calculates n xsect of pneumatic equipment blades made is apart from I i, i=1,2 ... n.
7, according to the theoretical inertia of n xsect apart from I iThe two-dimensional structure of determining a pneumatic equipment blades made n xsect is that material thickness distributes.
The structure of general pneumatic equipment blades made is the box beam structure and waits the wall thickness structure, introduces respectively below.
(1) pneumatic equipment blades made is the straight blade structure
Utilize formula (2) to obtain the thickness y of a pneumatic equipment blades made n xsect i, i=1,2 ... n,
I i＝∫∫y i 2dx idy i (2)
X wherein iBe the two-dimensional section width of i pneumatic equipment blades made xsect, y iThe material thickness of i pneumatic equipment blades made xsect.
(2) pneumatic equipment blades made is the box beam blade construction
It is y that the material thickness that utilizes formula (3) to obtain a pneumatic equipment blades made n xsect distributes Ij,
I i = Σ i = 1 n Σ j = 1 J ∫ ∫ y ij 2 dx ij dy ij - - - ( 3 )
I=1 wherein, 2 ... n, j=1,2 ... J, J are the number of different materials thickness on the single xsect, and general J 〉=3.x IjBe the two-dimensional section width of j material thickness of i pneumatic equipment blades made xsect, y IjBe j material thickness of i pneumatic equipment blades made xsect.
With the i xsect is example, if be divided into four thickness areas, the inertia of first thickness area is apart from I I1'=∫ ∫ y I1Dx I1Dy I1, the inertia of second thickness area is apart from I I2'=∫ ∫ y I2Dx I2Dy I2, the inertia of the 3rd thickness area is apart from I I3'=∫ ∫ y I3Dx I3Dy I3, the inertia of the 4th thickness area is apart from I I4'=∫ ∫ y I4Dx I4Dy I4, the inertia distance of i xsect then
Figure BSA00000389344100052
The two-dimensional section width x of first thickness area wherein I1Get about i xsect aerofoil profile 15% chord length, the two-dimensional section width of second thickness area is between i xsect aerofoil profile 15%～50% chord length, and the 3rd, the 4th thickness area installation and design requires to choose after cross section aerofoil profile 50% chord length, order
Figure BSA00000389344100053
The theoretical inertia of the i xsect that equals to obtain in the step 6 is apart from I i, determine the one-tenth-value thickness 1/10 of each thickness area.
8,, determine the three-dimensional structure of pneumatic equipment blades made according to the two-dimensional structure of all pneumatic equipment blades made xsects.
Describe blade construction of the present invention in detail below in conjunction with instantiation and determine method.
According to the result that 1.5WM pneumatic equipment blades made aerodynamic configuration is optimized, the population parameter of blade is as shown in table 1, and possible maximum load is as shown in table 2, and blade shop layer is by [60/20/20] shop stratum proportion, material adopts glass/epoxy composite material, and material longitudinal elasticity constant E is 43GPa:
Table 1 blade population parameter
Figure BSA00000389344100061
The maximum load that table 2 blade bears
Figure BSA00000389344100062
20 cross sections have been divided in the blade profile design in the design.
According to the notion of the beam of uniform strength, the amount of deflection of blade profile is as shown in table 3, and it is as shown in the table to obtain the cross section bendind rigidity according to step 5.
Design result
Carry out the blade profile design according to each cross section bendind rigidity that obtains and elasticity modulus of materials, obtained blade profile and exhibition to distribution of material, only the cross section with 25%, 50% blade radius place (these two positions are complete aerofoil profiles) is an example, and shown in Fig. 2,3, other cross sections are similar.Fig. 2 is that erect-position is that cross section, the Fig. 3 at 1750mm place is erect-position 8750mm place xsect.
After finishing the material thickness design in each cross section, can finish the structural design of whole blade according to each position, cross section.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.

Claims (3)

1. the wind turbine blade structure based on method of finite difference is determined method, it is characterized in that realizing by following steps:
The first step according to the ply sequence of pneumatic equipment blades made, utilizes blanket formula curve method to obtain the longitudinal elasticity constant E of pneumatic equipment blades made;
Second step was divided into the n five equilibrium with pneumatic equipment blades made by length, obtained n xsect, and every part of length is h;
In the 3rd step, according to the aerodynamic configuration of pneumatic equipment blades made, obtain the aerodynamic loading of n xsect of pneumatic equipment blades made, and obtain the moment M of n xsect according to aerodynamic loading i, i=1,2 ... n;
In the 4th step,, utilize polynomial curve to obtain the deflection v of a pneumatic equipment blades made n xsect according to the distortion of pneumatic equipment blades made i, i=1,2 ... n;
In the 5th step, go on foot the moment M that obtains according to the 3rd iWith the 4th deflection v that obtains of step i, utilize the method for finite difference of formula (1) to obtain the bendind rigidity EI of a pneumatic equipment blades made n xsect i, i=1,2 ... n,
v i + 1 - 2 v i + v i - 1 = h 2 M i EI i - - - ( 1 ) ;
In the 6th step, utilized for the 5th step obtained bendind rigidity EI i, the theoretical inertia that calculates n xsect of pneumatic equipment blades made is apart from I i, i=1,2 ... n;
The 7th step, according to the theoretical inertia of n xsect apart from I iThe two-dimensional structure of determining a pneumatic equipment blades made n xsect is that material thickness distributes,
A7.1, if pneumatic equipment blades made be the straight blade structure, then utilize formula (2) to obtain the thickness y of a pneumatic equipment blades made n xsect i, i=1,2 ... n,
I i＝∫∫y i 2dx idy i (2)
X wherein iBe the two-dimensional section width of i pneumatic equipment blades made xsect, y iThe material thickness of i pneumatic equipment blades made xsect;
A7.2, if pneumatic equipment blades made is the box beam blade construction, the material thickness distribution that then utilizes formula (3) to obtain a pneumatic equipment blades made n xsect is y Ij,
I i = Σ i = 1 n Σ j = 2 J ∫ ∫ y ij 2 dx ij dy ij - - - ( 3 )
I=1 wherein, 2 ... n, j=1,2 ... J, J are the number of different materials thickness on the single xsect, x IjBe the two-dimensional section width of j material thickness of i pneumatic equipment blades made xsect, y IjBe j material thickness of i pneumatic equipment blades made xsect;
In the 8th step,, determine the three-dimensional structure of pneumatic equipment blades made according to the two-dimensional structure of the 7th pneumatic equipment blades made n xsect that obtain of step.
2. a kind of wind turbine blade structure based on method of finite difference according to claim 1 is determined method, it is characterized in that: the described second step n is not less than 20.
3. a kind of wind turbine blade structure based on method of finite difference according to claim 1 is determined method, it is characterized in that: number J 〉=3 of different materials thickness on the single xsect in the described steps A 7.2.
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Cited By (8)

