METHOD AND TESTING DEVICE FOR SIMULTANEOUSLY TESTING TWO ROTOR BLADES AND/OR TWO ROTOR BLADE SEGMENTS FOR A WIND POWER INSTALLATION

Abstract

A testing device for simultaneously testing two rotor blades and/or two rotor blade segments for a wind power installation, to a method for simultaneously testing two rotor blades and/or two rotor blade segments for a wind power installation, to a method for testing a rotor blade and/or a rotor blade segment for a wind power installation, and to the use of a testing device for testing a rotor blade and/or a rotor blade segment for a wind power installation and/or for simultaneously testing two rotor blades and/or two rotor blade segments for a wind power installation. The testing device comprises a first adapter element for fastening thereto a first rotor blade or rotor blade segment, a second adapter element for fastening thereto a second rotor blade or rotor blade segment, a support structure to which the first and the second adapter element are fastened so as to be rotatable about a common rotation axis, an excitation device which is configured to apply a static and/or cyclic load to the first and/or the second rotor blade or rotor blade segment, wherein the first and the second adapter element are connected to each other.

Claims

1. A testing device for simultaneously testing two rotor blades and/or two rotor blade segments for a wind power installation, the testing device comprising: a first adapter element configured for fastening to a first rotor blade or a first rotor blade segment; a second adapter element configured for fastening to a second rotor blade or a rotor blade segment; a support structure, the first and the second adapter elements fastened to the support structure; an excitation device configured to apply at least one load chosen from a static load and cyclic load to the first and/or the second rotor blades or the first and/or second rotor blade segments; wherein the first and the second adapter elements are connected to each other.

2. The testing device according to claim 1, wherein the first and the second adapter elements are fastened to the support structure so as to be rotatable about a common rotation axis, wherein the common rotation axis is aligned so as to be substantially orthogonal to longitudinal axes of first and second rotor blades and/or the first and second rotor blade segments that during the testing operation are fastened to the first and/or the second adapter elements.

3. The testing device according to claim 2, wherein the common rotation axis is aligned so as to be horizontal and/or vertical; and/or wherein the common rotation axis is configured so as to be adjustable between a horizontal position and a vertical position.

4. The testing device according to claim 1, wherein the support structure is configured to absorb lateral forces and bending moments, wherein a ratio of the bending moments in kNm able to be absorbed by the support structure to the lateral forces in kN able to be absorbed by the support structure is at most 15.

5. The testing device according to claim 1, comprising a foundation, wherein the foundation is configured to absorb lateral forces and bending moments, wherein a ratio of the bending moments in kNm able to be absorbed by the support structure to the lateral forces in kN able to be absorbed by the support structure is at most 15.

6. The testing device according to claim 1, wherein a link between the support structure and a foundation is configured to absorb lateral forces and bending moments, wherein a ratio of the bending moments in kNm able to be absorbed by the support structure to the lateral forces in kN able to be absorbed by the support structure is at most 15.

7. The testing device according to claim 1, wherein the first and the second adapter elements mutually include an angle of 0° to 40°, and/or wherein the first adapter element in relation to a vertical includes an angle of 0° to 20° or 0° to 5°, and/or the second adapter element in relation to the vertical includes an angle of 0° to 20° or 0° to 5°.

8. The testing device according to claim 1, wherein the longitudinal axis of the first rotor blade or the first rotor blade segment and the longitudinal axis of the second rotor blade or the second rotor blade segment mutually include an angle of 180° to 140° or 180° to 170°; and/or wherein the longitudinal axis of the first rotor blade or the first rotor blade segment in relation to the horizontal includes an angle of 0° to 20° or 0° to 5°, and/or the longitudinal axis of the second rotor blade or the second rotor blade segment in relation to the horizontal includes an angle of 0° to 20° or 0° to 5°.

