Rigidity-adjustable test blade structure

Abstract

The invention provides a rigidity-adjustable test blade structure which comprises a blade shell, the blade shell is provided with a hollow area and a solid area, and the solid area is located on the peripheral side of the hollow area; wherein a plurality of hollow shells are arranged at the joint of the hollow area and the entity area, and the plurality of hollow shells are arranged at intervals; the test blade structure further comprises a plurality of embedded assemblies, and at least one of the embedded assemblies is selectively filled into at least one of the hollow shells according to rigidity change required by the test blade structure, so that the blade shell is detachably connected with the embedded assemblies. The problems that in the prior art, the rigidity of blades is fixed, when the blades with different structural characteristics are subjected to aeroelastic energy comparison, the blades with different rigidities need to be machined for testing, and therefore the machining period and the machining cost are increased, and the machining cost is reduced are solved. And the economical efficiency of testing and comparing the aeroelastic properties of the blades with different rigidities is not facilitated.

Description

Technical Field

[0001] The invention relates to the technical field of wind power generation blades, and in particular to a test blade structure with adjustable stiffness. Background Art

[0002] With the rapid development of the wind power industry, the demand for large blades and lightweight is increasing day by day. How to design wind turbine blades that meet the requirements of large scale and lightweight and have better performance has become an important research topic in the current wind power field. The flexibility of existing large blades is constantly increasing, which has a great impact on the load and performance of the blades. The errors caused by simulation tools are getting bigger and bigger, and it is necessary to understand and master their aeroelastic response characteristics through experiments. However, the full-scale experiment of large wind turbine blades is very expensive. In order to reduce the experimental cost and ensure the design reliability of the blades, it is necessary to carry out scaled blade design, manufacturing and experiments.

[0003] In order to compare the aeroelastic performance of blades with different structural characteristics, it is necessary to process blades with different stiffness for testing. However, due to the small processing size of such blades and the high requirements for layer positioning and processing accuracy, processing different blades may bring about many changes in structural performance parameters, which is not conducive to performance comparison. At the same time, it increases the processing cycle and processing cost, which is not conducive to the aeroelastic performance test comparison of blades with different stiffness. Summary of the invention

[0004] The main purpose of the present invention is to provide a test blade structure with adjustable stiffness to solve the problem in the prior art that when comparing the aeroelastic performance of blades with different structural characteristics, it is necessary to process blades with different stiffnesses for testing. However, since the processing size of such blades is small and the layer positioning and processing accuracy requirements are high, processing different blades may bring about many changes in structural performance parameters, which is not conducive to performance comparison. At the same time, it increases the processing cycle and processing cost, which is not conducive to the aeroelastic performance test comparison of blades with different stiffnesses.

[0005] In order to achieve the above-mentioned objectives, the present invention provides a test blade structure with adjustable stiffness, including a blade shell, the blade shell having a hollow area and a solid area, and the solid area is located on the outer peripheral side of the hollow area; wherein a plurality of hollow shells are arranged at the connection between the hollow area and the solid area, and the plurality of hollow shells are arranged at intervals; the test blade structure also includes a plurality of embedded components, at least one of the plurality of embedded components is selectively filled into at least one of the plurality of hollow shells according to the stiffness change required for the test blade structure, so that the blade shell is detachably connected to the embedded component.

[0006] In an exemplary embodiment, the cross-sectional profile of the hollow shell is at least one of a square, a circle, and an ellipse.

[0007] In an exemplary embodiment, the blade shell and the plurality of hollow shells are integrally formed.

[0008] In an exemplary embodiment, the contour line formed at the connection between the hollow area and the solid area includes a first area, a second area, and a third area in sequence in the direction from the head to the tail of the blade shell, wherein the test blade structure also includes a web, and at least one web is supported between at least two relatively arranged hollow shells in the second area.

[0009] In an exemplary embodiment, there are multiple webs, at least two of the multiple webs are used to connect two relatively arranged hollow shells in the second area, and in the direction from the first area to the third area, the thickness of the web close to the first area is not less than the thickness of the web close to the third area.

[0010] In an exemplary embodiment, at least the cross-sectional area of ​​the cross-section of the hollow shell in the second region is uniform.

[0011] In an exemplary embodiment, the cross-sectional length of the cross section of the hollow shell located in the first area is not less than the cross-sectional length of the cross section of the hollow shell located in the second area; and / or the cross-sectional length of the cross section of the hollow shell located in the third area is not less than the cross-sectional length of the cross section of the hollow shell located in the second area.

