CN105508147B - Wind electricity blade single-point fatigue loading tests moment of flexure matching process - Google Patents
Wind electricity blade single-point fatigue loading tests moment of flexure matching process Download PDFInfo
- Publication number
- CN105508147B CN105508147B CN201511004114.4A CN201511004114A CN105508147B CN 105508147 B CN105508147 B CN 105508147B CN 201511004114 A CN201511004114 A CN 201511004114A CN 105508147 B CN105508147 B CN 105508147B
- Authority
- CN
- China
- Prior art keywords
- mrow
- msub
- blade
- moment
- balancing weight
- 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.)
- Expired - Fee Related
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/83—Testing, e.g. methods, components or tools therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/84—Modelling or simulation
-
- 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
-
- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P80/00—Climate change mitigation technologies for sector-wide applications
- Y02P80/20—Climate change mitigation technologies for sector-wide applications using renewable energy
Landscapes
- Wind Motors (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention belongs to the single-point fatigue loading pilot system of fan blade, moment of flexure matching process is tested more particularly to a kind of wind electricity blade single-point fatigue loading, blade is separated into by n discrete portions along flapwise according to equivalent substitution principle, establish actual total moment model, finally combine dichotomy principle, since blade tip, for a certain section, using the minimum value of theoretical moment and the difference of actual total moment as object function, the error in other sections is as inequality constraints condition, devise the Optimization Solution algorithm based on object function and constraints, and the number of balancing weight is added by founding mathematical models optimization, quality and position and ensure that added balancing weight number is minimum.On the premise of balancing weight number is added at least the actual tests moment of flexure of blade can be made to match as far as possible with theoretical moment of flexure by the present invention, the fatigue loading test accuracy of blade is improved, its precision can strictly reach the δ (being usually 7% at present) of industrial requirements error requirements.
Description
Technical field
The present invention relates to a kind of wind electricity blade single-point fatigue loading to test moment of flexure matching process, the MW class that is particularly suitable for use in wind
The fatigue loading experiment of electric blade, belong to the single-point fatigue loading pilot system of fan blade.
Background technology
Single-point fatigue loading test method is one of main stream approach of wind electricity blade testing fatigue in the world at present.Single-point is tired
Labor load test method applies single-point-excitation generally at blade flapwise about 70% makes it with blade resonance to complete testing fatigue.
According to IEC 61400-23Full-Scale Structural Testing of Wind Turbine Blade standards, by this
The theoretical moment of flexure phase that the actual moment of flexure of each end section of blade caused by single-point-excitation should provide with blade design side as far as possible
Matching.Blade surface is typically employed in both at home and abroad adds multiple balancing weights to ensure that the moment of flexure matching error δ in each section controls exist
In certain error range (the usual value of the error is 7% at present).But due to lacking effective moment of flexure matching process, it is most
Blade testing producer only by experience or simple computation, only adds a balancing weight to realize reality in the correct position of blade flapwise
The matching of border moment of flexure and theoretical moment of flexure, matching error is larger, and the relative error in some sections is considerably beyond 7%, it follows that
Fatigue test data precision is not high, single-point fatigue loading experimental test result distortion is caused to a certain extent, it is difficult to meet
High-precision blade fatigue test request.Or the paper such as Zhang Lei's peace《MW level wind electricity blade loading system key technologies are ground
Study carefully》In, though giving calculation of Bending Moment model, model is excessively simple and follow-up Optimization Steps are ambiguous, does not provide specific reality
Existing method, it follows that Bending moment distribution data descendant can not verify that reliability is not high.There is provided according to certain blade production firm
Data：Design service phase and be 20 years certain model blade, although having passed through the experiment of single-point fatigue loading, actual life is not far up to
To projected life.As wind energy conversion system gradually develops to megawatt-grade high-power direction, blade dimensions increase therewith, to the intensity of blade
It is harsher with the requirement of rigidity, high-precision blade fatigue load test will be crop leaf measuring field research emphasis it
One.It is therefore proposed that a kind of effective actual-theoretical moment of flexure matching process, the distribution precision of actual moment of flexure in experiment can be improved,
So as to improve the fatigue loading test accuracy of blade.
