CN110220688A - Method for testing fatigue for blade of wind-driven generator - Google Patents
Method for testing fatigue for blade of wind-driven generator Download PDFInfo
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- CN110220688A CN110220688A CN201910588939.7A CN201910588939A CN110220688A CN 110220688 A CN110220688 A CN 110220688A CN 201910588939 A CN201910588939 A CN 201910588939A CN 110220688 A CN110220688 A CN 110220688A
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- G—PHYSICS
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Abstract
The invention discloses a kind of method for testing fatigue for blade of wind-driven generator, comprising the following steps: mounted angle sensor and foil gauge on blade；Apply different size of static load respectively in the blade tip of blade, acquires corresponding torsion angle and strain value；The torsion angle and strain value of blade are analyzed, unit torsion angle and strain value relationship are obtained；Dynamic load is applied to blade, acquires the torsion angle and strain value of blade；Calculate blade strain value caused by the unit torque of corresponding torsion angle in dynamic calibration；The strain value as caused by torque is eliminated, the strain value that the blade is generated in dynamic calibration by moment of flexure is obtained；The relation function that moment of flexure and strain when dynamic calibration are obtained by analyzing, obtains result in testing fatigue.The present invention obtains the relationship of moment of flexure and blade strain, more accurately blade fatigue test result can be obtained by eliminating the blade influence of torque to blade Strain-coupled in dynamic calibration.
Description
Technical field
The present invention relates to technical field of wind power generation, in particular to a kind of testing fatigue side for blade of wind-driven generator
Method.
Background technique
With wind power generating set high-power trend, the enlargement development of wind electricity blade is driven in terms of inherence.Fatigue
Test is the key link of large-scale blade pattern verifying.The fatigue load of blade be with load moment of flexure on blade profile or
The form of power provides, and the Cumulative Fatigue Damage of blade is counted with the strain data of material.Therefore, fatigue is carried out to blade
Test needs to establish the relationship between the moment of flexure of blade and strain.
The calibration mode in industry is (leeward in the front and rear edges and the face PS (windward side) girder of blade and the face SS at present
Face) erection of main beam foil gauge, by applying load in blade tip position, the transmitting between moment of flexure and strain on acquisition blade profile
Function.But when carrying out dynamic circulation load to blade using excitational equipment, in addition to moment of flexure, it is also easy to introduce torque, so that leaf
Vibration shape when vibration shape and dynamic of the piece in static state is inconsistent, causes blade in static demarcating, the front and rear edges of blade profile or
The strain of person PS face girder and the face SS girder and the transmission function of moment of flexure cannot really reflect feelings of the blade in dynamically load
Condition.
There was only several meters of blade for length, the influence of torque is little, can use above-mentioned traditional test method.But
It is, as blade the more is made the more big, to reach tens meters of large-scale blade for length, torque when blade vibration influences more it
Seriously, the accumulated damage on blade profile cannot be really reflected using classic fatigue test method.If using traditional blade
Method for testing fatigue, when strain loading deficiency in testing fatigue, testing fatigue cannot cover the accumulation of fatigue damage of blade, make
Blade reliability decrease；When straining overload in testing fatigue, the fatigue strength Redundancy Design of blade construction will cause, increase leaf
Sheet weight, so that the economy of blower is deteriorated.
Summary of the invention
The technical problem to be solved by the present invention is in order to overcome in the prior art to blade carry out testing fatigue when torque
Influence to blade strain obtains the relationship than more actually moment of flexure and blade strain, to obtain more accurately fatigue survey
Test result provides a kind of method for testing fatigue of blade for wind-driven generator.
The present invention is to solve above-mentioned technical problem by following technical proposals:
A kind of method for testing fatigue for blade of wind-driven generator, it is characterized in that, comprising the following steps:
S1, mounted angle sensor and foil gauge are distinguished in the first crucial section of the blade and the second crucial section,
The x-axis of the obliquity sensor is the axial direction of the blade, and the y-axis of the obliquity sensor is the front and rear edge side of the blade
To；
S2, apply different size of static load respectively in the blade tip of the blade blade is made to twist, pass through
The obliquity sensor and the foil gauge acquire the described first crucial section and the second crucial section respectively and mark in static state
The periodically torsion angle and strain value of the blade；
S3, finite element model analysis is carried out by torsion angle to the blade and strain value, calculates described first and closes
The unit torque in the key section stress value relationship with the described second crucial section respectively, obtains one with reference to coefficient；
S4, exciting force is issued by excitational equipment to blade application dynamic load, when the vibration amplitude of the blade
Stablize and when reaching target call, by the obliquity sensor and the foil gauge acquire respectively the described first crucial section and
The torsion angle and strain value of described second crucial section blade in dynamic calibration；
S5, coefficient is referred to by described obtained in step S3, calculates the blade and is accordingly reversed in dynamic calibration
Strain value caused by angular unit torque；
S6, when the blade to be carried out to dynamic calibration in step s 4 the strain value of acquisition subtract obtained in step S5 by
Strain value caused by torque obtains the strain value that the blade is generated in dynamic calibration by moment of flexure；
S7, in conjunction with finite element model analysis, decouple the influence of moment of flexure and torque couple to strain, obtain curved when dynamic calibration
The relation function of square and strain then obtains result of the blade in testing fatigue；
Wherein: the described first crucial section is the maximum chord length section of the blade, blade root section from rounded transitional to the wing
Dangerouse cross-section when shape region, the overlap joint transitional region of structural material not of the same race or structure design, the described second crucial section
Position is the face PS girder, the face SS girder, the face PS rear, the face SS rear, blade inlet edge.
