Blade cross-section bending stiffness optimization method and device, electronic equipment and storage medium

Abstract

The present disclosure provides a kind of blade section bending stiffness optimization method and device, electronic equipment and storage medium, it is related to blade structure design technical field, by establishing the design architecture of basic reinforcement layer, main reinforcement layer and auxiliary reinforcement layer cooperation, first in first preset position setting main reinforcement layer and iteration adjustment its geometric parameter, after main reinforcement layer reaches process limit, again in second preset position, add auxiliary reinforcement layer, and fixed main reinforcement layer parameter iteration optimization auxiliary reinforcement layer geometric parameter, formed the systematic design system of multiple reinforcement layer, multiple preset position, geometric parameter iteration adjustment, therefore, it can solve the problem that the stiffness direction imbalance caused by lacking multidimensional parameter collaborative adjustment system in prior art, only using single reinforcement strategy and not setting reinforcement layer position reasonably, difficult to meet preset tolerance, material redundancy and high risk of structural failure.

Description

Technical Field

[0001] This disclosure relates to the field of blade structure design technology, and in particular to a method and apparatus for optimizing the bending stiffness of a blade cross section, electronic equipment, and storage medium. Background Technology

[0002] As the core load-bearing component of wind power generation, the design of the bending stiffness of the wind turbine blade directly affects the aerodynamic performance and structural reliability of the unit. Existing technology is based on biaxial fiberglass cloth and has constructed a layup system that includes basic layup molding, local reinforcement, and stiffness verification. However, as offshore wind power develops towards larger blade sizes, traditional design faces the bottleneck of synergistic optimization of flapping stiffness and sway stiffness.

[0003] Existing methods mostly adopt a single-direction stiffness enhancement strategy, without establishing a multi-dimensional parameter adjustment system for thickness, width, position and material. They often achieve single-point optimization by increasing the overall ply thickness or replacing high-modulus materials, which can easily lead to a decrease in stiffness in another direction and make it difficult to meet quantitative standards. At the same time, there is a lack of systematic research on the position of the beam cap, which makes the blades prone to coupled vibration under complex wind conditions, posing a risk of structural failure and restricting the performance improvement of large-size blades. Summary of the Invention

[0004] This disclosure provides a method and apparatus for optimizing the bending stiffness of a blade cross section, as well as electronic equipment and a storage medium. Its main objective is to at least partially solve one of the technical problems in the related art.

[0005] According to a first aspect of this disclosure, a method for optimizing the bending stiffness of a blade section is provided, comprising: Establish a basic reinforcement layer for the blade cross section; Based on the structural analysis algorithm, the initial bending stiffness corresponding to the basic reinforcement layer is obtained and compared with the target bending stiffness. When the initial bending stiffness does not reach the target bending stiffness, a main reinforcing layer is provided at the first preset position of the blade section; At least one geometric parameter of the main reinforcing layer is iteratively adjusted, and the bending stiffness of the current blade section is recalculated after each adjustment until the deviation between the bending stiffness of the current blade section and the target bending stiffness meets the preset tolerance. If the bending stiffness of the current blade section still does not meet the preset tolerance after the geometric parameters of the main reinforcing layer reach its process limit, at least one auxiliary reinforcing layer is added at a second preset position different from the first preset position. With the geometric parameters of the main reinforcing layer fixed, the geometric parameters of the at least one auxiliary reinforcing layer are iteratively adjusted to continue to make the bending stiffness of the current blade section approach the target bending stiffness.

[0006] Optionally, the basic reinforcing layer for establishing the blade cross-section includes: A bidirectional fiber-reinforced composite material is used, laid along the chord length direction of the blade cross section from the leading edge to the trailing edge of the blade to form a closed shell structure.

[0007] Optionally, obtaining the initial bending stiffness corresponding to the base reinforcement layer based on the structural analysis algorithm includes: The bending stiffness components of the blade cross section in the flapping direction and the oscillation direction are calculated and obtained respectively.

[0008] Optionally, the iterative adjustment of at least one geometric parameter of the main enhancement layer includes: The thickness of the main reinforcing layer is adjusted incrementally by a preset thickness increment; Once the laying thickness reaches the limit thickness of a single process, the laying width of the main reinforcing layer is adjusted incrementally with a preset width increment.

[0009] Optionally, after adding at least one auxiliary enhancement layer, the method further includes: According to a preset priority order, the geometric parameters of each auxiliary reinforcement layer are iteratively adjusted in sequence. Among them, the reinforcement layer closer to the leading edge of the blade is given priority to enter the parameter adjustment process over the reinforcement layer farther from the leading edge of the blade.