The content of the invention
Deficiency of the prior art, the technical problem to be solved in the present invention are more than：Theory can be made by providing one kind
The control errors of moment of flexure and actual moment of flexure between the two within δ, effectively improve the wind of the reality of blade-theoretical moment of flexure matching
Electric blade single-point fatigue loading tests moment of flexure matching process.
Wind electricity blade single-point fatigue loading of the present invention tests moment of flexure matching process, comprises the following steps：
(1) blade is divided into along flapwise by n discrete portions according to equivalent substitution principle, obtains (n+1) individual section, tested
In blade vibration driven by fatigue loading drive device, while produce exciting force；
(2) model is established：
The actual moment of flexure model for only considering blade deadweight is established, the model is expressed as
T1kFor the actual moment at a certain section k of blade in the model (k=1,2 ..., n+1) place；
After establishing addition balancing weight, consider the actual moment of flexure model of drive device weight and balancing weight weight, the model table
It is shown as
T2kFor the actual moment at a certain section k of blade in the model (k=1,2 ..., n+1) place；
Actual total moment of flexure model is obtained by above-mentioned, the model is expressed as
Tk=T1k+T2k；[3]
TkFor the total moment of reality at a certain section k of blade in the model (k=1,2 ..., n+1) place；
Wherein, i numbers for section, and (if without balancing weight on the right of the k of section, j is just for the counterweight block number on the right of the k of section by j
Without numbering, i.e., j is not present, then T2k=0), N is the balancing weight sum of all additions, and p is the balancing weight on the right of the k of section
Total (p≤N), ρiFor the line mass density of each discrete portions, biFor the length of each discrete portions, LkiFor end section k and i-th
Discrete portions ρiThe distance of center of gravity, f are blade excited frequency, yiFor ρiThe amplitude of affiliated discrete portions center of gravity, g are gravity
Acceleration, tkFor end section k to blade root distance, ymjFor balancing weight mjThe amplitude of center of gravity, rkFor fatigue loading drive device
To end section k distance, M is the equivalent mass of fatigue loading drive device, yMFor the amplitude at fatigue loading drive device,
Each parameter is the given value that can be measured above；mjFor the balancing weight quality of addition, xjFor addition balancing weight away from root of blade
Distance, mjWith xjFor unknown-value；
(3) T is calculatedk, the quality m of each balancing weight addedjAnd each balancing weight is to the distance x of blade rootj(i.e.
The point of addition of balancing weight) it is unknown-value, and known conditions is：Required according to testing fatigue, for any section k of blade
(1≤k≤n+1), actual total moment T thereonkWith theoretical moment Tk' error need control within the specific limits, i.e.,：
|T′k-Tk|/Tk≤ δ (k=1,2 ..., n+1)；[4]
Wherein, δ is original set value；
Solution is optimized according to formula [4], finally draws number and quality and position and the institute of added balancing weight
The balancing weight number of addition is minimum.In Optimization Solution, conventional mathematical software can be used, such as Matlab, Lindo, Lingo
Deng.
The method of Optimization Solution is preferably as follows in the present invention, specific method is：
1) actual total moment section maximum with theoretical moment relative error before being not added with balancing weight is calculated, if
The distance of the cross-sectional distance root of blade isAdded since blade tip, first add a balancing weight (even N=1), institute
The balancing weight of addition is more remote apart from the section, and the quality of required balancing weight is smaller, but maximum distance no more than meets to miss
The section that difference requires；Actual total moment section minimum with theoretical moment relative error is found out, if the cross-sectional distance blade
The distance of root is
1. the initial position of balancing weight is determined using dichotomy：
According to dichotomy principle, orderTake x1 1For x1Initial value, optional a section a, a=
1,2 ..., n+1, by theoretical moment T thereona' and actual total moment TaDifference minimum value as object function, by it
Inequality constraints condition of the difference of his cross-section error as the object function, it is as follows to establish objective optimization mathematical modeling：
MinG=T 'a-Ta；[5]
Wherein, the j=1 in formula [5] and formula [6]；
Solve m1Value, if m1There is solution, then make x1 1=x1, x when obtaining adding a balancing weight1、m1Optimal value, complete
Optimization；
If 2. without solution, according to dichotomy principle, make againTake x1 2For x1Initial value, optionally
One section c, section c with 1. in section a can be same section or different cross section, by theoretical moment of flexure thereon