[0012] In an exemplary embodiment, the embedded component includes multiple stacked reinforcement layers.

[0013] In an exemplary embodiment, in the stacking direction of the multiple reinforcement layers, the projection areas of the multiple reinforcement layers are arranged to gradually increase.

[0014] In an exemplary embodiment, in the stacking direction of the multiple reinforcement layers, the thickness of each reinforcement layer is consistent.

[0015] By applying the technical solution of the present invention, a test blade structure with adjustable stiffness is provided, comprising a blade shell, wherein the blade shell has a hollow area and a solid area, and the solid area is located on the outer peripheral side of the hollow area; wherein a plurality of hollow shells are arranged at the connection between the hollow area and the solid area, and the plurality of hollow shells are arranged at intervals; the test blade structure also comprises a plurality of embedded components, wherein at least one of the plurality of embedded components is selectively filled into at least one of the plurality of hollow shells according to the stiffness change required for the test blade structure, so that the blade shell is detachably connected to the embedded component.

[0016] By arranging a plurality of hollow shells at the connection between the hollow area and the solid area, and selectively filling at least one of the plurality of embedded components into at least one of the plurality of hollow shells according to the stiffness change required for the test blade structure, the blade shell and the embedded component are detachably connected, and it is also beneficial to achieve the purpose of changing the stiffness of the test blade structure by filling the embedded components in the hollow shells at different positions. When subsequently performing aeroelastic performance comparison tests on test blade structures with different structural features, it is only necessary to change the stiffness of the test blade structure by filling the embedded components in the hollow shells at different positions, thereby ensuring the economy of the aeroelastic performance test comparison of test blade structures with different stiffnesses. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings constituting a part of the present application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0018] Figure 1 A schematic diagram of the internal structure of a test blade structure according to an optional embodiment of the present invention is shown;

[0019] Figure 2 Shows Figure 1 A schematic diagram of the internal structure of the test blade structure in FIG. 1 , in which a first region, a second region, and a third region are shown;

[0020] Figure 3 A structural schematic diagram of an embedded component according to an optional embodiment of the present invention is shown.

[0021] The above drawings include the following reference numerals:

[0022] 10. Blade shell; 11. Hollow area; 12. Solid area; 13. First area; 14. Second area; 15. Third area;

[0023] 20. Hollow shell;

[0024] 30. Embedded components; 31. Enhancement layer;

[0025] 40. Belly plate. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] In order to solve the problem that the stiffness of blades in the prior art is fixed stiffness, when comparing the aeroelastic performance of blades with different structural characteristics, it is necessary to process blades with different stiffnesses for testing, and since the processing size of such blades is small, the layer positioning and processing accuracy requirements are high, processing different blades may bring about many changes in structural performance parameters, which is not conducive to performance comparison, and at the same time increases the processing cycle and processing cost, which is not conducive to the aeroelastic performance test comparison of blades with different stiffnesses. The present invention provides a test blade structure with adjustable stiffness.

[0028] like Figures 1 to 3 As shown, the stiffness-adjustable test blade structure includes a blade shell 10, the blade shell 10 has a hollow area 11 and a solid area 12, and the solid area 12 is located on the outer peripheral side of the hollow area 11; wherein, a plurality of hollow shells 20 are arranged at the connection between the hollow area 11 and the solid area 12, and the plurality of hollow shells 20 are arranged at intervals; the test blade structure also includes a plurality of embedded components 30, at least one of the plurality of embedded components 30 is selectively filled into at least one of the plurality of hollow shells 20 according to the stiffness change required for the test blade structure, so that the blade shell 10 is detachably connected to the embedded component 30.

[0029] By arranging a plurality of hollow shells 20 at the connection between the hollow area 11 and the solid area 12, and selectively filling at least one of the plurality of embedded components 30 into at least one of the plurality of hollow shells 20 according to the stiffness change required for the test blade structure, the blade shell 10 and the embedded component 30 are detachably connected, and it is also beneficial to achieve the purpose of changing the stiffness of the test blade structure by filling the embedded component 30 in the hollow shells 20 at different positions. When subsequently performing aeroelastic performance comparison tests on test blade structures with different structural features, it is only necessary to fill the embedded component 30 in the hollow shells 20 at different positions to achieve the change of the stiffness of the test blade structure, thereby ensuring the economy of the aeroelastic performance test comparison of test blade structures with different stiffnesses.

