Test vane structure with adjustable stiffness

Abstract

The present application provides a kind of rigidity adjustable test blade structure, including blade shell, blade shell has hollow area and entity area, and entity area is located at the outer circumferential side of hollow area;Wherein, the junction of hollow area and entity area is provided with multiple hollow shells, multiple hollow shells are arranged at intervals;Test blade structure further includes multiple embedded components, at least one embedded component in multiple embedded components is selectively filled into at least one hollow shell in multiple hollow shells according to the rigidity variation required by test blade structure, so that blade shell and embedded component are detachably connected.The present application solves the problem that the rigidity of the blade in the prior art is fixed, when comparing the aeroelastic performance of blades with different structural characteristics, blades with different rigidity need to be processed for testing, which increases the processing cycle and processing cost, and is not conducive to the economic comparison of aeroelastic performance test of blades with different rigidity.

Description

Technical Field

[0001] This invention relates to the field of wind power blade technology, and more specifically, to a test blade structure with adjustable stiffness. Background Technology

[0002] With the rapid development of the wind power industry, the demand for large and lightweight blades is increasing daily. Designing wind turbine blades that meet the requirements of large scale and lightweight design while offering superior performance has become a crucial research topic in the wind power field. The increasing flexibility of existing large blades significantly impacts their load and performance, and simulation tools introduce growing errors, necessitating experimental understanding of their aeroelastic response characteristics. However, full-scale experiments on large wind turbine blades are prohibitively expensive. To reduce experimental costs while ensuring blade design reliability, scaled-down blade design, manufacturing, and testing are required.

[0003] To compare the aeroelastic properties of blades with different structural features, it is necessary to process blades with different stiffnesses for testing. However, because these blades are small in size and require high precision in ply placement and processing, processing different blades may lead to 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 testing and comparison of blades with different stiffnesses. Summary of the Invention

[0004] The main objective of this invention is to provide a test blade structure with adjustable stiffness to solve the problem that in the prior art, when comparing the aeroelastic performance of blades with different structural features, it is necessary to process blades with different stiffnesses for testing. However, because such blades have small processing dimensions and require high precision in ply placement and processing, processing different blades may lead to 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 testing and comparison of blades with different stiffnesses.

[0005] To achieve the above objectives, the present invention provides a stiffness-adjustable test blade structure, including a blade shell having a hollow region and a solid region, with the solid region located on the outer periphery of the hollow region; wherein, a plurality of hollow shells are provided at the connection between the hollow region and the solid region, and the plurality of hollow shells are spaced apart; the test blade structure also includes a plurality of embedded components, at least one of the embedded components being selectively filled into at least one of the hollow shells according to the stiffness change required by the test blade structure, so that the blade shell and the embedded component are detachably connected.

[0006] In one exemplary embodiment, the cross-sectional outline of the hollow shell is at least one of square, circular, and elliptical.

[0007] In one exemplary embodiment, the blade housing and multiple hollow housings are integrally formed.

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

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

[0010] In one exemplary embodiment, the cross-sectional areas of the hollow shells located at least within the second region are consistent.

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

[0012] In one exemplary embodiment, the embedded component includes multiple stacked enhancement layers.

[0013] In one exemplary embodiment, the projected area of ​​the multiple reinforcement layers is gradually increased in the stacking direction of the multiple reinforcement layers.

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

[0015] The present invention provides a test blade structure with adjustable stiffness, including a blade shell having a hollow region and a solid region, with the solid region located on the outer periphery of the hollow region; wherein, a plurality of hollow shells are provided at the connection between the hollow region and the solid region, and the plurality of hollow shells are spaced apart; the test blade structure also includes a plurality of embedded components, at least one of the embedded components being selectively filled into at least one of the hollow shells according to the stiffness change required by the test blade structure, so that the blade shell and the embedded component are detachably connected.

[0016] By setting multiple hollow shells at the connection between the hollow region and the solid region, and selectively filling at least one of the multiple embedded components into at least one of the hollow shells according to the stiffness change required by the test blade structure, the blade shell and the embedded components can be detachably connected. This also facilitates the change of stiffness of the test blade structure by filling the hollow shells with embedded components at different locations. Consequently, when conducting aeroelastic performance comparison tests on test blade structures with different structural features, it is only necessary to fill the hollow shells with embedded components at different locations to change the stiffness of the test blade structure, thereby ensuring the economy of aeroelastic performance comparison tests of test blade structures with different stiffnesses. Attached Figure Description

[0017] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the 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 It shows Figure 1 The diagram shows the internal structure of the test blade structure, including the first region, the second region, and the third region.