Value Tc' and actual total moment TcDifference minimum value as object function, using the error in other sections as the object function
Inequality constraints condition, such as 1. establish objective optimization mathematical modeling and (the subscript a in respective formula is changed to c, p is on the right side of the c of section
The number of balancing weight), solve m1Value, if m1There is solution, then make x1 2=x1, x when obtaining adding a balancing weight1、m1It is optimal
Value, complete optimization；
If 3. without solution, further according to dichotomy principle, orderSo circulation, until obtaining
X when adding a balancing weight1、m1Optimal value；
If 4. x1 nLevel off to(i.e.ε gives according to error size) when still without solution, i.e., still not
Meet error requirements, then need to add second balancing weight, and calculate its point of addition, now take x1 1、x1 2……x1 nMiddle reality
Position initial value of total moment location point minimum with theoretical moment relative error as first balancing weight of addition, and take
The m that the location point solves in above-mentioned objective optimization mathematical modeling1As the quality of first balancing weight, second is added afterwards
Balancing weight；
2) calculate and added first balancing weight total moment actual afterwards and theoretical moment relative error maximum
Section, if the distance of the cross-sectional distance root of blade isActual total moment and theoretical moment relative error are found out simultaneously
Minimum section, if the distance of the cross-sectional distance root of blade isAccording to dichotomy principle, order
Then x is taken2 1For x2Initial value, 1. 2. 3. use such as the step in 1) --- because the balancing weight number used is 2, therefore
N=2 in formula [5] and formula [6] --- obtain adding the x after two balancing weights1、m1、x2And m2Optimal value；If x2 nBecome
It is bordering on(i.e.And ε gives according to error size) when still without solution, i.e., be still unsatisfactory for error requirements, then
Need to add the 3rd balancing weight and calculate its point of addition, now, take x2 1、x2 2……x2 nThe middle total moment of reality and theory
Point of addition of the minimum location point of moment relative error as second balancing weight, by the point of addition of the two balancing weights
Substitute into the objective optimization mathematical modeling of above-mentioned foundation (now N=2), the m of solution1Quality, m as first balancing weight2Make
For the quality of second balancing weight, the 3rd balancing weight is added afterwards；
3) the Optimization Solution step of the 3rd balancing weight is added as 2), if adding three balancing weights still without solution, needed
Add the 4th ... ..., until the addition individual balancing weights of N ' have solution, then take the point of addition of the N number of balancing weight solved
Point x1、x2……xN’, now (make N=N ') in the objective optimization mathematical modeling of above-mentioned foundation and solve each point of addition point institute
The quality of corresponding balancing weight；
According to the method for above-mentioned Optimization Solution, you can be met number, the quality of the balancing weight added of formula [4]
And position, and the balancing weight number added is minimum.
The possessed compared with prior art beneficial effect of the present invention is：
1st, for the present invention to any end section of blade, the model accuracy for calculating its actual Bending moment distribution is higher；
2nd, the present invention is directed to quantity, position and the quality for adding balancing weight, gives specific calculating and optimization method,
And meet the minimum number of added balancing weight；
3rd, the precision of moment of flexure matching of the present invention is high, and the theoretical moment of flexure of any end section of blade and actual moment of flexure error can be strict
Control is within δ (being usually 7% at present).
Brief description of the drawings
Fig. 1 is the Bending moment distribution analysis chart for only considering blade deadweight；
Fig. 2 is after adding balancing weight, considered the Bending moment distribution analysis chart of drive device weight and balancing weight weight；
Fig. 3 is the theoretical moment curve map of certain type blade in the present embodiment；
Fig. 4 is the curve map of the equivalent line mass density of certain type blade in the present embodiment；
Fig. 5 is the curve map of the amplitude in each section of certain type blade in the present embodiment；
Fig. 6 is certain type blade moment curve at exciting force with each section under deadweight collective effect in the present embodiment
Figure；
Fig. 7 is the comparison figure of actual total moment and theoretical moment in each section of certain type blade in the present embodiment；
Fig. 8 is the error effect after actual total moment in certain each section of type blade in the present embodiment matches with theoretical moment
Fruit is schemed.