[0030] It should be noted that, in the present application, the contour line of the cross section of the hollow shell 20 is at least one of square, circular, and elliptical.

[0031] Preferably, the cross-section of the hollow shell 20 has a square outline, so as to ensure the processing convenience of the test blade structure.

[0032] It should be noted that, in the present application, the blade shell 10 and the plurality of hollow shells 20 are integrally formed, so as to ensure the convenience of processing and manufacturing of the test blade structure, and help reduce the processing and manufacturing procedures and processing and manufacturing costs of the test blade structure.

[0033] like Figure 2 As shown, the contour line formed at the connection of the hollow area 11 and the solid area 12 includes the first area 13, the second area 14, and the third area 15 in the direction from the head to the tail of the blade shell 10, wherein the test blade structure also includes a web 40, and at least one web 40 is supported and arranged between two oppositely arranged hollow shells 20 located at least in the second area 14. In this way, the first area 13, the second area 14, and the third area 15 are separated by dotted lines in the figure to facilitate the accuracy of the description. Since the distance between the two oppositely arranged hollow shells 20 in the second area 14 is relatively long, the web 40 is arranged to effectively support the two oppositely arranged hollow shells 20.

[0034] like Figure 2 As shown, there are multiple webs 40, at least two of which are used to connect two oppositely disposed hollow shells 20 in the second region 14, and in the direction from the first region 13 to the third region 15, the thickness of the web 40 close to the first region 13 is not less than the thickness of the web 40 close to the third region 15. In this way, Figure 2 The thicknesses of the two webs 40 are inconsistent, wherein the thickness of the web 40 close to the first region 13 is greater than the thickness of the web 40 close to the third region 15, ensuring that the test blade structure has sufficient rigidity.

[0035] It should be noted that, in the present application, considering that the space in the second area 14 is relatively large, and in order to ensure the adjustment accuracy and reliability of the stiffness of the test blade structure, preferably, as Figure 1 and Figure 2 As shown, the cross-sectional area of ​​the cross section of the hollow housing 20 at least in the second region 14 is uniform.

[0036] like Figure 1 and Figure 2As shown, the cross-sectional length of the cross section of the hollow shell 20 located in the first area 13 is not less than the cross-sectional length of the cross section of the hollow shell 20 located in the second area 14; and / or, the cross-sectional length of the cross section of the hollow shell 20 located in the third area 15 is not less than the cross-sectional length of the cross section of the hollow shell 20 located in the second area 14. In this way, it is ensured that the contour line of the cross section of each hollow shell 20 can be adapted to the outer contour line of the blade shell 10 as much as possible, that is, the contour line of the cross section of each hollow shell 20 has good conformability.

[0037] like Figure 3 As shown, the embedded component 30 includes multiple stacked reinforcement layers 31. Thus, by configuring the embedded component 30 to include multiple stacked reinforcement layers 31, the reliability of the embedded component 30 in changing the stiffness of the test blade structure is ensured.

[0038] like Figure 3 As shown, in the stacking direction of the multi-layer reinforcement layer 31, the projection area of ​​the multi-layer reinforcement layer 31 is gradually increased.

[0039] It should be noted that, in the present application, in the stacking direction of the multiple reinforcement layers 31 , the thickness of each reinforcement layer 31 is consistent.

[0040] It should be noted that in the present application, the contour line formed at the connection between the hollow area 11 and the solid area 12 is the inner shell of the test blade structure, and the inner shell mainly plays a supporting role. When the stiffness of the test blade structure needs to be adjusted, the embedded component 30 can be filled into the two relatively arranged hollow shells 20 on both sides of the same web 40 in the second area 14, and the remaining hollow shells 20 are not filled. When the stiffness of the test blade structure is insufficient, it can be considered to continue to fill the embedded component 30 into the two relatively arranged hollow shells 20 on both sides of another web 40 in the second area 14, thereby further improving the overall stiffness of the test blade structure.

[0041] Of course, when the stiffness of the test blade structure needs to be increased to increase EI0, ​​the formula EI0 = E × S × (h / 2 + H) can be used. 2 Quantitative control is performed according to the specific parameters of the height h, area S, elastic modulus E of the hollow shell 20 and the height H of the hollow shell 20 from the cross-section line, which are specifically related to the formula, so as to achieve quantitative control of the test blade structure. The hollow shell 20 that needs to be filled.