Preferably, the dangerouse cross-section when structure designs includes static strength and the minimum region of fatigue strength safety coefficient
Or stability coefficient lower region.
Preferably, the obliquity sensor is equipped with multiple, corresponds respectively and be mounted on multiple described first and crucial cut
Face.
Preferably, first pass through after step S2 obtains torsion angle, then other described first are calculated by formula and crucial is cut
Unit torque corresponding to the torsion angle in face, then carry out step S3 in finite element model analysis, obtain unit torque with
The relationship of stress value；
Wherein, the formula are as follows:
In formula:
α1For the torsion angle of blade root, initial value 0；
αi, the torsion angle in previous section；
αi+1, the torsion angle in latter section；
I, i=1,2 ..., n are corresponding section serial number, and n is the last one section；
T, torque；
Δ l, cross-sectional length；
GIpi, corresponding torsional rigidity of section；
The torsion stiffness GI in the crucial section of the blade each described firstpiIt is being set with cross-sectional length Δ l by the blade
The architectural characteristic of timing obtains.
Preferably, the described first crucial section is the maximum chord length section of the blade.
Preferably, the vibration frequency of the excitational equipment is 0.3~0.8Hz.
Preferably, the parameter request of the obliquity sensor is as follows: angle measurement range is -60 °~60 °, and resolution ratio is
0.01 °, sample frequency is 20~40Hz.
Preferably, the obliquity sensor is acceleration transducer.
On the basis of common knowledge of the art, above-mentioned each optimum condition, can any combination to get each preferable reality of the present invention
Example.
The positive effect of the present invention is that: the present invention is used for the method for testing fatigue of blade of wind-driven generator to leaf
Piece carry out testing fatigue when, by eliminate the blade influence of torque to blade Strain-coupled in dynamic calibration, obtain moment of flexure with
The relationship of blade strain, can be obtained more accurately blade fatigue test result, the testing fatigue suitable for large-scale blade.
Detailed description of the invention
Fig. 1 is the flow chart in the present invention for the method for testing fatigue of the blade of wind-driven generator.
Fig. 2 is the structural schematic diagram to twist under blade portion's load effect outside in the present invention.
Fig. 3 is the structure chart of the installation site of foil gauge in the present invention.
Description of symbols:
Obliquity sensor installation site 11
The face PS girder 21
The face SS girder 22
The face PS rear 23
The face SS rear 24
Blade inlet edge 25
Specific embodiment
The embodiment for further illustrating the present invention below by the mode of embodiment, but therefore not limiting the present invention to
Among range.
As shown in Figure 1 to Figure 3, the method for testing fatigue of a kind of blade for wind-driven generator of the invention comprising
Following steps:
Step S1, mounted angle sensor and foil gauge are distinguished in the first crucial section of blade and the second crucial section,
The x-axis of obliquity sensor is the axial direction of blade, and the y-axis of obliquity sensor is the front and rear edge direction of blade；
Step S2, applying different size of static load respectively in the blade tip of blade makes blade twist, and passes through inclination angle
Sensor and foil gauge acquire the first crucial section and the second crucial section respectively and the torsion angle of blade and answer in static demarcating
Variate；
Step S3, by the torsion angle and strain value progress finite element model analysis to blade, first crucial section is calculated
The unit torque in the face stress value relationship with the second crucial section respectively, obtains one with reference to coefficient；
Step S4, exciting force is issued by excitational equipment and dynamic load is applied to blade, when the vibration amplitude of blade is stablized
And when reaching target call, the first crucial section and the second crucial section are acquired dynamic by obliquity sensor and foil gauge respectively
The torsion angle and strain value of blade when state is demarcated；
Step S5, by referring to coefficient obtained in step S3, blade corresponding torsion angle in dynamic calibration is calculated
Strain value caused by unit torque；
In this step, the relationship of the torque and strain value that are obtained by blade in static load derives blade dynamic
The stress value generated when state load by torque.