[0010] Optional, also includes: If the bending stiffness of the current blade section still does not meet the preset tolerance after adjusting the geometric parameters of all reinforcing layers to their process limits, then the material upgrade step is executed. The material upgrading steps include: Replace the material used in at least one reinforcing layer with a reinforcing material having a higher elastic modulus; After the material replacement, the process restarts from the step of iteratively adjusting the geometric parameters of the main reinforcing layer.

[0011] According to a second aspect of this disclosure, a blade section bending stiffness optimization device is provided, comprising: Establish a unit to create the basic reinforcement layer for the blade section; The comparison unit is used to obtain the initial bending stiffness corresponding to the basic reinforcement layer based on the structural analysis algorithm, and compare it with the target bending stiffness. The setting unit is used to set a main reinforcing layer at a first preset position on the blade section when the initial bending stiffness does not reach the target bending stiffness. The first adjustment unit is used to iteratively adjust at least one geometric parameter of the main reinforcement layer, and recalculate the bending stiffness of the current blade section after each adjustment until the deviation between the bending stiffness of the current blade section and the target bending stiffness meets the preset tolerance. An additional unit is provided to add at least one auxiliary reinforcement layer at a second preset position different from the first preset position if the bending stiffness of the current blade section still does not meet the preset tolerance after the geometric parameters of the main reinforcement layer reach its process limit. The second adjustment unit is used to iteratively adjust the geometric parameters of the at least one auxiliary reinforcement layer while keeping the geometric parameters of the main reinforcement layer fixed, so as to continue to make the bending stiffness of the current blade section approach the target bending stiffness.

[0012] Optionally, the creation unit is also used for: A bidirectional fiber-reinforced composite material is used, laid along the chord length direction of the blade cross section from the leading edge to the trailing edge of the blade to form a closed shell structure.

[0013] Optionally, the comparison unit is also used for: The bending stiffness components of the blade cross section in the flapping direction and the oscillation direction are calculated and obtained respectively.

[0014] Optionally, the first adjustment unit is also used for: The thickness of the main reinforcing layer is adjusted incrementally by a preset thickness increment; Once the laying thickness reaches the limit thickness of a single process, the laying width of the main reinforcing layer is adjusted incrementally with a preset width increment.

[0015] Optionally, after adding at least one auxiliary enhancement layer, the method further includes: The third adjustment unit is used to iteratively adjust the geometric parameters of each of the auxiliary reinforcement layers in a preset priority order, wherein the reinforcement layer closer to the leading edge of the blade enters the parameter adjustment process first, before the reinforcement layer farther from the leading edge of the blade.

[0016] Optional, also includes: An execution unit is configured to perform a material upgrade step if the bending stiffness of the current blade section still does not meet the preset tolerance after adjusting the geometric parameters of all reinforcing layers to their process limits. The material upgrading steps include: Replace the material used in at least one reinforcing layer with a reinforcing material having a higher elastic modulus; After the material replacement, the process restarts from the step of iteratively adjusting the geometric parameters of the main reinforcing layer.

[0017] According to a third aspect of this disclosure, an electronic device is provided, comprising: At least one processor; and A memory communicatively connected to the at least one processor; wherein, The memory stores instructions that can be executed by the at least one processor to enable the at least one processor to perform the method described in the first aspect above.

[0018] According to a fourth aspect of this disclosure, a non-transitory computer-readable storage medium is provided storing computer instructions, wherein the computer instructions are configured to cause the computer to perform the method described in the first aspect above.

[0019] According to a fifth aspect of this disclosure, a computer program product is provided, comprising a computer program that, when executed by a processor, implements the method described in the first aspect above.

[0020] The blade section bending stiffness optimization method, apparatus, electronic equipment, and storage medium disclosed herein establish a design architecture that coordinates a basic reinforcement layer, a main reinforcement layer, and an auxiliary reinforcement layer. First, a main reinforcement layer is set at a first preset position, and its geometric parameters are iteratively adjusted. Once the main reinforcement layer reaches its process limit, an auxiliary reinforcement layer is added at a second preset position. The geometric parameters of the auxiliary reinforcement layer are iteratively optimized while maintaining the parameters of the main reinforcement layer. This forms a systematic design system with multiple reinforcement layers, multiple preset positions, and iterative adjustment of geometric parameters. Therefore, it can solve the problems in existing technologies caused by the lack of a multi-dimensional parameter coordinated adjustment system, the use of only a single reinforcement strategy, and the improper setting of reinforcement layer positions, leading to stiffness orientation imbalance, difficulty in meeting preset tolerances, material redundancy, and high risk of structural failure. It achieves the technical effect of simultaneously meeting the flapping stiffness and yaw stiffness requirements of the blade section, making the bending stiffness accurately approach the target stiffness and conforming to preset tolerances, reducing material redundancy, and improving the reliability of the blade structure.