Embodiment
The present invention is described further with reference to specific embodiment：
Certain blade testing center provides certain type blade that length is 40.3m, and according to equivalent substitution principle by the blade
22 discrete portions are separated into along flapwise, obtain 23 sections, i numbers for section, the length bi=1.5m of each discrete portions,
Table 1 gives the theoretical moment T ' in each section in the blade fatigue load testk, each discrete portions line mass density pi
And the amplitude y for each discrete portions center of gravity measured by laser testing instrumenti；And driven by fatigue loading drive device each
Discrete portions rotation produces exciting force, mass M=700Kg of the fatigue loading drive device, the amplitude y of its center of gravityM=
0.4, it drives the vibration frequency f=0.78Hz of the blade vibration.Optimized in the present embodiment using mathematical software MatLab
Solve.
Table 1
The single-point fatigue loading experiment moment of flexure matching process of certain type blade in the present embodiment is as follows：
(1) under exciting force caused by fatigue loading drive device, only consider blade deadweight, bring the data of table 1 into formula
[1]：
23 sections formed to discrete, actual moment thereon can be calculated respectively, the following institute of calculating process
Show：
(2) after adding balancing weight, the weight of fatigue loading drive device and the weight of balancing weight are considered, then all sections
Actual moment is calculated as follows：
The balancing weight quality m of additionjWith position xjFor known variables, it is expressed in matrix as：
In formula：N is the quantity of addition balancing weight.
Bring the data in table 1 into formula [2]：
Wherein：P be section k on the right of balancing weight sum, p≤N；J is the counterweight block number on the right of the k of section；If section k
The right does not have balancing weight, i.e. j is not present, then j is without numbering, T2k=0；
Actual moment thereon can be calculated respectively, and result of calculation is as follows：
Now, [T21,T22,…,T223] in m containing unknown quantityj、xj。
(3) the total moment of reality in all sections is calculated, according to formula [3]：
Tk=T1k+T2k
It can obtain:
Now, [T1,T2,…,T23] in m containing unknown quantityj、xj。
(4) required according to testing fatigue, for any section k (1≤k≤23) of the blade, the total moment of flexure of reality thereon
Value TkWith theoretical moment Tk' relative error δ need control 7% in the range of, that is, need to meet formula [4]：
|T′k-Tk|/Tk≤δ
It should meet：
According to formula [4] unknown quantity m is carried by above-mentionedj、xjObject function optimize in Matlab, wherein Optimization Steps
It is as follows：
1) calculate first and be not added with balancing weight total moment actual before section maximum with theoretical moment relative error
Face position isAll sections are all unsatisfactory for error requirements, wherein actual total moment and theoretical moment relative error
Minimum sectional position isOrderIs determined according to dichotomy principle
Initial value (the setting of one balancing weightWhen, ε=10-2, x1 nLevel off to)：
1. x is taken first1 1For x1Initial value, for convenience of calculating, select section k=1 actual total moment and theoretical moment of flexure
The minimum value of the difference of value is as object function, the inequality constraints bar of the difference of the error in other sections as the object function
Part, it is as follows that objective optimization mathematical modeling is established in Matlab：
MinG=T '1-T1 [5]
Note：N=1 in formula [5], formula [6], p are the number (p≤N) of balancing weight on the right of the k of section；
Result of calculation shows no solution, then continues step 2..
2. according to the initial position of dichotomy principle again balancing weight, then x1 2=30.23m, if step is 1. in Matlab
Establish objective optimization mathematical modeling and solve m1Value, as a result still show no solution, then continue step 3..
3. the initial position that balancing weight is 2. redefined such as step optimizes down successively, as a result show no solution, then after
Continuous step is 4..
4. when(i.e. x1 nLevel off to) when be still unsatisfactory for error requirements, then need addition second
Individual balancing weight simultaneously calculates its point of addition, now, takes x1 1、x1 2……x1 14The middle total moment of reality is relative with theoretical moment by mistake
Poor minimum location point (x1 5=38.59m) as the position initial value for adding first balancing weight, m1=417kg is as first
The quality of individual balancing weight, continue step 2), add second balancing weight.