Step S6, when blade to be carried out to dynamic calibration in step s 4 the strain value of acquisition subtract obtained in step S5 by
Strain value caused by torque obtains the strain value that blade is generated in dynamic calibration by moment of flexure；
In this step, the stress value generated after the torque measured and moment of flexure coupling is subtracted into the stress generated by torque
Value decouples the stress value of torque, the distribution of the available strain value generated by moment of flexure.This step is eliminated mainly for reaching
The purpose of torque influence when blade vibration, so that the strain obtained when blade vibration really reflects bending moment level.
Step S7, in conjunction with finite element model analysis, the influence of moment of flexure and torque couple to strain is decoupled, dynamic calibration is obtained
When moment of flexure and strain relation function, then obtain result of the blade in testing fatigue.
In this step, in conjunction with finite element model analysis, the influence of moment of flexure and torque couple to strain is decoupled, dynamic is obtained
The relation function of moment of flexure and strain when calibration, the Goodman diagram of bond material, for assessing the Cumulative Fatigue Damage of blade.
The method for testing fatigue of blade for wind-driven generator of the invention passes through when carrying out testing fatigue to blade
The blade influence of torque to blade Strain-coupled in dynamic calibration is eliminated, the relationship of moment of flexure and blade strain is obtained, can be obtained
More accurately blade fatigue test result, the testing fatigue suitable for large-scale blade.
The torsion angle in the crucial section when present invention is vibrated by pilot blade is asked in conjunction with the torsion stiffness information of blade
Solve the torsional deflection distribution of blade.According to finite element model, the face PS of the corresponding blade of unit windup-degree is extracted
The Strain Distribution of girder 21, the face SS girder 22, the face PS rear 23, the face SS rear 24, blade inlet edge 25.It is utilized in blade calibration
Above data waves the influence with shimmy moment of flexure eliminating torque to blade.It is waved or shimmy so that calibration strain really reflects
Moment of flexure eliminates the influence of torque couple.The damage of the front and rear edge of blade increases torsion angle and surveys in Static Leaf and dynamic calibration
The testing fatigue scaling scheme of examination is conducive to the Cumulative Fatigue Damage counted in test result and really reflects that the fatigue of blade is strong
The case where spending, preventing insufficient structural fatigue Intensity Design or redundancy, improves the reliability of blade.
In the present embodiment, the first crucial section is the maximum chord length section of blade, blade root section from rounded transitional to wing
One or more of dangerouse cross-section when region, the overlap joint transitional region of structural material not of the same race or structure design, for example, can
To select the maximum chord length section of blade as the first crucial section, because the torsion angle that blade herein generates is relative to other
Section is bigger, when selecting the multiple first crucial sections, needs the mounted angle sensor on each first crucial section, obtains
To the torsion angle in each first crucial section；The position in the second crucial section is the face PS girder 21, the face SS girder 22, the face PS rear
23, the face SS rear 24, blade inlet edge 25.
Dangerouse cross-section of the blade when structure designs include static strength and the minimum region of fatigue strength safety coefficient or
Stability coefficient lower region.These positions are easy to generate torsion under external force, can be used as the first crucial section, use
In the torsion angle of pilot blade.
In the present embodiment, it if only selecting one or seldom several first crucial sections, is obtained by obliquity sensor
After related torsion angle, then unit torque corresponding to the torsion angle in the other first crucial sections is calculated by formula, then
Finite element model analysis in step S3 is carried out to blade again, obtains the relationship of unit torque and stress value；
Wherein, formula are as follows:
In formula:
α1For the torsion angle of blade root, initial value 0；
αi, the torsion angle in previous section；
αi+1, the torsion angle in latter section；
I, i=1,2 ..., n are corresponding section serial number, and n is the last one section；
T, torque；
Δ l, cross-sectional length；
GIpi, corresponding torsional rigidity of section；
The torsion stiffness GI in the crucial section of blade each firstpiIt is special by structure of the blade in design with cross-sectional length Δ l
Property obtains.
In the present embodiment, the vibration frequency of excitational equipment is 0.3~0.8Hz, according to the size of wanted pilot blade, choosing
Select the excitational equipment of proper vibration frequency.When institute's blade to be tested is larger or smaller, other vibration frequencies can also be used
Excitational equipment.
In the present embodiment, the parameter request of obliquity sensor is as follows: angle measurement range is -60 °~60 °, resolution ratio
It is 0.01 °, sample frequency is 20~40Hz.The obliquity sensor of other parameters can also be used
In the present embodiment, the multi-functional acceleration transducer of the multiaxis of obliquity sensor preferred high accuracy, can also be used it
It can measure the sensor of torsion angle.