[0021] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of this disclosure, nor is it intended to limit the scope of this disclosure. Other features of this disclosure will become readily apparent from the following description. Attached Figure Description

[0022] The accompanying drawings are provided to better understand this solution and do not constitute a limitation of this disclosure. Wherein: Figure 1 A flowchart illustrating a method for optimizing the bending stiffness of a blade section provided in this embodiment of the present disclosure; Figure 2 This is a schematic diagram of a blade section bending stiffness optimization device provided in an embodiment of the present disclosure; Figure 3 A schematic block diagram of an example electronic device provided for embodiments of this disclosure. Detailed Implementation

[0023] The exemplary embodiments of this disclosure are described below with reference to the accompanying drawings, including various details of the embodiments to aid understanding, and should be considered merely exemplary. Therefore, those skilled in the art will recognize that various changes and modifications can be made to the embodiments described herein without departing from the scope and spirit of this disclosure. Similarly, for clarity and brevity, descriptions of well-known functions and structures are omitted in the following description.

[0024] The following description, with reference to the accompanying drawings, outlines a method and apparatus for optimizing the bending stiffness of a blade section, an electronic device, and a storage medium according to embodiments of the present disclosure.

[0025] Figure 1 This is a flowchart illustrating a method for optimizing the bending stiffness of a blade section provided in an embodiment of this disclosure.

[0026] like Figure 1 As shown, the method includes the following steps: Step 101: Establish the basic reinforcement layer for the blade cross section.

[0027] In the embodiments of this disclosure, to achieve precise control of the blade cross-sectional bending stiffness, a basic reinforcement layer (i.e., a ply structure used to ensure the basic shape and initial structural performance of the blade cross-section) is first established. This basic reinforcement layer is formed by selecting a suitable shell material and using a ply process based on the target bending stiffness (EId) and preset geometric shape of the blade. Its core function is to provide the basic structural shape and initial load-bearing capacity for the blade cross-section, laying a stable foundation for subsequent stiffness optimization and adjustment. As one implementation method, biaxial fiberglass cloth can be used as the shell material, ply-laid from the leading edge to the trailing edge, with one layer on each of the inner and outer sides of the blade cross-section to meet the requirements of maintaining the basic shape.

[0028] The establishment of this basic reinforcement layer provides a stable benchmark for the subsequent precise optimization of bending stiffness. It not only ensures the basic structural integrity of the blade section, but also provides a quantifiable basis for the initial stiffness analysis. This provides a reliable premise for the setting of subsequent reinforcement layers and parameter adjustment, helping the bending stiffness of the blade section to accurately approach the target value.

[0029] Step 102: Based on the structural analysis algorithm, obtain the initial bending stiffness corresponding to the basic reinforcement layer and compare it with the target bending stiffness.

[0030] In the embodiments of this disclosure, to clarify the direction and benchmark for subsequent stiffness optimization, a stiffness characteristic analysis is performed on the established foundation reinforcement layer based on a preset structural analysis algorithm (i.e., a professional analysis algorithm for calculating the bending stiffness of ply structures). This yields the initial bending stiffness (EIO) corresponding to the foundation reinforcement layer, which is then quantitatively compared with a preset target bending stiffness (EId). The comparison results determine whether the stiffness performance of the foundation reinforcement layer meets the design requirements, providing a core basis for deciding whether to add a reinforcement layer and how to adjust its parameters. As one implementation method, cross-sectional bending stiffness analysis software or programs can be used to execute the above structural analysis algorithm, directly calculating the initial bending stiffness of the foundation reinforcement layer. The comparison process is then completed by calculating the deviation between the initial and target bending stiffness.

[0031] The structural analysis algorithm enabled the quantitative analysis and comparison of stiffness, providing a precise quantitative basis for the subsequent setting of reinforcement layers and parameter adjustment. This avoided blind optimization operations, ensured the pertinence and scientific nature of the stiffness optimization process, and laid a data foundation for ultimately achieving the target requirement of bending stiffness.