9. The testing device according to claim 1, wherein the first and/or the second adapter elements are configured as an adapter plate, wherein the first adapter element and the second adapter element are connected directly to each other and to the support structure by ties, and/or wherein two or more spacers are disposed between the first and the second adapter element; and/or wherein the excitation device comprises at least one actuator, wherein the excitation device is configured to identically excite the first and the second rotor blades or the first and second rotor blade segments in a synchronous manner and/or at a same frequency.

10. The testing device according to claim 1, wherein the testing device is configured to be able to be disassembled and transported, wherein a plurality of component parts of the testing device are configured to be transported conjointly in at least one of a container, an ISO container motor truck, a motor truck of up to 40 ton, a semitrailer or a semitrailer having maximum external dimensions of 13.68 m×2.55 m×4.00 m.

11. A method for simultaneously testing first and second rotor blades or first and second rotor blade segments for a wind power installation, the method comprising: fastening the first rotor blade or the first rotor blade segment to a first adapter element; fastening the second rotor blade or the second rotor blade segment to a second adapter element; connecting first and the second adapter elements to each other; disposing the first and the second adapter elements on a support structure; and applying a static load and/or a cyclic load to the first and/or the second rotor blades or the first and/or second rotor blade segments.

12. The method according to claim 11, wherein the first and/or the second rotor blade segments comprises a region of 30% to 99%, of an overall length of the rotor blade; and/or wherein the first and the second rotor blades or the first and second rotor blade segments are of substantially identical configuration; and/or comprising applying in a synchronized manner a cyclic load to the first and the second rotor blades or the first and second rotor blade segments.

13. A method for testing s component of for a wind power installation, said method comprising: fastening a first rotor blade or a rotor blade segment to a first adapter element; disposing the first adapter element on a support structure; and applying at least one load chosen from a static load and a cyclic load to the first second rotor blade or the rotor blade segment.

14. The method according to claim 13, wherein fastening comprises fastening the rotor blade segment to the first adapter element, wherein the rotor blade segment comprises a region of 30% to 99% of an overall length of the rotor blade.

15. The method according to claim 14, comprising disposing a counter element that is adjustable to an inherent frequency of the first rotor blade segment on a second adapter element.

16. A method comprising: transporting a testing device according to claim 1 to a testing site, wherein transporting comprises transporting the testing device in a disassembled form; providing a foundation at the testing site; and erecting the testing device at the testing site.

17. A use of a testing device according to claim 1 comprising: simultaneously testing two rotor blades for a wind power installation, and/or simultaneously testing two rotor blades segments for the wind power installation.

Description

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

[0063] Preferred exemplary embodiments will be described by way of example by means of the appended figures in which:

[0064] FIG. 1 shows a schematic illustration of a wind power installation;

[0065] FIG. 2a shows a schematic illustration of an exemplary embodiment of a testing device for a fatigue test using two rotor blade segments;

[0066] FIG. 2b shows an enlarged illustration of a detail from FIG. 2a;

[0067] FIG. 3 shows a schematic illustration of an exemplary embodiment of a testing device for a static test using two rotor blades;

[0068] FIG. 4a shows a schematic three-dimensional view of an exemplary embodiment of a testing device for a fatigue test using two rotor blades;

[0069] FIG. 4b shows a schematic lateral view of the testing device according to FIG. 4a;

[0070] FIG. 4c shows an enlarged illustration of a detail from FIG. 4a;

[0071] FIG. 4d shows an enlarged illustration of a detail of the testing device according to FIG. 4a, without adapter element and rotor blade;

[0072] FIG. 4e shows a schematic three-dimensional view of the testing device according to FIG. 4a, having an excitation device;

[0073] FIG. 4f shows an enlarged illustration of a detail of the testing device according to FIG. 4e;

[0074] FIG. 5 shows a schematic flow chart of an exemplary embodiment of a method for simultaneously testing two rotor blades and/or two rotor blade segments for a wind power installation; and

[0075] FIG. 6 shows a schematic flow chart of an exemplary embodiment of a method for testing a rotor blade and/or a rotor blade segment for a wind power installation.

