CN110220688B - Fatigue testing method for wind driven generator blade - Google Patents
Fatigue testing method for wind driven generator blade Download PDFInfo
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- CN110220688B CN110220688B CN201910588939.7A CN201910588939A CN110220688B CN 110220688 B CN110220688 B CN 110220688B CN 201910588939 A CN201910588939 A CN 201910588939A CN 110220688 B CN110220688 B CN 110220688B
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Abstract
The invention discloses a fatigue testing method for a wind driven generator blade, which comprises the following steps: mounting a tilt angle sensor and a strain gauge on the blade; respectively applying static loads with different sizes on the blade tips of the blades, and collecting corresponding torsion angles and strain values; analyzing the torsion angle and the strain value of the blade to obtain the relation between the unit torsion angle and the strain value; applying dynamic load to the blade, and collecting the torsion angle and the strain value of the blade; calculating strain values generated by unit torque of corresponding torsion angles of the blades during dynamic calibration; eliminating a strain value caused by torque to obtain a strain value generated by bending moment of the blade during dynamic calibration; and obtaining a relation function of the bending moment and the strain during dynamic calibration through analysis, and obtaining a result in the fatigue test. According to the invention, the influence of the torque on the strain coupling of the blade in the dynamic calibration is eliminated, the relation between the bending moment and the strain of the blade is obtained, and a more accurate blade fatigue test result can be obtained.
Description
Technical Field
The invention relates to the technical field of wind power generation, in particular to a fatigue testing method for a wind driven generator blade.
Background
With the trend of high power of the wind generating set, the large-scale development of the wind power blade is driven from the internal aspect. The fatigue test is a key link for verifying the large blade type. The fatigue load of the blade is provided in the form of bending moment or force loaded on the blade section, and the fatigue accumulated damage of the blade is counted by strain data of materials. Therefore, fatigue testing of a blade requires establishing a relationship between the bending moment and the strain of the blade.
The calibration mode in the prior art is to install strain gauges on the front edge and the rear edge of the blade, a PS (windward) main beam and an SS (leeward) main beam, and to apply load at the position of a blade tip to obtain a transfer function between bending moment and strain on the section of the blade. However, when the excitation equipment is used for dynamically and circularly loading the blade, in addition to the bending moment, torque is easily introduced, so that the vibration shape of the blade in a static state is inconsistent with the vibration shape of the blade in a dynamic state, and therefore, when the blade is statically calibrated, the transfer functions of the strain and the bending moment of the front edge and the rear edge of the section of the blade or the main beams of the PS surface and the SS surface cannot truly reflect the condition of the blade in the dynamic loading.
For blades only a few meters in length, the torque is not much affected and the above conventional test method can be used. However, as the blades are made larger and larger, for large blades with a length of several tens of meters, the influence of the torque of the blades during vibration is more serious, and the accumulated damage on the blade section cannot be truly reflected by applying the traditional fatigue testing method. If the traditional blade fatigue test method is adopted, when the strain loading is insufficient in the fatigue test, the fatigue test cannot cover the accumulated fatigue damage of the blade, so that the reliability of the blade is reduced; when strain overloads in a fatigue test, the fatigue strength redundancy design of a blade structure is caused, the weight of the blade is increased, and the economical efficiency of the fan is deteriorated.
Disclosure of Invention
The invention aims to solve the technical problem of overcoming the influence of torque on blade strain during the fatigue test of blades in the prior art, and obtaining a relatively real relation between bending moment and blade strain so as to obtain a relatively accurate fatigue test result.
The invention solves the technical problems through the following technical scheme:
a fatigue testing method for a wind driven generator blade is characterized by comprising the following steps:
s1, respectively installing an inclination angle sensor and a strain gauge on a first critical section and a second critical section of the blade, wherein the x axis of the inclination angle sensor is the axial direction of the blade, and the y axis of the inclination angle sensor is the front edge direction and the rear edge direction of the blade;
s2, applying static loads with different sizes to the blade tip of the blade to enable the blade to be twisted, and collecting the twisting angle and the strain value of the blade when the first key section and the second key section are statically calibrated respectively through the tilt angle sensor and the strain gauge;
s3, calculating the relationship between the unit torque of the first key section and the stress value of the second key section by carrying out finite element model analysis on the torsion angle and the strain value of the blade, and obtaining a reference coefficient;
s4, exciting force is sent out through exciting equipment to apply dynamic load to the blade, and when the vibration amplitude of the blade is stable and meets the target requirement, the torsion angle and the strain value of the blade are respectively collected when the first key section and the second key section are dynamically calibrated through the tilt angle sensor and the strain gauge;
s5, calculating strain values generated by unit torque of corresponding torsion angles of the blades during dynamic calibration through the reference coefficients obtained in the step S3;
s6, subtracting the strain value caused by the torque obtained in the step S5 from the strain value obtained when the blade is dynamically calibrated in the step S4 to obtain the strain value caused by the bending moment when the blade is dynamically calibrated;
s7, analyzing by combining a finite element model, decoupling the influence of the bending moment and the torque coupling on the strain, obtaining a relation function of the bending moment and the strain during dynamic calibration, and further obtaining the result of the blade in the fatigue test;
wherein: the first key section is a maximum chord length section of the blade, a blade root section is transited from a circle to an airfoil-shaped region, a lap joint transition region of different structural materials or a dangerous section during structural design, and the second key section is positioned at a PS surface main beam, an SS surface main beam, a PS surface rear edge, an SS surface rear edge and a blade front edge.
Preferably, the dangerous section when the structure is designed comprises a region with the lowest safety factor of static strength and fatigue strength or a region with a lower stability coefficient.
Preferably, the tilt angle sensor is provided with a plurality of first key cross sections, and the plurality of first key cross sections are respectively installed in a one-to-one correspondence manner.
Preferably, after the torsion angle is obtained in step S2, the unit torques corresponding to the torsion angles of the other first critical cross sections are obtained through formula calculation, and then the finite element model analysis in step S3 is performed to obtain the relationship between the unit torques and the stress values;
wherein the formula is:
in the formula:
α1the torsion angle of the blade root is 0 at the initial value;
αithe twist angle of the previous section;
αi+1the twist angle of the latter section;
i, i is 1,2, n is the corresponding section serial number, and n is the last section;
t, torque;
Δ l, cross-sectional length;
GIpicorresponding section torsional stiffness;
torsional stiffness GI of each first critical section of the bladepiAnd the cross-sectional length deltal is derived from the structural characteristics of the blade at design time.
Preferably, the first critical section is a maximum chord length section of the blade.
Preferably, the vibration frequency of the vibration excitation equipment is 0.3-0.8 Hz.
Preferably, the parameters of the tilt sensor require the following: the angle test range is-60 degrees to 60 degrees, the resolution is 0.01 degrees, and the sampling frequency is 20 Hz to 40 Hz.
Preferably, the tilt sensor is an acceleration sensor.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows: when the fatigue test method for the blades of the wind driven generator is used for carrying out fatigue test on the blades, the relation between bending moment and blade strain is obtained by eliminating the influence of torque on the strain coupling of the blades in dynamic calibration, and a more accurate blade fatigue test result can be obtained, so that the method is suitable for the fatigue test of large blades.
Drawings
FIG. 1 is a flow chart of a method of fatigue testing for a blade of a wind turbine according to the present invention.
FIG. 2 is a schematic view of the blade twisted under external load according to the present invention.
Fig. 3 is a structural view of the mounting position of the strain gauge in the present invention.
Description of reference numerals:
inclination sensor mounting position 11
PS surface main beam 21
SS face main beam 22
PS-face trailing edge 23
SS face trailing edge 24
Vane leading edge 25
Detailed Description
The invention is further illustrated by the following examples, which are not intended to limit the scope of the invention.
As shown in fig. 1 to 3, a fatigue testing method for a blade of a wind power generator of the present invention includes the steps of:
step S1, respectively installing an inclination angle sensor and a strain gauge on a first key section and a second key section of the blade, wherein the x axis of the inclination angle sensor is the axial direction of the blade, and the y axis of the inclination angle sensor is the front edge direction and the rear edge direction of the blade;
step S2, respectively applying static loads with different sizes to the blade tips of the blades to enable the blades to be twisted, and respectively collecting the twisting angle and the strain value of the blades when the first key section and the second key section are statically calibrated through the tilt angle sensor and the strain gauge;
step S3, calculating the relationship between the unit torque of the first key section and the stress value of the second key section respectively by carrying out finite element model analysis on the torsion angle and the strain value of the blade to obtain a reference coefficient;
step S4, exciting force is sent out through exciting equipment to apply dynamic load to the blade, and when the vibration amplitude of the blade is stable and meets the target requirement, the torsion angle and the strain value of the blade are respectively collected when the first key section and the second key section are dynamically calibrated through the tilt angle sensor and the strain gauge;
step S5, calculating strain values generated by unit torque of corresponding torsion angles of the blades during dynamic calibration through the reference coefficients obtained in the step S3;
in the step, the stress value of the blade generated by the torque under the dynamic load is deduced through the relation between the torque and the strain value obtained by the blade under the static load.
Step S6, subtracting the strain value caused by the torque obtained in the step S5 from the strain value obtained when the blade is dynamically calibrated in the step S4 to obtain the strain value caused by the bending moment of the blade during dynamic calibration;
in this step, the stress value generated by the torque is subtracted from the stress value generated after the measured torque and bending moment are coupled, that is, the stress value of the torque is decoupled, and the distribution of the strain value generated by the bending moment can be obtained. The method mainly aims to achieve the purpose of eliminating the torque influence of the blade during vibration, so that the strain obtained during vibration of the blade truly reflects the bending moment level.
And step S7, analyzing by combining a finite element model, decoupling the influence of the bending moment and the torque coupling on the strain, obtaining a relation function of the bending moment and the strain during dynamic calibration, and further obtaining the result of the blade in the fatigue test.
In the step, the influence of the bending moment and the torque coupling on the strain is decoupled by combining finite element model analysis, a relation function of the bending moment and the strain during dynamic calibration is obtained, and a Goodman curve of a material is combined for evaluating the fatigue accumulated damage of the blade.
When the fatigue test method for the blade of the wind driven generator is used for carrying out fatigue test on the blade, the relation between the bending moment and the blade strain is obtained by eliminating the influence of the torque on the blade strain coupling in dynamic calibration of the blade, so that a more accurate blade fatigue test result can be obtained, and the method is suitable for the fatigue test of a large blade.
According to the invention, the torsional deformation distribution of the blade is solved by testing the torsional angle of the key section when the blade vibrates and combining the torsional rigidity information of the blade. And extracting strain distributions of the PS surface main beam 21, the SS surface main beam 22, the PS surface rear edge 23, the SS surface rear edge 24 and the blade front edge 25 of the blade corresponding to the unit torsion angle respectively according to the finite element model. The above data is utilized in blade calibration to eliminate the effect of torque on blade flap and edgewise bending moments. The calibration strain can truly reflect the waving or shimmy bending moment, and the influence of torque coupling is eliminated. When the damage of the front edge and the rear edge of the blade is statically and dynamically calibrated, a fatigue test calibration scheme of a torsion angle test is added, so that fatigue strength of the blade is truly reflected by fatigue accumulated damage counted in a test result, the condition of insufficient design or redundancy of structural fatigue strength is prevented, and the reliability of the blade is improved.
In this embodiment, the first critical cross section is one or more of a maximum chord length cross section of the blade, a transition area of a blade root from a circle to an airfoil shape, a lap joint transition area of different structural materials, or a dangerous cross section in structural design, for example, the maximum chord length cross section of the blade may be selected as the first critical cross section, because a torsion angle generated by the blade is larger than that generated by other cross sections, when a plurality of first critical cross sections are selected, a tilt angle sensor needs to be installed on each first critical cross section to obtain the torsion angle of each first critical cross section; the second critical section positions are the PS surface main beam 21, the SS surface main beam 22, the PS surface rear edge 23, the SS surface rear edge 24 and the blade front edge 25.
The dangerous section of the blade in the structural design comprises a region with the lowest safety factors of static strength and fatigue strength or a region with a lower stability coefficient. The positions are easy to twist under the action of external force and can be used as first key sections for testing the twisting angle of the blade.
In this embodiment, if only one or a few first key cross sections are selected, after the related torsion angles are obtained through the tilt angle sensor, the unit torques corresponding to the torsion angles of other first key cross sections are obtained through formula calculation, and then the finite element model analysis in step S3 is performed on the blade to obtain the relationship between the unit torques and the stress values;
wherein, the formula is:
in the formula:
α1the torsion angle of the blade root is 0 at the initial value;
αithe twist angle of the previous section;
αi+1the twist angle of the latter section;
i, i is 1,2, n is the corresponding section serial number, and n is the last section;
t, torque;
Δ l, cross-sectional length;
GIpicorresponding section torsional stiffness;
torsional stiffness GI of each first critical section of bladepiAnd the cross-sectional length deltal is derived from the structural characteristics of the blade at design time.
In the embodiment, the vibration frequency of the vibration excitation equipment is 0.3-0.8 Hz, and the vibration excitation equipment with the proper vibration frequency is selected according to the size of the blade to be tested. Excitation devices of other vibration frequencies may also be used when the blade to be tested is larger or smaller.
In the present embodiment, the parameters of the tilt sensor are required as follows: the angle test range is-60 degrees to 60 degrees, the resolution is 0.01 degrees, and the sampling frequency is 20 Hz to 40 Hz. Tilt angle sensor using other parameters
In this embodiment, the tilt sensor is preferably a multi-axis multi-functional acceleration sensor with high precision, and other sensors capable of measuring a torsion angle may be used.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (7)
1. A fatigue testing method for a wind turbine blade is characterized by comprising the following steps:
s1, respectively installing an inclination angle sensor and a strain gauge on a first critical section and a second critical section of the blade, wherein the x axis of the inclination angle sensor is the axial direction of the blade, and the y axis of the inclination angle sensor is the front edge direction and the rear edge direction of the blade;
s2, applying static loads with different sizes to the blade tip of the blade to enable the blade to be twisted, and collecting the twisting angle and the strain value of the blade when the first key section and the second key section are statically calibrated respectively through the tilt angle sensor and the strain gauge;
s3, calculating the relationship between the unit torque of the first key section and the strain value of the second key section by carrying out finite element model analysis on the torsion angle and the strain value of the blade to obtain a reference coefficient;
s4, exciting force is sent out through exciting equipment to apply dynamic load to the blade, and when the vibration amplitude of the blade is stable and meets the target requirement, the torsion angle and the strain value of the blade are respectively collected when the first key section and the second key section are dynamically calibrated through the tilt angle sensor and the strain gauge;
s5, calculating strain values generated by unit torque of corresponding torsion angles of the blades during dynamic calibration through the reference coefficients obtained in the step S3;
s6, subtracting the strain value caused by the torque obtained in the step S5 from the strain value obtained when the blade is dynamically calibrated in the step S4 to obtain the strain value caused by the bending moment when the blade is dynamically calibrated;
s7, analyzing by combining a finite element model, decoupling the influence of the bending moment and the torque coupling on the strain, obtaining a relation function of the bending moment and the strain during dynamic calibration, and further obtaining the result of the blade in the fatigue test;
wherein: the first key section is a maximum chord length section of the blade, a blade root section is transited from a circle to an airfoil-shaped region, a lap joint transition region of different structural materials or a dangerous section during structural design, and the second key section is positioned at a PS surface main beam, an SS surface main beam, a PS surface rear edge, an SS surface rear edge and a blade front edge.
2. A fatigue testing method for a wind turbine blade according to claim 1, wherein the critical section in the structural design includes a region where the safety factor of static strength and fatigue strength is lowest or a region where the stability factor is low.
3. The fatigue testing method for a wind turbine blade according to claim 1, wherein a plurality of the tilt sensors are installed, and are respectively installed on a plurality of the first critical sections in a one-to-one correspondence.
4. The fatigue testing method for the wind turbine blade according to claim 1, wherein after the torsion angle is obtained in step S2, the unit torques corresponding to the torsion angles of the other first critical cross sections are obtained through formula calculation, and then the finite element model analysis in step S3 is performed to obtain the relationship between the unit torque and the stress value;
wherein the formula is:
in the formula:
α1the torsion angle of the blade root is 0 at the initial value;
αithe twist angle of the previous section;
αi+1the twist angle of the latter section;
i, i is 1,2, n is the corresponding section serial number, and n is the last section;
t, torque;
Δ l, cross-sectional length;
GIpicorresponding section torsional stiffness;
torsional stiffness GI of each of the first critical cross-sections of the bladepiAnd the cross-sectional length deltal is derived from the structural characteristics of the blade at design time.
5. The fatigue testing method for the blades of the wind driven generator according to claim 1, wherein the vibration frequency of the excitation device is 0.3 to 0.8 Hz.
6. A fatigue testing method for a wind turbine blade according to claim 1, wherein the parameters of said pitch sensor are as follows: the angle test range is-60 degrees to 60 degrees, the resolution is 0.01 degrees, and the sampling frequency is 20 Hz to 40 Hz.
7. A fatigue testing method for a wind turbine blade according to any of claims 1-6, wherein said pitch sensor is an acceleration sensor.
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| CN111795899B (en) * | 2020-07-30 | 2023-08-04 | 上海电气风电集团股份有限公司 | Torsion loading equipment and blade torsion testing method |
| CN112129503A (en) * | 2020-09-16 | 2020-12-25 | 明阳智慧能源集团股份公司 | Fan blade torsional fatigue test device and test method thereof |
| CN114323602B (en) * | 2021-11-30 | 2024-03-26 | 明阳智慧能源集团股份公司 | Static testing method and system for fan blade |
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