[0032] Step 103: When the initial bending stiffness does not reach the target bending stiffness, a main reinforcing layer is set at the first preset position of the blade section.

[0033] In the embodiments of this disclosure, when the initial bending stiffness of the basic reinforcement layer is confirmed by structural analysis algorithms to not meet the preset target bending stiffness, a main reinforcement layer (i.e., a core reinforcement ply structure for directionally improving the bending stiffness of the blade section) is set at a first preset position on the blade section based on the stiffness enhancement requirements, geometric characteristics, and stress distribution law of the blade section. The first preset position is a reasonable layout position determined after stiffness requirement matching, capable of efficiently improving bending stiffness. The material selection of the main reinforcement layer must be adapted to the structural bearing requirements and stiffness enhancement target of the blade. The directional setting of this main reinforcement layer achieves targeted enhancement of the bending stiffness of the blade section, providing core support for subsequent precise stiffness optimization. As one implementation method, the first preset position can be selected at a specific proportional distance from the leading edge of the blade section in the chord direction, and the main reinforcement layer can be constructed using a unidirectional reinforcement material.

[0034] By strategically setting the main reinforcement layer at the first preset position, the stiffness deficiency can be directly addressed for directional reinforcement, quickly narrowing the gap between the initial bending stiffness and the target bending stiffness. Furthermore, the adaptability design of the preset position ensures the directionality and effectiveness of the stiffness reinforcement, avoiding stiffness imbalance caused by blind reinforcement, and laying a stable foundation for further parameter optimization.

[0035] Step 104: Iteratively adjust at least one geometric parameter of the main reinforcing layer, and recalculate the bending stiffness of the current blade section after each adjustment, until the deviation between the bending stiffness of the current blade section and the target bending stiffness meets the preset tolerance.

[0036] In the embodiments of this disclosure, to ensure that the bending stiffness of the blade section accurately meets the target requirements, at least one geometric parameter of the main reinforcing layer (i.e., structural dimensional parameters affecting the stiffness contribution of the main reinforcing layer, such as thickness and width) needs to be iteratively adjusted. After each adjustment, the overall bending stiffness of the current blade section is recalculated using a preset structural analysis algorithm, and the deviation of this calculation result is compared with the target bending stiffness. This adjustment and calculation process is continuously repeated until the deviation between the current bending stiffness and the target bending stiffness meets the preset tolerance (i.e., the pre-set allowable fluctuation range of stiffness). As one implementation method, the thickness parameter of the main reinforcing layer can be adjusted first, followed by the width parameter. The preset tolerance can be set so that the stiffness deviation accounts for no more than 0.5% of the target bending stiffness. After each adjustment, the current stiffness is calculated and verified using section bending stiffness analysis software.

[0037] By iteratively adjusting the geometric parameters of the main reinforcing layer and verifying the stiffness in real time, the stiffness contribution of the main reinforcing layer can be precisely controlled, so that the bending stiffness of the blade section gradually approaches the target value and meets the preset accuracy requirements. This avoids the problem of excessive stiffness deviation caused by adjusting a single parameter at once, improves the accuracy and controllability of stiffness design, and reduces unnecessary material redundancy.

[0038] Step 105: If the bending stiffness of the current blade section still does not meet the preset tolerance after the geometric parameters of the main reinforcing layer reach their process limits, then at least one auxiliary reinforcing layer is added at a second preset position different from the first preset position.

[0039] In the embodiments of this disclosure, when the geometric parameters of the main reinforcing layer have reached their process limits (i.e., the extreme range of geometric parameters allowed by material properties and processing conditions), and the bending stiffness of the current blade section still does not meet the preset tolerance, at least one auxiliary reinforcing layer (i.e., a ply structure for supplementing and improving stiffness) is added at a second preset position that does not overlap with the first preset position to further superimpose the stiffness contribution and continuously advance the bending stiffness toward the target value. The selection of the second preset position needs to be adapted to the stress distribution and stiffness improvement requirements of the blade section, and the material selection of the auxiliary reinforcing layer can be consistent with or adapted to the basic reinforcing layer or the main reinforcing layer. As one implementation, the first preset position can be a position 30% of the chordal distance from the leading edge of the blade section, and the second preset position can be a position 60% of the chordal distance from the leading edge. The auxiliary reinforcing layer can use the same unidirectional fabric material as the main reinforcing layer. If the requirements are still not met after adding one auxiliary reinforcing layer, more auxiliary reinforcing layers can be added along the trailing edge direction of the blade.