2) calculate and added first balancing weight total moment actual afterwards and theoretical moment relative error maximum
Section, its distance apart from root of bladeFind out simultaneously add after first balancing weight actual total moment and
The minimum section of theoretical moment relative error, its distance apart from root of bladeThen According to dichotomy principle, x is taken2 1For x2Initial value, using such as the 1. 2. 3. (note of the step in 1)：Formula [5], public affairs
N=2 in formula [6]), as a result show no solution.WhenWhen be still unsatisfactory for error requirements, then need to add
Add the 3rd balancing weight and calculate its point of addition.Now, x is taken2 1、x2 2……x2 10The middle total moment of reality and theoretical moment
The minimum location point x of relative error2 6Point of additions of=the 32.48m as second balancing weight, and take above-mentioned two balancing weight
Location point x1=38.59m, x2The m that=32.48m is solved in Matlab1Quality of=the 349.4kg as first balancing weight,
m2Quality of=the 377kg as second balancing weight, continue 3), to add the 3rd balancing weight.
3) point of addition point of the Optimization Solution step of the 3rd balancing weight as 2), solved the 3rd balancing weight is added
x3=21.5m, but still be unsatisfactory for error requirements, then need to add the 4th balancing weight, 2) step is same to solve the 4th counterweight
The point of addition point x of block4=10.5m, the quality that can now solve balancing weight corresponding to four point of addition points are as follows：
x1=38.59m, m1=330kg
x2=32.48m, m2=336kg
x3=21.5m, m3=170kg
x4=10.5m, m4=90kg
I.e. balancing weight number at least can meet actual total moment with the relative error of theoretical moment 7% for four
Within.
Bring data above into formula [3], calculate the total moment of reality in each section after addition balancing weight, and by the reality
The total moment in border draws the percentage error of the two compared with theoretical moment, specific as shown in table 2：
Table 2
As table 2 it can also be seen that according to obtained by blade single-point fatigue loading of the present invention experiment moment of flexure matching process
The precision of moment of flexure matching is high, and the error of the theoretical moment in any section of blade and actual total moment, which can be strict controlled in, to be wanted
Within 7% asked.
Claims (1)
1. a kind of wind electricity blade single-point fatigue loading tests moment of flexure matching process, it is characterised in that：Comprise the following steps：
（1）Blade is divided into along flapwise by n discrete portions according to equivalent substitution principle, obtains n+1 section, in experiment passing through
Fatigue loading drive device drives blade vibration, while produces exciting force；
（2）Establish model：
The actual moment of flexure model for only considering blade deadweight is established, this only considers that the actual moment of flexure model of blade deadweight is expressed as<math display = 'block'>
<mrow>
<msub>
<mi>T1</mi>
<mi>k</mi>
</msub>
<mo>=</mo>
<mrow>
<msubsup>
<mo>&sum;</mo>
<mrow>
<mi>i</mi>
<mo>=</mo>
<mn>1</mn>
</mrow>
<mi>k</mi>
</msubsup>
<mrow>
<msub>
<mi>&rho;</mi>
<mi>i</mi>
</msub>
<msub>
<mi>b</mi>
<mi>i</mi>
</msub>
<msub>
<mi>L</mi>
<mi>ki</mi>
</msub>
</mrow>
</mrow>
<mfenced open = '[' close = ']'>
<mrow>
<msup>
<mfenced open = '(' close = ')'>
<mrow>
<mn>2</mn>
<mi>&pi;</mi>
<mi>f</mi>
</mrow>
</mfenced>
<mn>2</mn>
</msup>
<msub>
<mi>y</mi>
<mi>i</mi>
</msub>
<mo>&plus;</mo>
<mi>g</mi>
</mrow>
</mfenced>
</mrow>
</math>, T1k is the actual moment of flexure model middle period that this only considers blade deadweight
Actual moment at a certain section k of piece, wherein k=1,2 ..., n+1；
After establishing addition balancing weight, consider the actual moment of flexure model of drive device weight and balancing weight weight, the addition balancing weight
Afterwards, consider that the actual moment of flexure model of drive device weight and balancing weight weight is expressed as
<math display = 'block'>
<mrow>
<msub>
<mi>T2</mi>
<mi>k</mi>
</msub>
<mo>=</mo>
<mrow>
<msubsup>
<mo>&sum;</mo>
<mrow>
<mi>j</mi>
<mo>=</mo>
<mn>1</mn>
</mrow>
<mi>k</mi>
</msubsup>
<mrow>