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

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

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

[0023] 20. Hollow shell;

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

[0025] 40. Web. Detailed Implementation

[0026] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0027] To address the issue that existing blades have a fixed stiffness, comparing the aeroelastic performance of blades with different structural features requires fabricating blades with varying stiffnesses. However, because these blades are small in size and require high precision in ply placement and fabrication, fabricating different blades can lead to changes in many structural performance parameters, which is detrimental to performance comparison. This also increases the fabrication cycle and cost, hindering the aeroelastic performance testing and comparison of blades with different stiffnesses. Therefore, this 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, which has a hollow region 11 and a solid region 12, with the solid region 12 located on the outer periphery of the hollow region 11. Multiple hollow shells 20 are provided at the connection between the hollow region 11 and the solid region 12, and these hollow shells 20 are spaced apart. The test blade structure also includes multiple embedded components 30, at least one of which is selectively filled into at least one of the hollow shells 20 according to the stiffness variation required by the test blade structure, so that the blade shell 10 and the embedded component 30 are detachably connected.

[0029] By setting multiple hollow shells 20 at the connection between the hollow region 11 and the solid region 12, and selectively filling at least one of the multiple embedded components 30 into at least one of the multiple hollow shells 20 according to the stiffness change required by the test blade structure, the blade shell 10 and the embedded component 30 can be detachably connected. At the same time, it is also beneficial to change the stiffness of the test blade structure by filling the hollow shells 20 at different positions with embedded components 30. Therefore, when conducting aeroelastic performance comparison tests on test blade structures with different structural features, it is only necessary to fill the hollow shells 20 at different positions with embedded components 30 to change the stiffness of the test blade structure, thereby ensuring the economy of aeroelastic performance comparison tests of test blade structures with different stiffnesses.

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

[0031] Preferably, the cross-sectional outline of the hollow shell 20 is square. This ensures ease of fabrication for the test blade structure.

[0032] It should be noted that in this application, the blade shell 10 and the multiple hollow shells 20 are integrally formed. This ensures the ease of processing and manufacturing the test blade structure, and helps to reduce the processing and manufacturing steps and costs of the test blade structure.

[0033] like Figure 2 As shown, the outline formed by the connection between the hollow region 11 and the solid region 12 includes, in sequence, a first region 13, a second region 14, and a third region 15 in the direction from the head to the tail of the blade shell 10. The test blade structure also includes a web 40, with at least one web 40 supporting the two opposing hollow shells 20 located within the second region 14. Thus, the first region 13, the second region 14, and the third region 15 are separated by dashed lines in the figure for clarity. Because the distance between the two opposing hollow shells 20 in the second region 14 is relatively long, the web 40 effectively supports the two opposing hollow shells 20.

[0034] like Figure 2 As shown, there are multiple web plates 40, and at least two of the web plates 40 are used to connect two oppositely arranged hollow shells 20 within the second region 14. Furthermore, in the direction from the first region 13 to the third region 15, the thickness of the web plate 40 closer to the first region 13 is not less than the thickness of the web plate 40 closer to the third region 15. Thus, Figure 2 The two webs 40 have different thicknesses, with the web 40 closer to the first region 13 having a greater thickness than the web 40 closer to the third region 15, ensuring that the test blade structure has sufficient stiffness.

[0035] It should be noted that, in this application, considering the large space within the second region 14, and to ensure the accuracy and reliability of the stiffness adjustment of the test blade structure, preferably, as follows: Figure 1 and Figure 2 As shown, the cross-sectional area of ​​the hollow shell 20 located at least in the second region 14 is consistent.

[0036] like Figure 1 and Figure 2As shown, the cross-sectional length of the hollow shell 20 located in the first region 13 is not less than the cross-sectional length of the hollow shell 20 located in the second region 14; and / or, the cross-sectional length of the hollow shell 20 located in the third region 15 is not less than the cross-sectional length of the hollow shell 20 located in the second region 14. This ensures that the outline of the cross-section of each hollow shell 20 can be adapted to the outer outline of the blade shell 10 as closely as possible, that is, the conformability of the outline of the cross-section of each hollow shell 20 is good.

[0037] like Figure 3 As shown, the embedded component 30 includes multiple stacked reinforcement layers 31. In this way, by configuring the embedded component 30 with a structure including multiple stacked reinforcement layers 31, the reliability of the embedded component 30 in responding to changes in the stiffness of the test blade structure is ensured.