[0040] By adding an auxiliary reinforcement layer at the second preset position, the technological limitations of a single main reinforcement layer are effectively overcome. The stiffness can be continuously improved without compromising the stability of the existing structure, avoiding the problem that the target stiffness cannot be achieved due to the limitation of a single reinforcement structure. At the same time, the multi-position reinforcement design ensures the directionality and balance of stiffness improvement, significantly improving the flexibility and applicability of blade section stiffness design.

[0041] Step 106: Under the condition of fixing the geometric parameters of the main reinforcing layer, the geometric parameters of the at least one auxiliary reinforcing layer are iteratively adjusted to continue to make the bending stiffness of the current blade section approach the target bending stiffness.

[0042] In the embodiments of this disclosure, to continuously push the bending stiffness towards the target value while ensuring the existing structural stability of the blade cross-section, under the condition of fixing all geometric parameters of the main reinforcing layer (i.e., the structural dimensions and layout-related parameters of the main reinforcing layer), at least one geometric parameter of the at least one auxiliary reinforcing layer is iteratively optimized and adjusted. After each adjustment, the overall bending stiffness of the current blade cross-section is recalculated using a preset structural analysis algorithm, and the adjustment direction is dynamically optimized based on the deviation between the calculation result and the target bending stiffness. The above adjustment and stiffness verification process is repeated until the current bending stiffness meets the preset tolerance or achieves the design target. As one implementation method, the laying position, thickness, and width of the main reinforcing layer can be fixed, and the thickness parameter of the auxiliary reinforcing layer can be iteratively adjusted first. After the thickness reaches the process limit, the width parameter is adjusted. If the requirements are still not met after adjusting a single auxiliary reinforcing layer, a new auxiliary reinforcing layer can be added along the trailing edge direction of the blade and the iteration can continue according to the same logic.

[0043] Fixing the parameters of the main reinforcement layer can avoid interference with the existing stable structure by subsequent adjustments, while iterative optimization of the auxiliary reinforcement layer can accurately fill the stiffness gap and effectively avoid the problem of stiffness imbalance between multiple reinforcement layers. This not only improves the accuracy and controllability of bending stiffness design, but also expands the adjustable space of stiffness enhancement, ensuring that the target bending stiffness is achieved efficiently and stably.

[0044] The blade section bending stiffness optimization method disclosed herein establishes a design architecture in which a basic reinforcement layer, a main reinforcement layer, and an auxiliary reinforcement layer work together. First, a main reinforcement layer is set at a first preset position and its geometric parameters are iteratively adjusted. Once the main reinforcement layer reaches its process limit, an auxiliary reinforcement layer is added at a second preset position. The geometric parameters of the auxiliary reinforcement layer are iteratively optimized while the parameters of the main reinforcement layer are fixed. This forms a systematic design system with multiple reinforcement layers, multiple preset positions, and iterative adjustment of geometric parameters. Therefore, it can solve the problems in existing technologies caused by the lack of a multi-dimensional parameter collaborative adjustment system, the use of only a single reinforcement strategy, and the improper setting of reinforcement layer positions, which lead to stiffness orientation imbalance, difficulty in meeting preset tolerances, material redundancy, and high risk of structural failure. This method achieves the technical effect of simultaneously meeting the flapping stiffness and yaw stiffness requirements of the blade section, making the bending stiffness accurately approach the target stiffness and conforming to preset tolerances, reducing material redundancy, and improving the reliability of the blade structure.

[0045] As a specific embodiment of this disclosure, based on the basic scheme, the basic reinforcement layer for establishing the blade cross section is further defined as follows: a bidirectional fiber reinforced composite material is used and laid along the chord length direction of the blade cross section from the leading edge to the trailing edge of the blade to form a closed shell structure.

[0046] Specifically, when constructing the basic reinforcement layer of the blade cross-section, a biaxial fiber-reinforced composite material (such as biaxial fiberglass cloth, a commonly used shell material) is selected. This material possesses the mechanical properties and molding characteristics suitable for the load-bearing requirements of the blade's foundation structure. The laying process is strictly carried out along the chord length direction of the blade cross-section, starting from the leading edge of the blade and extending continuously to the trailing edge to complete the laying. A layer is laid on both the inner and outer sides of the blade cross-section, and the two layers work together to form a closed shell structure. This closed shell reliably ensures the basic geometric shape of the blade cross-section while providing initial structural support and basic load-bearing capacity, preventing structural deformation during subsequent reinforcement layer laying and stiffness adjustment.