<msub>
<mi>m</mi>
<mi>j</mi>
</msub>
<mfenced open = '(' close = ')'>
<mrow>
<msub>
<mi>x</mi>
<mi>j</mi>
</msub>
<mo>&minus;</mo>
<msub>
<mi>t</mi>
<mi>k</mi>
</msub>
</mrow>
</mfenced>
</mrow>
</mrow>
<mfenced open = '[' close = ']'>
<mrow>
<msup>
<mfenced open = '(' close = ')'>
<mrow>
<mn>2</mn>
<mi>&pi;</mi>
<mi>f</mi>
</mrow>
</mfenced>
<mn>2</mn>
</msup>
<msub>
<mi>y</mi>
<mi>mj</mi>
</msub>
<mo>&plus;</mo>
<mi>g</mi>
</mrow>
</mfenced>
<mo>+</mo>
<mi>M</mi>
<msub>
<mi>r</mi>
<mi>k</mi>
</msub>
<mfenced open = '[' close = ']'>
<mrow>
<msup>
<mfenced open = '(' close = ')'>
<mrow>
<mn>2</mn>
<mi>&pi;</mi>
<mi>f</mi>
</mrow>
</mfenced>
<mn>2</mn>
</msup>
<msub>
<mi>y</mi>
<mi>M</mi>
</msub>
<mo>&plus;</mo>
<mi>g</mi>
</mrow>
</mfenced>
</mrow>
</math>,
T2kFor after the addition balancing weight, consider a certain section of blade in the actual moment of flexure model of drive device weight and balancing weight weight
Actual moment at the k of face, wherein, k=1,2 ..., n+1；
Actual total moment of flexure model is expressed as Tk=T1k+T2k, TkFor the reality at a certain section k of blade in actual total moment of flexure model
Total moment, wherein k=1,2 ..., n+1；
Wherein, i numbers for section, and j is the counterweight block number on the right of the k of section, and N is the balancing weight sum of all additions, and p is section
The sum of balancing weight on the right of k, wherein p≤N, ρiFor the line mass density of each discrete portions, biFor the length of each discrete portions,
LkiFor end section k and i-th of discrete portions ρiThe distance of center of gravity, f are blade excited frequency, yiFor ρiAffiliated discrete portions weight
Amplitude at the heart, g are acceleration of gravity, tkFor end section k to blade root distance, ymjFor balancing weight mjThe amplitude of center of gravity, rk
Distance for fatigue loading drive device to end section k, M be fatigue loading drive device equivalent mass, yMFor fatigue loading
Amplitude at drive device, above ρi、bi、Lki、f、yi、tk、ymj、rk、M、yMIt is the given value that can be measured； mjFor addition
Balancing weight quality, xjFor distance of the balancing weight away from root of blade of addition, mjWith xjFor unknown-value；
（3）According to<math display = 'block'>
<mrow>
<mrow>
<apply>
<csymbol>
<msup>
<msub>
<mi>T</mi>
<mi>k</mi>
</msub>
<mo>&#8242;</mo>
</msup>
<mo>&minus;</mo>
<msub>
<mi>T</mi>
<mi>k</mi>
</msub>
</csymbol>
</apply>
<mo>/</mo>
<msub>
<mi>T</mi>
<mi>k</mi>
</msub>
</mrow>
<mi>&delta;</mi>
</mrow>
</math>Solution is optimized, wherein,<math display = 'block'>
<mrow>
<msup>
<msub>
<mi>T</mi>
<mi>k</mi>
</msub>
<mo>&#8242;</mo>
</msup>
</mrow>
</math>Representation theory moment, k=1,2 ..., n
+ 1, δ are original set value, finally draw the number and quality and position and the balancing weight number added of added balancing weight
At least. 1
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511004114.4A CN105508147B (en) | 2015-12-28 | 2015-12-28 | Wind electricity blade single-point fatigue loading tests moment of flexure matching process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511004114.4A CN105508147B (en) | 2015-12-28 | 2015-12-28 | Wind electricity blade single-point fatigue loading tests moment of flexure matching process |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105508147A CN105508147A (en) | 2016-04-20 |
| CN105508147B true CN105508147B (en) | 2017-12-08 |
Family
ID=55716377
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201511004114.4A Expired - Fee Related CN105508147B (en) | 2015-12-28 | 2015-12-28 | Wind electricity blade single-point fatigue loading tests moment of flexure matching process |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105508147B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102016117191A1 (en) * | 2016-09-13 | 2018-03-15 | fos4X GmbH | Method and device for determining loads on a tower of a wind energy plant |
| CN110296053B (en) * | 2018-03-23 | 2020-06-05 | 北京金风慧能技术有限公司 | Fatigue damage monitoring method and device for wind driven generator blade |
| CN110232238B (en) * | 2019-06-11 | 2023-02-07 | 南昌工程学院 | Loader layout method and device, computer equipment and storage medium |