[0042] By applying the technical solution of the present invention, a test blade structure with adjustable stiffness is provided, comprising a blade shell 10, wherein the blade shell 10 has a hollow area 11 and a solid area 12, and the solid area 12 is located on the outer peripheral side of the hollow area 11; wherein a plurality of hollow shells 20 are arranged at the connection between the hollow area 11 and the solid area 12, and the plurality of hollow shells 20 are arranged at intervals; the test blade structure also comprises a plurality of embedded components 30, wherein at least one of the plurality of embedded components 30 is selectively filled into at least one of the plurality of hollow shells 20 according to the stiffness change required for the test blade structure, so that the blade shell 10 is detachably connected to the embedded component 30.

[0043] By arranging a plurality of hollow shells 20 at the connection between the hollow area 11 and the solid area 12, and selectively filling at least one of the plurality of embedded components 30 into at least one of the plurality of hollow shells 20 according to the stiffness change required for the test blade structure, the blade shell 10 and the embedded component 30 are detachably connected, and it is also beneficial to achieve the purpose of changing the stiffness of the test blade structure by filling the embedded component 30 in the hollow shells 20 at different positions. When subsequently performing aeroelastic performance comparison tests on test blade structures with different structural features, it is only necessary to fill the embedded component 30 in the hollow shells 20 at different positions to achieve the change of the stiffness of the test blade structure, thereby ensuring the economy of the aeroelastic performance test comparison of test blade structures with different stiffnesses.

[0044] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0045] Unless otherwise specifically stated, the relative arrangement of the parts and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present invention. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to ordinary technicians in the relevant field may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be regarded as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0046] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0047] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0048] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0049] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A test blade structure with adjustable stiffness, characterized in that: include: A blade shell (10), the blade shell (10) having a hollow area (11) and a solid area (12), wherein the solid area (12) is located on the outer peripheral side of the hollow area (11); Wherein, a plurality of hollow shells (20) are arranged at the connection between the hollow area (11) and the solid area (12), and the plurality of hollow shells (20) are arranged at intervals; The test blade structure also includes: A plurality of embedded components (30), at least one of the plurality of embedded components (30) is selectively filled into at least one of the plurality of hollow shells (20) according to a stiffness change required for the test blade structure, so that the blade shell (10) and the embedded component (30) are detachably connected.

2. The test blade structure according to claim 1, characterized in that: The cross-sectional contour of the hollow shell (20) is at least one of square, circular and elliptical.

3. The test blade structure according to claim 1, characterized in that: The blade shell (10) and the plurality of hollow shells (20) are integrally formed.

4. The test blade structure according to claim 1, characterized in that: The contour line formed at the connection between the hollow area (11) and the solid area (12) includes a first area (13), a second area (14), and a third area (15) in the direction from the head to the tail of the blade shell (10), wherein the test blade structure also includes a web (40), and at least one of the webs (40) is supported and arranged between at least two of the hollow shells (20) arranged opposite to each other in the second area (14).

5. The test blade structure according to claim 4, characterized in that: There are a plurality of webs (40), at least two of the plurality of webs (40) are used to connect two relatively arranged hollow shells (20) in the second region (14), and in the direction from the first region (13) to the third region (15), the thickness of the web (40) close to the first region (13) is not less than the thickness of the web (40) close to the third region (15).

6. The test blade structure according to claim 4, characterized in that: The cross-sectional area of ​​the cross section of the hollow shell (20) at least in the second region (14) is consistent.

7. The test blade structure according to claim 4, characterized in that: The cross-sectional length of the cross section of the hollow shell (20) located in the first area (13) is not less than the cross-sectional length of the cross section of the hollow shell (20) located in the second area (14); and / or, The cross-sectional length of the cross section of the hollow shell (20) located in the third area (15) is not less than the cross-sectional length of the cross section of the hollow shell (20) located in the second area (14).

8. The test blade structure according to any one of claims 1 to 7, characterized in that: The embedded component (30) comprises a plurality of stacked reinforcement layers (31).

9. The test blade structure according to claim 8, characterized in that: In the stacking direction of the multiple layers of reinforcement layers (31), the projection areas of the multiple layers of reinforcement layers (31) are arranged to gradually increase.

10. The test blade structure according to claim 8, characterized in that: In the stacking direction of the multiple reinforcement layers (31), the thickness of each reinforcement layer (31) is consistent.

Images