[0047] By employing bidirectional fiber-reinforced composite materials to form a closed shell structure, the excellent structural stability and molding adaptability of this type of material are utilized. Furthermore, the closed laying of inner and outer layers ensures the regularity of the blade cross-section foundation shape, providing a stable benchmark for the precise positioning and laying of the subsequent main and auxiliary reinforcement layers. At the same time, it endows the foundation reinforcement layer with reliable initial load-bearing capacity, laying a solid structural foundation for the subsequent optimization and adjustment of bending stiffness.

[0048] As a specific embodiment of this disclosure, based on the basic scheme, the method of obtaining the initial bending stiffness corresponding to the basic reinforcement layer based on the structural analysis algorithm is further defined, including: calculating and obtaining the bending stiffness components of the blade section in the flapping direction and the oscillation direction respectively.

[0049] Specifically, when obtaining the initial bending stiffness corresponding to the base reinforcement layer based on the structural analysis algorithm, the flapping direction (i.e., the bending direction along the blade chord) and yaw direction (i.e., the bending direction along the blade spanwise) of the blade section are first identified, as these are the core bending directions of the blade section under stress. A suitable section bending stiffness analysis software (such as Precomp) is used as the execution carrier for the structural analysis algorithm. The material property parameters of the base reinforcement layer (such as the modulus and density of the biaxial fiber reinforced composite material), the layup structure parameters (including the inner and outer layer layup methods and the coverage along the chord length), and the geometric shape data of the blade section are input. Through the software's built-in structural mechanics analysis logic, the bending stiffness in the two directions is independently quantified and calculated, accurately separating and outputting the flapping direction bending stiffness component and the yaw direction bending stiffness component. These two components together constitute the initial bending stiffness corresponding to the base reinforcement layer, providing dual data support—both directional and overall—for subsequent comparison with the target bending stiffness.

[0050] By calculating the bending stiffness components in the two core directions separately, the stiffness status of the base reinforcement layer in different stress directions can be accurately grasped, avoiding the problem of fuzzy directional characteristics caused by overall stiffness calculation. This provides accurate data basis for subsequent targeted optimization of stiffness in each direction and achieving synergistic satisfaction of swing stiffness and oscillation stiffness, effectively avoiding the risk of performance imbalance in another direction caused by stiffness optimization in a single direction.

[0051] As a specific embodiment of this disclosure, based on the basic scheme, the iterative adjustment of at least one geometric parameter of the main reinforcing layer is further defined, including: increasing the laying thickness of the main reinforcing layer by a preset thickness increment; and when the laying thickness reaches the single process limit thickness, increasing the laying width of the main reinforcing layer by a preset width increment.

[0052] Specifically, when iteratively adjusting the geometric parameters of the main reinforcement layer, the main reinforcement layer uses unidirectional fabric as the laying material. First, the preset thickness increment (such as the single layer thickness of the unidirectional fabric, which is the standard lay-up thickness commonly used in the industry) and the preset width increment (such as a fixed width increment value set based on the convenience of production and processing) are determined. First, the thickness of the main reinforcing layer is gradually increased in increments of a preset thickness. After each thickness increase, the bending stiffness of the current blade section is recalculated using cross-sectional bending stiffness analysis software (such as Precomp), and the deviation from the target bending stiffness is checked to ensure it meets the preset tolerance. When the thickness of the main reinforcing layer reaches the single-process limit thickness (i.e., the maximum thickness that a unidirectional fabric layer can achieve in production), and the deviation still does not meet the preset tolerance, the maximum thickness is kept constant, and the width of the main reinforcing layer is gradually increased in increments of a preset width. The initial width is set to the standard width of the production fabric layer (e.g., 600mm). After each width adjustment, the bending stiffness is recalculated and checked until the deviation meets the preset tolerance or the width reaches the maximum allowable width in the process.

[0053] The incremental iterative adjustment method of "thickness first, then width" is adopted, which is in line with the process characteristics and stiffness contribution law of unidirectional fabric layers. Thickness adjustment can improve stiffness more directly and efficiently, while width adjustment further supplements the stiffness increment under the constraints of process limits. This ensures the orderliness and controllability of the adjustment process, and avoids material waste or process conflicts caused by blind adjustment, which significantly improves the efficiency and accuracy of main reinforcement layer stiffness optimization.

[0054] As a specific embodiment of this disclosure, based on the basic scheme, after adding at least one auxiliary reinforcement layer, it further includes: iteratively adjusting the geometric parameters of each of the auxiliary reinforcement layers in a preset priority order, wherein the reinforcement layer closer to the leading edge of the blade enters the parameter adjustment process first, before the reinforcement layer farther from the leading edge of the blade.