| CN113447376B (en) * | 2021-07-05 | 2023-03-28 | 山东理工大学 | Bending moment matching optimization method for wind power blade double-shaft fatigue test |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102004838A (en) * | 2010-12-17 | 2011-04-06 | 中国航天空气动力技术研究院 | Method for determining wind turbine blade structure based on finite difference method |
| CN202768249U (en) * | 2012-08-03 | 2013-03-06 | 国电联合动力技术有限公司 | Wind generation set control system based on pneumatic torque calculation model |
| CN104732060A (en) * | 2015-01-19 | 2015-06-24 | 湖南科技大学 | Online identification method for multiple loads on blades of large wind power generation set |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10302067B2 (en) * | 2013-02-08 | 2019-05-28 | Vestas Wind Systems A/S | Model based controller for a wind turbine generator |
-
2015
- 2015-12-28 CN CN201511004114.4A patent/CN105508147B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102004838A (en) * | 2010-12-17 | 2011-04-06 | 中国航天空气动力技术研究院 | Method for determining wind turbine blade structure based on finite difference method |
| CN202768249U (en) * | 2012-08-03 | 2013-03-06 | 国电联合动力技术有限公司 | Wind generation set control system based on pneumatic torque calculation model |
| CN104732060A (en) * | 2015-01-19 | 2015-06-24 | 湖南科技大学 | Online identification method for multiple loads on blades of large wind power generation set |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105508147A (en) | 2016-04-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105508147B (en) | Wind electricity blade single-point fatigue loading tests moment of flexure matching process | |
| EP3791060B1 (en) | Wind turbine control method | |
| CN102880764B (en) | Method for calculating front frame strength of wind generating set | |
| CN103541862B (en) | Reduce pitch control method and the system of wind turbine extreme load | |
| CN103970965A (en) | Test run method for accelerated life test of gas turbine engine | |
| CN102866637B (en) | Quadratic order-reduction based method for simulating unsteady aerodynamic force of aerofoil with operation surface | |
| CN103678762A (en) | Optimal scaling modeling method of aeroelasticity wind-tunnel model of composite material wing | |
| CN106777549B (en) | Bridge multi-scale finite element simulation method for load test | |
| CN107633105A (en) | A kind of four rotor wing unmanned aerial vehicle parameter identification methods based on improvement shuffled frog leaping algorithm | |
| CN105117539B (en) | Pneumatic equipment bladess modal frequency and its bimodal Gauss Distribution Fitting method | |
| Draper et al. | A large eddy simulation-actuator line model framework to simulate a scaled wind energy facility and its application | |
| Campagnolo et al. | Design, manufacturing and characterization of aero-elastically scaled wind turbine blades for testing active and passive load alleviation techniques within a ABL wind tunnel | |
| CN106286151B (en) | A kind of Wind turbines slow-speed shaft torsional load monitoring method and loading analysis method | |
| Bottasso et al. | Wind tunnel testing of wind turbines and farms | |
| CN106097157A (en) | A kind of synchronous generator excited system identification of Model Parameters optimization method | |
| CN107704679A (en) | Correction equipment and method for direct-drive generator model | |
| CN107657073A (en) | A kind of parameter identification method of sandwich composite structure | |
| CN105956318A (en) | Improved splitting H-K clustering method-based wind power plant fleet division method | |
| JP2021049841A (en) | Control device, learning device, control method, learning method, and program | |
| CN106786675A (en) | A kind of power system stabilizer, PSS and its implementation | |
| CN101794338A (en) | Correction method of matrix dynamics model based on structure modal test | |
| CN104318005A (en) | Virtools based multivariate data fusion virtual test display system | |
| CN110018695B (en) | Active control method for flutter pneumatic wing plate of super-large-span suspension bridge | |
| CN111680823A (en) | Wind direction information prediction method and system | |
| CN108489696B (en) | A kind of method of spring additional stiffness in elimination frequency response function |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171208 Termination date: 20191228 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |