CN103321853A - Method for restraining wind turbine blade adopting compound damping structure from vibrating - Google Patents
Method for restraining wind turbine blade adopting compound damping structure from vibrating Download PDFInfo
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Abstract
The invention specifically discloses a method for restraining a wind turbine blade adopting a compound damping structure from vibrating, which solves the problem that vibration easily caused by a large-scale flexible blade cannot be effectively prevented and eliminated by using a method. The method for restraining the wind turbine blade adopting the compound damping structure from vibrating comprises the following specific steps: a co-cured constrained damping layer is arranged on the surface of the blade, and a free damping layer is arranged on the outer surface of a girder; the free damping layer is formed by a single layer of damping material, and damping viscoelastic material, damping alloy or damping compound material is selected; the co-cured formation of the co-cured constrained damping layer is achieved by arranging a compound material layer and a damping material layer in a staggered manner, the compound material layer is made of fibre glass compound material, carbon fibre compound material or glass and carbon fibre compound material, and the damping material layer is made of the damping viscoelastic material. Compared with the prior art, the method has universal applicability, effective vibration restraining performance, economical efficiency and designability.
Description
Technical field
The present invention relates to technical field of wind power generation, but be specially a kind of pneumatic equipment blades made that utilizes compound damping structure method of quivering.
Background technique
Along with environmental problem more and more is subject to people's attention, clean energy resource progressively becomes the main flow of world energy sources development.Wind energy obtains develop rapidly as a kind of renewable and clean energy resource in recent years, wherein MW level wind energy conversion system has become the mainstream model of wind energy conversion system.For satisfying the high-power output requirement of wind energy conversion system, pneumatic equipment blades made is towards maximization, thin-long development (for example single length of blade of external certain company's production has reached 55 meters).Flutter occurs in large-scale slender blade under the complex load effect of aerodynamic force, elastic force and inertial force, its main flutter form has span vibration (edgwise vibration) and pats vibration (flapwise vibration).The flutter of blade not only reduces the power stage of wind wheel, the more important thing is that the alternating stress of blade flutter can make blade produce fatigue crack even fracture; Flutter Blades and air effect produce aerodynamic noise in addition, and environment is caused noise pollution, have influence near the resident's of wind energy turbine set life and the normal activity of other animals.
For blade noise, existing solution mainly contains:
Patent (CN 101619705 B) discloses a kind of Blades For Horizontal Axis Wind with bionic-type blade top boss, this blade can improve the flow losses at blade tip place, thereby reduce the noise that interfere mutually in pneumatic equipment blades made and blade tip whirlpool, reach the purpose to whole wind wheel noise reduction.
Patent (CN 102003333 A) discloses a kind of pneumatic equipment blades made with decrease of noise functions, and the profile line undulate of this blade tip part, transition portion and trailing edge part also is provided with toothed segment.
Patent (CN 102562436 A) discloses a kind of Denoiser of wind mill rotor blade, and this Denoiser contains bristle, hair family and porous layer.This Denoiser can have good noise reduction to the blade in the distinguished and admirable situation of different direction.
Patent (EP 0652367) discloses a kind of pneumatic equipment blades made with dissimilar tooth form trailing edge; Patent (EP 1314885) discloses a kind of pneumatic equipment blades made with profile of tooth panel; Patent (EP 1338793) discloses a kind of pneumatic equipment blades made with variable profile of tooth trailing edge.
Such scheme has all changed the blade tip shape, improves the blade tip gas flow shape with different tooth profile, thereby reaches the noise reduction purpose.But the profile of tooth blade tip difficulty of processing in the such scheme is larger, has changed the aerodynamic configuration of former aerofoil profile, and its whole pneumatic ability is still to be tested.