[0055] Specifically, after adding at least one auxiliary reinforcement layer, the geometric parameter iterative adjustment process for each auxiliary reinforcement layer is initiated sequentially according to the preset priority order of "adjusting the reinforcement layer closer to the blade leading edge first". Each auxiliary reinforcement layer uses unidirectional fabric as the laying material, and the initial width is set to the standard width of the production fabric layer (e.g., 600mm). First, the parameters of the first auxiliary reinforcement layer closest to the leading edge (whose centerline is located at 60% chord length of the blade section) are adjusted. The laying thickness is gradually increased by using the single-layer thickness of the unidirectional fabric as the preset thickness increment. After each adjustment, the current overall bending stiffness is calculated by the section bending stiffness analysis software (e.g., precomp) to verify whether the deviation from the target bending stiffness meets the preset tolerance of abs(EI-EId) / EId≤0.5%. When the thickness of the auxiliary reinforcement layer reaches the maximum processable thickness but still does not meet the tolerance requirement, the thickness is kept unchanged, and the laying width is adjusted by increasing the preset fixed width increment until both the thickness and width reach the process limit or the deviation meets the standard. Subsequently, the next auxiliary reinforcement layer (further from the leading edge) added along the trailing edge of the blade is iteratively adjusted using the same "thickness first, then width" logic, and so on, to complete the parameter optimization of all auxiliary reinforcement layers.

[0056] By adjusting the parameters of each auxiliary reinforcement layer according to the "near leading edge priority" principle, the high efficiency contribution characteristics of the reinforcement layer located closer to the leading edge to the overall stiffness of the blade are fully utilized. This avoids the problem of inefficient stiffness improvement caused by disordered adjustment. It ensures the orderliness and targeting of the adjustment process, and can continuously and accurately fill the stiffness gap without interfering with the structural stability of the main reinforcement layer and the optimized auxiliary reinforcement layer. This significantly improves the efficiency and controllability of the blade section bending stiffness approaching the target value.

[0057] As a specific embodiment of this disclosure, based on the basic scheme, the embodiment of this disclosure further includes: if the bending stiffness of the current blade section still does not meet the preset tolerance after adjusting the geometric parameters of all reinforcing layers to their process limits, then a material upgrade step is performed; the material upgrade step includes: replacing the material used in at least one reinforcing layer with a reinforcing material with a higher elastic modulus; after the material replacement, the step of iteratively adjusting the geometric parameters of the main reinforcing layer is restarted.

[0058] Specifically, when the geometric parameters (including layup thickness and width) of the main reinforcing layer and all added auxiliary reinforcing layers (i.e., each beam cap structure) have been adjusted to their respective process limits, and the current blade section bending stiffness calculated by section bending stiffness analysis software (such as precomp) still does not meet the preset tolerance of abs(EI-EId) / EId≤0.5%, the material upgrade step is initiated. During the material upgrade process, the unidirectional fabric material used in the main reinforcing layer, all auxiliary reinforcing layers, or any one or more of these reinforcing layers can be replaced with a reinforcing material with a higher elastic modulus (such as high-modulus glass fiber cloth, carbon fiber cloth, and other reinforcing composite materials adapted to the blade layup process). After the material replacement is completed, keeping the layup position of each reinforcing layer unchanged, the step of iteratively adjusting the geometric parameters of the main reinforcing layer is restarted. That is, following the logic of "first adjusting the thickness in preset thickness increments, and then adjusting the width in preset width increments after reaching the process limit", the parameter optimization of the main reinforcing layer and each auxiliary reinforcing layer is completed sequentially until the blade section bending stiffness meets the preset tolerance.

[0059] This material upgrade and process reuse design effectively breaks through the limitation of the original material's elastic modulus on stiffness improvement, avoiding the problem of not being able to achieve the target stiffness due to the geometric parameters reaching the process limit; at the same time, by reusing the verified parameter iteration adjustment process, there is no need to redesign the adjustment logic, which not only ensures the continuity and accuracy of stiffness optimization, but also significantly broadens the applicability of the technical solution, ensuring that design requirements can be achieved efficiently under different target stiffness requirements.

[0060] It should be noted that the embodiments of this disclosure may include multiple steps. For ease of description, these steps are numbered, but these numbers are not a limitation on the execution time slots or execution order between the steps; these steps can be implemented in any order, and the embodiments of this disclosure do not limit this.