[0076] In the figures, identical or substantially functionally equivalent elements are provided with the same reference signs. General descriptions typically refer to all embodiments unless differences are explicitly set forth.

DETAILED DESCRIPTION

[0077] FIG. 1 shows a schematic illustration of a wind power installation 100 in which rotor blades 108 are used. The wind power installation 100 has tower 102 and a nacelle 104 on the tower 102. An aerodynamic rotor 106 having three rotor blades 108 and a spinner 110 is provided on the nacelle 104. During the operation of the wind power installation the aerodynamic rotor 106 is set in a rotating movement by the wind, thus also rotating an electrodynamic rotor or rotor of a generator, which is coupled directly or indirectly to the aerodynamic rotor 106. The electric generator is disposed in the nacelle 104 and generates electric energy. The pitch angles of the rotor blades 108 can be varied by pitch motors on the rotor blade roots 109 of the respective rotor blades 108.

[0078] FIG. 2a shows a schematic illustration of an exemplary embodiment of a testing device 20 for a fatigue test using two rotor blade segments 108′. FIG. 3 shows a schematic illustration of an exemplary embodiment of a testing device 20′ for a static test using two rotor blade segments 108′. The two testing devices 20, 20′ differ from each other in particular in terms of the excitation devices 30a, 30b, 30′a, 30′b.

[0079] Both testing devices 20, 20′ are disposed on a foundation 1 which may also be referred to as a test platform.

[0080] Both testing devices 20, 20′ comprise in each case one first adapter element 21a in the form of an adapter plate, and a second adapter element 21b in the form of an adapter plate. The flanges of the rotor blade segments 108′ are fastened, preferably screwed, to these adapter elements.

[0081] As can be seen in particular in FIG. 2b, the first and the second adapter element 21a, 21b mutually include an angle α of approx. 40°, wherein the first adapter element 21a in relation to the vertical includes an angle β.sub.a of approx. 20°, and the second adapter element 21b in relation to the vertical includes an angle β.sub.b of 0° to 20°.

[0082] Furthermore, the longitudinal axis L of the first rotor blade segment 108′ and the longitudinal axis L of the second rotor blade segment 108′ mutually include an angle γ of approx. 140°. The longitudinal axis L of the first rotor blade segment in relation to the horizontal includes an angle δ.sub.a of approx. 20°, and the longitudinal axis L of the second rotor blade segment in relation to the horizontal includes an angle δ.sub.b of 0° to 20°.

[0083] The testing device 20 for a fatigue test using two rotor blade segments 108′ according to FIG. 2a has an excitation device 30a, 30b, which comprises two sub-excitation devices. Each of the sub-excitation devices preferably comprises a load bracket 32a, 32b, an actuator 31a, 31b (for example in the form of a hydraulic actuating drive), and is disposed on a concrete block 33a, 33b. Like the foundation 1, the concrete blocks 33a, 33b, can be produced on site with little financial outlay. The sub-excitation devices, in particular the load brackets 32a, 32b, thereof, are fastened to the rotor blade segments 108′ at a spacing from the blade root.

[0084] The excitation device 30a, 30b, is configured to excite the rotor blade segments 108′by way of cyclic fatigue loads and to set the rotor blade segments 108′ in vibration, wherein upward as well as downward flexing D is created at the tip of the rotor blade segments 108′.

[0085] In such a fatigue experiment, a fatigue load is preferably applied by exciting the first or the second inherent frequency of the rotor blades and/or rotor blade segments (in particular in a flap-wise and/or lead-lag-wise test). A preferably synchronous excitation of the two rotor blades and/or rotor blade segments to the inherent frequency vibration in the vertical direction can take place, for example, by way of an excitation device 30a, 30b, in the form of hydraulic cylinders 31a, 31b, which are coupled by load brackets 32a, 32b.