Although specific embodiments of the present invention have been described above, it will be appreciated by those of skill in the art that this is only
For example, protection scope of the present invention is to be defined by the appended claims.Those skilled in the art without departing substantially from
Under the premise of the principle and substance of the present invention, many changes and modifications may be made, but these change and
Modification each falls within protection scope of the present invention.
Claims (8)
1. a kind of method for testing fatigue for blade of wind-driven generator, which comprises the following steps:
S1, mounted angle sensor and foil gauge are distinguished in the first crucial section of the blade and the second crucial section, it is described
The x-axis of obliquity sensor is the axial direction of the blade, and the y-axis of the obliquity sensor is the front and rear edge direction of the blade；
S2, apply different size of static load respectively in the blade tip of the blade blade is made to twist, by described
Obliquity sensor and the foil gauge acquire the described first crucial section and the second crucial section in static demarcating respectively
The torsion angle and strain value of the blade；
S3, finite element model analysis is carried out by torsion angle to the blade and strain value, calculates described first and crucial cuts
The unit torque in the face strain value relationship with the described second crucial section respectively, obtains one with reference to coefficient；
S4, exciting force is issued by excitational equipment to blade application dynamic load, when the vibration amplitude of the blade is stablized
And when reaching target call, the described first crucial section and described is acquired by the obliquity sensor and the foil gauge respectively
The torsion angle and strain value of second crucial section blade in dynamic calibration；
S5, coefficient is referred to by described obtained in step S3, calculates the blade corresponding torsion angle in dynamic calibration
Strain value caused by unit torque；
S6, the strain value of acquisition subtracts obtained in step S5 by torque when the blade to be carried out to dynamic calibration in step s 4
Caused strain value obtains the strain value that the blade is generated in dynamic calibration by moment of flexure；
S7, in conjunction with finite element model analysis, decouple the influence of moment of flexure and torque couple to strain, obtain when dynamic calibration moment of flexure with
The relation function of strain then obtains result of the blade in testing fatigue；
Wherein: the described first crucial section is the maximum chord length section of the blade, blade root section from rounded transitional to wing area
Dangerouse cross-section when domain, the overlap joint transitional region of structural material not of the same race or structure design, the position in the described second crucial section
For the face PS girder, the face SS girder, the face PS rear, the face SS rear, blade inlet edge.
2. being used for the method for testing fatigue of blade of wind-driven generator as described in claim 1, which is characterized in that the structure is set
The dangerouse cross-section of timing includes static strength and the minimum region or stability coefficient lower region of fatigue strength safety coefficient.
3. being used for the method for testing fatigue of blade of wind-driven generator as described in claim 1, which is characterized in that the inclination angle passes
Sensor is equipped with multiple, corresponds be mounted on multiple first crucial sections respectively.
4. being used for the method for testing fatigue of blade of wind-driven generator as described in claim 1, which is characterized in that first pass through step
After S2 obtains torsion angle, then unit corresponding to the torsion angle in the other described first crucial sections is calculated by formula and is turned round
Then square is carrying out the finite element model analysis in step S3, is obtaining the relationship of unit torque and stress value；
Wherein, the formula are as follows:
In formula:
α1For the torsion angle of blade root, initial value 0；
αi, the torsion angle in previous section；
αi+1, the torsion angle in latter section；
I, i=1,2 ..., n are corresponding section serial number, and n is the last one section；
T, torque；
Δ l, cross-sectional length；
GIpi, corresponding torsional rigidity of section；
The torsion stiffness GI in each described first crucial section of the bladepiIt is being designed with cross-sectional length Δ l by the blade
When architectural characteristic obtain.
5. being used for the method for testing fatigue of blade of wind-driven generator as described in claim 1, which is characterized in that described first closes
Key section is the maximum chord length section of the blade.
6. being used for the method for testing fatigue of blade of wind-driven generator as described in claim 1, which is characterized in that the exciting is set
Standby vibration frequency is 0.3~0.8Hz.
7. being used for the method for testing fatigue of blade of wind-driven generator as described in claim 1, which is characterized in that the inclination angle passes
The parameter request of sensor is as follows: angle measurement range is -60 °~60 °, and resolution ratio is 0.01 °, and sample frequency is 20~40Hz.
8. the method for testing fatigue for blade of wind-driven generator as described in claim 1-7 any one, which is characterized in that
The obliquity sensor is acceleration transducer.
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Cited By (2)
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| CN111795899A (en) * | 2020-07-30 | 2020-10-20 | 上海电气风电集团股份有限公司 | Torsion loading equipment and blade torsion testing method |
| CN114323602A (en) * | 2021-11-30 | 2022-04-12 | 明阳智慧能源集团股份公司 | Fan blade static force testing method and system |
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