For blade flutter, existing solution mainly contains:
Patent (CN 102322391A) discloses a kind of guard method of pneumatic equipment blades made vibration condition being carried out forecast analysis, predicts the hour of danger of blade according to calculating, and dangerous blade is shut down in advance, reaches the protection to blade.This method can effectively be protected blade, but but do not improve blade self ability of quivering, improve the stability of blade.
Patent (CN 2737980Y) and patent (CN 102348892A) disclose respectively a kind of structural damping device of wind wheel blade, this damper invests the blade inwall by the mode such as bonding, can in wider frequency of okperation, effectively control blade vibration, but exist damper to break away from, increase leaf quality with the defective of complex structure etc.
In sum, but the research of quivering for large-scale blade at present mainly concentrates on Pneumatic method and extra damper method.Pneumatic method mainly is to utilize the aerodynamic configuration that changes blade, make it to have good stall performance, thereby but reach the purpose of quivering in the high wind speed district, but the method can reduce the dynamics ability of blade, thereby reduce the output power of wind wheel, but and in the effect of quivering in low wind speed district relatively poor; Extra damper method is to utilize at the extra damper of blade layout to realize blade flutter is suppressed, but only works in certain frequency domain scope or a certain flutter direction, and can make blade increase extra mass, and damper easily comes off in addition, causes potential safety hazard.
Summary of the invention
The present invention is in order to solve wind energy conversion system large-scale flexible blade and easily flutter to occur and the problem that lacks the effectively preventing method, but a kind of pneumatic equipment blades made that utilizes compound damping structure method of quivering is provided.
The present invention adopts following technological scheme to realize: but utilize the pneumatic equipment blades made of the compound damping structure method of quivering, be specially at blade surface and establish the co-curing restriction damping layer, establish the free damping layer at the girder outer surface; The free damping layer is specially and is adhered to the girder outer surface by individual layer damping viscoelastic material or individual layer damping alloy or individual layer damp composite material, and wherein the thickness of free damping layer can be calculated by following formula:
Wherein
Be the main beam structure fissipation factor,
Be girder thickness,
Be damping layer thickness,
Be the girder Young's modulus,
Be the damping material Young's modulus,
Be the damping material fissipation factor;
The co-curing restriction damping layer is by composite layer and the wrong layout of damping material interlayer (being specially the staggered stack of one deck composite layer one deck damping material layer) co-curing moulding, and the superiors and orlop are composite layer, the damping material layer is established one deck at least, composite layer selects that glass fiber compound material or carbon fiber composite or glass and carbon fiber are mixed takes composite material, and the damping material layer is selected the damping viscoelastic material; The thickness of co-curing restriction damping layer can be calculated with method of iteration by following various simultaneous:
Wherein
Be the covering co-curing restriction damping layer structural loss factor,
lBe the thickness of composite layer,
LBe the total thickness of co-curing restriction damping layer,
NFor damping material is counted layer by layer,
H v Be the damping material layer thickness;
βBe damping material layer fissipation factor;
GShear modulus for damping material;
fExcited frequency for the suffered fluid-load of blade (wind carries);
WQuality for co-curing restriction damping layer unit length;
gBe gravity accleration;
A i Be
iThe area of layer composite layer;
E i Be
iThe Young's modulus of layer composite layer;
d i Be first layer composite layer to the
iThe distance of layer composite layer;
I i Be
iLayer composite layer is for the moment of inertia of its neutral surface, and neutral surface refers to that structure had not both had pulling force not have the face (neutral surface refers to both do not had pulling force also not have the face of pressure when structure bends vibration) of pressure yet when bending vibration;
K i Be
iThe tensible rigidity of the composite layer of layer,
(EI) ∞ Flexural rigidity for co-curing restriction damping layer neutral surface;
(EI) 0 Calculate the summation of flexural rigidity with self neutral surface for each composite layer;
(EI) r Flexural rigidity real part for the co-curing restriction damping layer.
ReFor getting real part,
ImFor getting imaginary part,
Be amount of transition,
I, j, eBe counting variable,
RIntermediate quantity for computational algorithm.
Of the present inventionly establish the co-curing restriction damping layer at blade surface, establish the processing technology that the free damping layer has specifically adopted the co-curing moulding at the girder outer surface, this is that the forming materials those skilled in the art know.The method of above-mentioned definite co-curing restriction damping layer and free damping layer thickness is to set up mathematical model on the basis of great many of experiments, adopt rational calculation process, utilize suitable numerical simulation to draw, this method can be described the relation between other parameters in the thickness of co-curing restriction damping layer and free damping layer and the vane design of wind turbines process more exactly.
For the main beam structure fissipation factor,
Be the covering co-curing restriction damping layer structural loss factor, this is that designing requirement determines; All the other each parameters are the known parameters in the vane design of wind turbines process in the above-mentioned design process, such as girder thickness, girder Young's modulus, damping material Young's modulus, damping material fissipation factor etc., be that those skilled in the art hold facile in different design processes.
Beneficial effect of the present invention is as follows: utilize detailed design and be calculated as pneumatic equipment blades made and added co-curing restriction damping layer and free damping layer, but realized quivering of wind energy conversion system.The present invention compared with prior art has:
1) general applicability.Since the present invention mainly to the blade interior structure damping of be correlated with process, the blade aerodynamic configuration is not made amendment, and blade root and wind wheel hub link the employing traditional approach.Therefore the present invention can be suitable for the apparatus for lower wind machine wind wheel of most situation.
2) but effective quivering property.The present invention adopts the co-curing restriction damping layer structure of composite material+damping material+composite material to the blade covering, girder adopts free damping layer structure, therefore the compound damping structure blade has the higher structural loss factor, can in wider frequency domain, carry out establishment to blade flutter, improve the aerodynamic stability of wind mill wind wheel.
3) Economy.Co-curing damping and free damping are processed can significantly not increase the blade cost of production, but so the present invention have simultaneously certain Economy in the performance that obtains better to quiver.
4) designability.Can according to actual needs damping parameter be designed and optimize, obtain required blade structure fissipation factor, satisfy the design needs.
Description of drawings
Fig. 1 is the blade section structural representation;
Fig. 2 is co-curing restriction damping layer structural representation.
Among the figure: 1-blade, 2-free damping layer, 3-co-curing restriction damping layer, 4 girders, 5-composite layer, 6-damping material layer.
Embodiment
The method but the pneumatic equipment blades made that utilizes compound damping structure quivers is specially on blade 1 surface and establishes co-curing restriction damping layer 3, establishes free damping layer 2 at girder 4 outer surfaces; Free damping layer 2 is specially and is adhered to the girder outer surface by individual layer damping viscoelastic material or individual layer damping alloy or individual layer damp composite material, and wherein the thickness of free damping layer can be calculated by following formula:
Wherein
Be main beam structure structure fissipation factor,
Be girder thickness,
Be damping layer thickness,
Be the girder Young's modulus,
Be the damping material Young's modulus,
Be the damping material fissipation factor;
Co-curing restriction damping layer 3 is by composite layer and the moulding of the wrong layout of damping material interlayer co-curing, and the superiors and orlop are composite layer, the damping material layer is established one deck at least, composite layer selects that glass fiber compound material or carbon fiber composite or glass and carbon fiber are mixed takes composite material, and the damping material layer is selected the damping viscoelastic material; The thickness of co-curing restriction damping layer 3 can be calculated with method of iteration by following various simultaneous:
Wherein
Be the covering co-curing restriction damping layer structural loss factor,
lBe the composite material layer thickness,
LBe co-curing structure total thickness,
NFor damping material is counted layer by layer,
H v Be the damping material layer thickness;
βBe damping material layer fissipation factor;
GShear modulus for damping material;
f Excited frequency for the suffered fluid-load of blade (wind carries);
WQuality for co-curing restriction damping layer unit length;
gBe gravity accleration;
A i Be
iThe area of layer composite layer;
E i Be
iThe Young's modulus of layer composite layer;
d i Be first layer composite layer to the
iThe distance of layer composite layer;
I i Be
iLayer composite layer is for the moment of inertia of its neutral surface, and neutral surface refers to both do not had pulling force also not have the face of pressure when structure bends vibration;
K i Be
iThe tensible rigidity of the composite layer of layer,
(EI) ∞ Flexural rigidity for co-curing restriction damping layer neutral surface;
(EI) 0 Calculate the summation of flexural rigidity with self neutral surface for each composite layer;
(EI) r Flexural rigidity real part for the co-curing restriction damping layer.
In the specific implementation process, establish between girder 4 outer surfaces and free damping layer 2 and expand the change layer, it is the rigid foam of spherical cavity structure that expansion change layer is selected inside, perhaps selects the material of the inside cellular structure of being made by metal or macromolecular material.
Embodiment 1
Take certain 2 500 kW wind energy conversion system as embodiment.This wind energy conversion system is mainly used in marine wind electric field, and its design power is 2.5 MW, adopts three blade shapes, and leaf covering sheet material is GRP, I-steel girder, planetary pinion speedup, double loop asynchronous motor, air cooling; Its main design parameters such as table 1.
Table 1 main design parameters
| Sequence number | Design flow | Design load |
| 1 | The wind wheel blade number | 3 |
| 2 | Rotating speed/rpm | 10.5～19.0 |
| 3 | Root diameter/m | 80 |
| 4 | Wind-exposuring area/ | 5 026 |
| 5 | Power is adjusted mode | Feather |
| 6 | Start wind speed/m/s | 4 |
| 7 | Rated power wind speed/m/s | 15 |
| 8 | Shut down wind speed/m/s | 25 |
| 9 | Survival wind speed/m/s | 65 |
| 10 | Slurry is apart from adjusting | Single electricity drives |
| 11 | Wind wheel gross weight/kg | 50 000 |
| 12 | Length of blade/m | 38.8 |
| 13 | Leaf weight/kg | 8 700 |
| 14 | Blade material | GRP |
(1) aerofoil profile is selected
According to designing requirement, whole lamina is selected NACA 6413 aerofoil profiles, and this aerofoil profile has larger ratio of lift coefficient to drag coefficient and good stall performance.
(2) damping structure
Adopt the co-curing restriction damping layer structure of composite material, damping material, composite material; Girder is selected steel I-beam, and does the free damping layer and process, and is about to damping material and sticks on the girder web plate with epoxy resin.Damping material is all selected epoxy resin viscoelastic material (SMRD 100 F50), its fissipation factor
β=0.89, and can bear for a long time 120 ℃ temperature, satisfy the working condition requirement of large scale wind power machine blade.
(3) but quiver specificity analysis
At the Matlab/Simulink environment this pneumatic equipment blades made is carried out modeling.Co-curing restriction damping layer performance parameter is: E
11=42.6GPa, E
12=16.5 GPa, G
12=5.5 GPa,
ν 12=0.22,
ρ=1 950 kg/m
-3The damping property parameter is:
β=0.89, G=3.43 * 10
6N/m, E=1.14 * 10
6N/m, the temperature of ignoring damping material is effect frequently.Based on ONERA nonlinear aerodynamic model common blade and damping vane are being started wind speed
V 1 =4 m/s, rated wind speed
V 2 =15 m/s, shutdown wind speed
V 3 =25 m/s and survival wind speed
V 4 Carry out the numerical simulation contrast under four kinds of wind speed of=45 m/s.The structural damping of simulation process common blade is ignored.Table 2 is the performance comparison of common blade and damping vane under each operating mode.
Table 2 correlation data
The structural loss factor that is calculated damping vane under four kinds of wind speed by emulated data and formula (23) is respectively
η 1=0.617,
η 2=0.579,
η 3=0.523 He
η 4=0.439.By as seen from Table 2, under four kinds of wind speed, damping vane has reduced respectively 51.1%, 48.1%, 43.6%, 37.1% than the shimmy displacement standard deviation of common blade, and shimmy velocity standard difference has not reduced 51.1%, 47.9%, 43.7%, 37.1%; Wave the displacement standard deviation and reduced respectively 37.9%, 34.8%, 30.8%, 25.2%, wave the velocity standard difference and do not reduced 37.9%, 35.0%, 30.8%, 25.0%.
In sum, the interior friction of damping vane by damping material can be converted into thermal energy consumption with the part flutter and dissipate, to blade pat flutter, exhibition can be carried out establishment to flutter and torsional flutter, but significantly improve blade self ability of quivering, give full play to the advantage of flexible blade.
Claims (2)
1. but a pneumatic equipment blades made that utilizes compound damping structure method of quivering is characterized in that: be specially on blade (1) surface and establish co-curing restriction damping layer (3), establish free damping layer (2) at girder (4) outer surface; Free damping layer (2) is individual layer damping viscoelastic material or individual layer damping alloy or individual layer damp composite material, is specially to adhere to girder (4) outer surface, and wherein the thickness of free damping layer can be calculated by following formula:
Wherein
Be the main beam structure fissipation factor,
Be girder thickness,
Be damping layer thickness,
Be the girder Young's modulus,
Be the damping material Young's modulus,
Be the damping material fissipation factor;
Co-curing restriction damping layer (3) is by composite layer and the moulding of the wrong layout of damping material interlayer co-curing, and the superiors and orlop are composite layer, the damping material layer is established one deck at least, composite layer selects that glass fiber compound material or carbon fiber composite or glass and carbon fiber are mixed takes composite material, and the damping material layer is selected the damping viscoelastic material; The composite layer of co-curing restriction damping layer (3) and the thickness of damping material layer can be calculated with method of iteration by following various simultaneous:
Wherein
Be the structural loss factor of co-curing restriction damping layer,
lBe the thickness of composite layer,
LBe the total thickness of co-curing restriction damping layer,
NBe the composite layer number of plies,
H v Be the damping material layer thickness;
βBe damping material layer fissipation factor;
GShear modulus for damping material;
fExcited frequency for the suffered fluid-load of blade (wind carries);
WQuality for co-curing restriction damping layer unit length;
gBe gravity accleration;
A i Be
iThe area of layer composite layer;
E i Be
iThe Young's modulus of layer composite layer;
d i Be outermost surface composite layer to the
iThe distance of layer composite layer;
I i Be
iLayer composite layer be for the moment of inertia of its neutral surface,
K i Be
iThe tensible rigidity of the composite layer of layer;
(EI) ∞ Flexural rigidity for co-curing restriction damping layer neutral surface;
(EI) 0 Calculate the summation of flexural rigidity with self neutral surface for each composite layer;
(EI) r Flexural rigidity real part for the co-curing restriction damping layer.
2. but the pneumatic equipment blades made that the utilizes compound damping structure according to claim 1 method of quivering, it is characterized in that: between girder (4) outer surface and free damping layer (2), establish and expand the change layer, it is the rigid foam of spherical cavity structure that expansion change layer is selected inside, perhaps selects the material of the inside cellular structure of being made by metal or macromolecular material.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104948395A (en) * | 2015-07-15 | 2015-09-30 | 成都高斯电子技术有限公司 | Wind driven generator blade |
| CN105257485A (en) * | 2015-10-23 | 2016-01-20 | 西安交通大学 | Wind turbine blade with vibration reduced through particle damping |
| CN106739003A (en) * | 2016-12-20 | 2017-05-31 | 太原科技大学 | Co-curing damping perforation type presses down pneumatic equipment bladess for structure of quivering and preparation method thereof |
| CN107144478A (en) * | 2016-03-01 | 2017-09-08 | 上海艾郎风电科技发展（集团）有限公司 | The method of the fatigue strength of its pilot blade of blade fatigue test device and use |
| CN109533260A (en) * | 2018-11-19 | 2019-03-29 | 中国舰船研究设计中心 | Screw shaft of ship commitments beam isolation structure device |
| CN109766604A (en) * | 2018-12-27 | 2019-05-17 | 浙江大学 | A kind of blade high rigidity design method based on random equal geometrical analysis |
| US11536144B2 (en) | 2020-09-30 | 2022-12-27 | General Electric Company | Rotor blade damping structures |
| US11739645B2 (en) | 2020-09-30 | 2023-08-29 | General Electric Company | Vibrational dampening elements |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RO112433B1 (en) * | 1997-02-26 | 1997-09-30 | Nicolae Stoica | Resistance structures vibrations reducing process and device |
| WO1999032789A1 (en) * | 1997-12-09 | 1999-07-01 | Lm Glasfiber A/S | Windmill blade with vibration damper |
| EP1008747A2 (en) * | 1998-12-08 | 2000-06-14 | Franz Mitsch | Vibration absorber for wind turbines |
| CN1375040A (en) * | 1999-06-16 | 2002-10-16 | 尼格麦康有限公司 | Damping of oscillations in wind turbines |
-
2013
- 2013-04-12 CN CN201310126333.4A patent/CN103321853B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RO112433B1 (en) * | 1997-02-26 | 1997-09-30 | Nicolae Stoica | Resistance structures vibrations reducing process and device |
| WO1999032789A1 (en) * | 1997-12-09 | 1999-07-01 | Lm Glasfiber A/S | Windmill blade with vibration damper |
| EP1008747A2 (en) * | 1998-12-08 | 2000-06-14 | Franz Mitsch | Vibration absorber for wind turbines |
| CN1375040A (en) * | 1999-06-16 | 2002-10-16 | 尼格麦康有限公司 | Damping of oscillations in wind turbines |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104948395A (en) * | 2015-07-15 | 2015-09-30 | 成都高斯电子技术有限公司 | Wind driven generator blade |
| CN105257485A (en) * | 2015-10-23 | 2016-01-20 | 西安交通大学 | Wind turbine blade with vibration reduced through particle damping |
| CN107144478A (en) * | 2016-03-01 | 2017-09-08 | 上海艾郎风电科技发展（集团）有限公司 | The method of the fatigue strength of its pilot blade of blade fatigue test device and use |
| CN106739003A (en) * | 2016-12-20 | 2017-05-31 | 太原科技大学 | Co-curing damping perforation type presses down pneumatic equipment bladess for structure of quivering and preparation method thereof |
| CN106739003B (en) * | 2016-12-20 | 2019-03-15 | 太原科技大学 | Co-curing damping perforation type presses down the pneumatic equipment bladess and preparation method thereof for structure of quivering |
| CN109533260A (en) * | 2018-11-19 | 2019-03-29 | 中国舰船研究设计中心 | Screw shaft of ship commitments beam isolation structure device |
| CN109766604A (en) * | 2018-12-27 | 2019-05-17 | 浙江大学 | A kind of blade high rigidity design method based on random equal geometrical analysis |
| CN109766604B (en) * | 2018-12-27 | 2020-10-16 | 浙江大学 | Blade high-rigidity design method based on random isogeometric analysis |
| US11977823B2 (en) | 2018-12-27 | 2024-05-07 | Zhejiang University | Method for designing high-rigidity blade based on stochastic isogeometric analysis |
| US11536144B2 (en) | 2020-09-30 | 2022-12-27 | General Electric Company | Rotor blade damping structures |
| US11739645B2 (en) | 2020-09-30 | 2023-08-29 | General Electric Company | Vibrational dampening elements |
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