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

[0039] It should be noted that in this application, the thickness of each reinforcement layer 31 is the same in the stacking direction of the multilayer reinforcement layers 31.

[0040] It should be noted that in this application, the outline formed by the connection between the hollow region 11 and the solid region 12 is the inner shell of the test blade structure. The inner shell mainly plays a supporting role. When it is necessary to adjust the stiffness of the test blade structure, the embedded component 30 can be filled into the two oppositely arranged hollow shells 20 located on both sides of the same web 40 in the second region 14. The remaining hollow shells 20 are not filled. When the stiffness of the test blade structure is insufficient, it is possible to continue to fill the two oppositely arranged hollow shells 20 on both sides of the other web 40 in the second region 14 with the embedded component 30, thereby further improving the overall stiffness of the test blade structure.

[0041] Of course, when it is necessary to increase the stiffness of the test blade structure to increase EI0, ​​the formula EI0=E×S×(h / 2+H) can be used. 2 Quantitative control is achieved by using specific parameters such as 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. These parameters are related to specific formulas, thereby enabling quantitative control of the hollow shell 20 that needs to be filled in the test blade structure.

[0042] The present invention provides a test blade structure with adjustable stiffness, including a blade shell 10, which has a hollow region 11 and a solid region 12, with the solid region 12 located on the outer periphery of the hollow region 11. Multiple hollow shells 20 are provided at the connection between the hollow region 11 and the solid region 12, and the multiple hollow shells 20 are spaced apart. The test blade structure also includes multiple embedded components 30, at least one of which is selectively filled into at least one of the multiple hollow shells 20 according to the stiffness change required by the test blade structure, so that the blade shell 10 and the embedded component 30 are detachably connected.

[0043] By setting multiple hollow shells 20 at the connection between the hollow region 11 and the solid region 12, and selectively filling at least one of the multiple embedded components 30 into at least one of the multiple hollow shells 20 according to the stiffness change required by the test blade structure, the blade shell 10 and the embedded component 30 can be detachably connected. At the same time, it is also beneficial to change the stiffness of the test blade structure by filling the hollow shells 20 at different positions with embedded components 30. Therefore, when conducting aeroelastic performance comparison tests on test blade structures with different structural features, it is only necessary to fill the hollow shells 20 at different positions with embedded components 30 to change the stiffness of the test blade structure, thereby ensuring the economy of aeroelastic performance comparison tests of test blade structures with different stiffnesses.

[0044] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0045] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

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

[0047] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

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

[0049] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A test blade structure with adjustable stiffness, characterized in that, include: The blade shell (10) has a hollow region (11) and a solid region (12), and the solid region (12) is located on the outer periphery of the hollow region (11); Among them, a plurality of hollow shells (20) are provided at the connection between the hollow region (11) and the solid region (12), and the plurality of hollow shells (20) are spaced apart; The test blade structure also includes: Multiple embedded components (30), at least one of the multiple embedded components (30) selectively fills into at least one of the multiple hollow shells (20) according to the stiffness variation required by the test blade structure, so that the blade shell (10) is detachably connected to the embedded component (30); The outline formed at the junction of the hollow region (11) and the solid region (12) includes, in sequence, a first region (13), a second region (14), and a third region (15) in the direction from the head to the tail of the blade shell (10). The cross-sectional length of the hollow shell (20) located in the first region (13) is not less than the cross-sectional length of the hollow shell (20) located in the second region (14); and / or, The cross-sectional length of the hollow shell (20) located in the third region (15) is not less than the cross-sectional length of the hollow shell (20) located in the second region (14).

2. The test blade structure according to claim 1, characterized in that, The outline of the cross-section of the hollow shell (20) is at least one of square, circular, or 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 test blade structure also includes a web (40), at least one of the webs (40) is supported between at least two oppositely disposed hollow shells (20) located in the second region (14).

5. The test blade structure according to claim 4, characterized in that, There are multiple web plates (40), at least two of which are used to connect two oppositely 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 plate (40) near the first region (13) is not less than the thickness of the web plate (40) near the third region (15).

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

7. The test blade structure according to any one of claims 1 to 6, characterized in that, The embedded component (30) includes multiple stacked reinforcement layers (31).

8. The test blade structure according to claim 7, characterized in that, In the stacking direction of the multiple reinforcement layers (31), the projected area of ​​the multiple reinforcement layers (31) is gradually increased.

9. The test blade structure according to claim 7, characterized in that, In the stacking direction of the multiple reinforcing layers (31), the thickness of each reinforcing layer (31) is the same.

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