[0086] In a static test as is illustrated in FIG. 3, the rotor blade segments 108′ are tested in a quasi-static manner using extreme loads. To this end, an excitation device 30′a, 30′b, having a plurality of sub-excitation devices can be used. Each of the sub-excitation devices preferably comprises a load bracket 32a, 32b, an actuator 34a, 34b (for example in the form of an electric winch), and is disposed on a concrete block 33a, 33b. The rotor blade segments 108′ are deflected downward by way of the actuators 34a, 34b. The concrete blocks 33a, 33b, can serve as counterweights. Here too, no bending moments, or no significant bending moments, have to be directed into the foundation. Only the vertical counter forces, or primarily the vertical counter forces, of the rotor blade segments 108′ and of the test loads are to be directed into the foundation. The foundation 1 for such loads is relatively easy to install, just like the concrete blocks 33a, 33b.

[0087] Moreover, the directions of the arising lateral forces Q.sub.+, Q.sub.− and bending moments M.sub.+, M.sub.− are set forth in FIG. 2b.

[0088] In conventional rotor blade test beds according to the prior art, the bending moment applied to the blade flange has to be transmitted into the foundation and into the ground by way of the test bed construction. In the testing devices 20, 20′ described here, the bending moment M.sub.+, M.sub.− acting on the blade flange is absorbed directly by the second rotor blade or rotor blade segment, the latter being assembled “back-to-back” (or else “flange-to-flange”). In the solution described here, the support structure experiences no bending moment stress, or only an extremely low bending moment stress. Only moderate vertical fatigue loads, or primarily moderate vertical fatigue loads, in the form of lateral forces Q.sub.+, Q.sub.− are to be handled. The solution described here, therefore, leads to a test bed for very large rotor blades and/or rotor blade segments at minimal investment costs.

[0089] Both testing devices 20, 20′ according to FIGS. 2a and 3 are configured such that they excite rotor blades and/or rotor blade segments in a vertical direction. The testing devices 20, 20′ can preferably also be configured such that they excite rotor blades and/or rotor blade segments in a horizontal direction. To this end, the testing devices 20, 20′ can be configured so as to be correspondingly adjustable.

[0090] According to FIGS. 2a and 3, the flanges of the two rotor blade segments 108′ are disposed “back-to-back”, which may also be referred to as “shorting”. As a result, the flange moments are cancelled directly between the two flanges. For this purpose, two identical rotor blades or rotor blade segments 108′ are preferably used.

[0091] A schematic illustration of an exemplary embodiment of a testing device 200 for a fatigue test using two rotor blades is shown in FIGS. 4a-4f. Tests using two identical rotor blades 108 were carried out here.

[0092] The two rotor blades 108 by way of two adapter plates 121a, 121b, are connected to each other and to the support structure 210 by means of screw connections 215, 216. The adapter plates 121a, 121b, are screwed to one another (“back-to-back”) by way of the swivel pin 214, which is mounted in an articulated manner, of the support structure 210. Spacers can preferably be disposed between the adapter plates 121a, 121b.

[0093] The support structure 210 by way of a foundation attachment 211 is disposed on a foundation 1 which during operation has to absorb almost only vertical loads.

[0094] The support structure 210 comprises two steel profiles 212, for example HEB profiles, which are substantially perpendicular during operation and are connected to each other by way of upper cross members 213o and a lower cross member 213u. Furthermore, the swivel pin 214, which is mounted in an articulated manner, connects the steel profiles 212.

[0095] The two adapter plates 121a, 121b, are suspended on the common swivel pin 214 so as to reinforce the effect that ideally no bending moment is transmitted to the support structure 210 and/or the foundation 1. The two adapter plates 121a, 121b, by way of ties 216 are connected directly to each other, and by way of ties 215 are connected to the support structure 210 by way of the pendulum elements 217 suspended on the swivel pin 214. The rotor blade flanges can be screwed to the adapter plates 121a, 121b, from the insides of the latter. The adapter plates 121a, 121b, are preferably mutually spaced apart.

[0096] The testing device 200 furthermore has an excitation device 130a, as can be seen in particular in FIGS. 4e and 4f. One load bracket 132a, 132b is disposed on each of the rotor blades 108, this being preferable when both rotor blades 108 are excited, but when exciting only one rotor blade 108 also has the advantage that the inherent frequencies of the two rotor blades can be adjusted as similarly as possible. Only one rotor blade 108 was excited in the test illustrated in FIGS. 4e and 4f To this end, an actuator 131a is coupled to the load bracket 132a, in the example here a pneumatic actuator is coupled to the load bracket 132a and actuated so as to excite the rotor blades 108 at the first inherent frequency. The actuation of the actuator 131a takes place, for example, by way of a soft programmable controller which is integrated in a PMX measurement amplifier of HBM. When a further actuator is coupled to the second load bracket 132b, both rotor blades can also be directly excited simultaneously by the testing device 200. If only one rotor blade 108 is excited directly by way of an actuator, the second rotor blade oscillates conjointly by way of the direct coupling and the back-to-back arrangement of the two rotor blades.

[0097] In an experiment using one actuator, both rotor blades 108, when excited at their first inherent frequency, oscillated in a laterally reversed manner in relation to the adapter plates (see FIG. 4e).

[0098] In a test (not illustrated) using two actuators, both rotor blades 108 were excited by an actuator on each rotor blade. Both wings, when excited at their first inherent frequency, oscillated in a laterally reversed manner in relation to the adapter plate.

[0099] Furthermore, the inherent frequency can be changed, for example reduced, by attaching trimming weights, for example in the form of further load brackets, to the rotor blades 108. As a result, adapting the experiment setup to different testing frequencies can be easily performed.

[0100] FIG. 5 shows a schematic flowchart of an exemplary embodiment of a method (1000) for simultaneously testing two rotor blades and/or two rotor blade segments for a wind power installation. In a step 1001, a testing device is preferably transported to the testing site, preferably in the disassembled form, and in a step 1002 is then preferably erected at the testing site. Furthermore preferably, a foundation is provided at the testing site if required.

[0101] In step 1003, a first rotor blade a rotor blade segment is fastened to a first adapter element. In step 1004, a second rotor blade or rotor blade segment is fastened to a second adapter element. In step 1005, the first and the second adapter element are connected to each other and, in step 1006, disposed on a support structure before, in step 1007, a static and/or cyclic load is applied to the first and/or the second rotor blade or rotor blade segment, wherein applying the cyclic load to the first and the second rotor blade or rotor blade segment can take place in a synchronous manner.

[0102] FIG. 6 shows a schematic flowchart of an exemplary embodiment of a method (2000) for testing a rotor blade and/or a rotor blade segment for a wind power installation. In a step 2001, a first rotor blade or rotor blade segment is fastened to the first adapter element, and the first adapter element is disposed on a support structure in step 2002. It is furthermore preferable that, in step 2003, a counter element, in particular in the form of a single mass oscillator, which is preferably adjustable to the inherent frequency of the first rotor blade or rotor blade segment, is fastened to the second adapter element. In step 2004, a static and/or cyclic load is then applied to the first second rotor blade or rotor blade segment.

[0103] The method steps described here are preferably carried out in the sequence mentioned. Depending on the situation, however, deviations from the sequence mentioned here are also possible within the context of technical feasibility.

[0104] The various embodiments described above can be combined to provide further embodiments. These and other changes can be made to the embodiments in light of the above-detailed description. In general, in the following claims, the terms used should not be construed to limit the claims to the specific embodiments disclosed in the specification and the claims, but should be construed to include all possible embodiments along with the full scope of equivalents to which such claims are entitled. Accordingly, the claims are not limited by the disclosure.