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CN102322407A (en) * 2011-08-30 2012-01-18 重庆大学 Aerodynamic configuration collaborative design method for wind turbine blade
CN102680226A (en) * 2012-06-12 2012-09-19 中国科学院工程热物理研究所 Method for evaluating performance of wing profile special for horizontal axis wind turbine
CN103049621A (en) * 2013-01-14 2013-04-17 合肥工业大学 Design method of detachable connecting structure based on TRIZ (Theory of Intensive Problem solving)
CN105508147A (en) * 2015-12-28 2016-04-20 山东理工大学 Bending moment matching method for single-point fatigue loading test of wind blade
CN105844022A (en) * 2016-03-25 2016-08-10 兰州理工大学 Design method for wind turbine blade added with prestress
CN111159929A (en) * 2019-11-26 2020-05-15 华北电力大学 Composite material blade structure dynamics numerical simulation method
CN111339609A (en) * 2018-12-19 2020-06-26 中国航发商用航空发动机有限责任公司 Blade, method and device for constructing thickness distribution of blade, and computer-readable storage medium
CN111475872A (en) * 2020-03-26 2020-07-31 青岛海尔空调器有限总公司 Air conditioner air deflector optimization design method and device

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CN101158990A (en) * 2007-11-29 2008-04-09 北京航空航天大学 Big and small blade integral leaf disc structural integrity fluid-solid coupling integrated design method
CN101428686A (en) * 2008-12-23 2009-05-13 北京航空航天大学 Method for structural design of coaxal helicopter composite material blade
CN101532906A (en) * 2009-04-27 2009-09-16 东南大学 Method for analyzing fluid dynamics and structural mechanics of wind generator blades

Patent Citations (3)

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Publication number Priority date Publication date Assignee Title
CN101158990A (en) * 2007-11-29 2008-04-09 北京航空航天大学 Big and small blade integral leaf disc structural integrity fluid-solid coupling integrated design method
CN101428686A (en) * 2008-12-23 2009-05-13 北京航空航天大学 Method for structural design of coaxal helicopter composite material blade
CN101532906A (en) * 2009-04-27 2009-09-16 东南大学 Method for analyzing fluid dynamics and structural mechanics of wind generator blades

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102322407A (en) * 2011-08-30 2012-01-18 重庆大学 Aerodynamic configuration collaborative design method for wind turbine blade
CN102680226A (en) * 2012-06-12 2012-09-19 中国科学院工程热物理研究所 Method for evaluating performance of wing profile special for horizontal axis wind turbine
CN102680226B (en) * 2012-06-12 2014-06-04 中国科学院工程热物理研究所 Method for evaluating performance of wing profile special for horizontal axis wind turbine
CN103049621A (en) * 2013-01-14 2013-04-17 合肥工业大学 Design method of detachable connecting structure based on TRIZ (Theory of Intensive Problem solving)
CN105508147A (en) * 2015-12-28 2016-04-20 山东理工大学 Bending moment matching method for single-point fatigue loading test of wind blade
CN105508147B (en) * 2015-12-28 2017-12-08 山东理工大学 Wind electricity blade single-point fatigue loading tests moment of flexure matching process
CN105844022A (en) * 2016-03-25 2016-08-10 兰州理工大学 Design method for wind turbine blade added with prestress
CN111339609A (en) * 2018-12-19 2020-06-26 中国航发商用航空发动机有限责任公司 Blade, method and device for constructing thickness distribution of blade, and computer-readable storage medium
CN111339609B (en) * 2018-12-19 2023-07-21 中国航发商用航空发动机有限责任公司 Blade, method and device for constructing thickness distribution of blade, and computer-readable storage medium
CN111159929A (en) * 2019-11-26 2020-05-15 华北电力大学 Composite material blade structure dynamics numerical simulation method
CN111475872A (en) * 2020-03-26 2020-07-31 青岛海尔空调器有限总公司 Air conditioner air deflector optimization design method and device
CN111475872B (en) * 2020-03-26 2024-01-16 青岛海尔空调器有限总公司 Air conditioner air deflector optimal design method and device

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