[0061] Corresponding to the aforementioned method for optimizing the bending stiffness of blade cross sections, this disclosure also proposes a device for optimizing the bending stiffness of blade cross sections. Since the device embodiments of this disclosure correspond to the method embodiments described above, details not disclosed in the device embodiments can be referred to the method embodiments described above, and will not be repeated here.

[0062] Figure 2 This is a schematic diagram of a blade section bending stiffness optimization device provided in an embodiment of the present disclosure, as shown below. Figure 2 As shown, it includes: Establish unit 21, used to establish the basic reinforcement layer of the blade section; Comparison unit 22 is used to obtain the initial bending stiffness corresponding to the basic reinforcement layer based on the structural analysis algorithm, and compare it with the target bending stiffness. Setting unit 23 is used to set a main reinforcing layer at a first preset position on the blade section when the initial bending stiffness does not reach the target bending stiffness; The first adjustment unit 24 is used to iteratively adjust at least one geometric parameter of the main reinforcing layer, and recalculate the bending stiffness of the current blade section after each adjustment until the deviation between the bending stiffness of the current blade section and the target bending stiffness meets the preset tolerance. An additional unit 25 is provided to add at least one auxiliary reinforcement layer at a second preset position different from the first preset position if the bending stiffness of the current blade section still does not meet the preset tolerance after the geometric parameters of the main reinforcement layer reach its process limit. The second adjustment unit 26 is used to iteratively adjust the geometric parameters of the at least one auxiliary reinforcement layer under the condition of fixing the geometric parameters of the main reinforcement layer, so as to continue to make the bending stiffness of the current blade section approach the target bending stiffness.

[0063] The blade section bending stiffness optimization device disclosed herein establishes a design architecture in which a basic reinforcement layer, a main reinforcement layer, and an auxiliary reinforcement layer work together. First, a main reinforcement layer is set at a first preset position and its geometric parameters are iteratively adjusted. Once the main reinforcement layer reaches its process limit, an auxiliary reinforcement layer is added at a second preset position. The geometric parameters of the auxiliary reinforcement layer are iteratively optimized while the parameters of the main reinforcement layer are fixed. This forms a systematic design system with multiple reinforcement layers, multiple preset positions, and iterative adjustment of geometric parameters. Therefore, it can solve the problems in existing technologies caused by the lack of a multi-dimensional parameter collaborative adjustment system, the use of only a single reinforcement strategy, and the improper setting of reinforcement layer positions, which lead to stiffness orientation imbalance, difficulty in meeting preset tolerances, material redundancy, and high risk of structural failure. It achieves the technical effect of simultaneously meeting the flapping stiffness and teeter stiffness requirements of the blade section, making the bending stiffness accurately approach the target stiffness and conforming to preset tolerances, reducing material redundancy, and improving the reliability of the blade structure.

[0064] Furthermore, in one possible implementation of this embodiment, the establishing unit 21 is also used for: A bidirectional fiber-reinforced composite material is used, laid along the chord length direction of the blade cross section from the leading edge to the trailing edge of the blade to form a closed shell structure.

[0065] Furthermore, in one possible implementation of this embodiment, the comparison unit 22 is also used for: The bending stiffness components of the blade cross section in the flapping direction and the oscillation direction are calculated and obtained respectively.

[0066] Furthermore, in one possible implementation of this embodiment, the first adjustment unit 24 is also used for: The thickness of the main reinforcing layer is adjusted incrementally by a preset thickness increment; Once the laying thickness reaches the limit thickness of a single process, the laying width of the main reinforcing layer is adjusted incrementally with a preset width increment.

[0067] Furthermore, in one possible implementation of this embodiment, such as Figure 2 As shown, after adding at least one auxiliary reinforcement layer, it further includes: The third adjustment unit 27 is used to iteratively adjust the geometric parameters of each of the auxiliary reinforcement layers in a preset priority order, wherein the reinforcement layer closer to the leading edge of the blade enters the parameter adjustment process first, before the reinforcement layer farther from the leading edge of the blade.

[0068] Furthermore, in one possible implementation of this embodiment, such as Figure 2 As shown, it also includes: The execution unit 28 is configured to perform a material upgrade step if the bending stiffness of the current blade section still does not meet the preset tolerance after adjusting the geometric parameters of all reinforcing layers to their process limits. The material upgrading steps include: Replace the material used in at least one reinforcing layer with a reinforcing material having a higher elastic modulus; After the material replacement, the process restarts from the step of iteratively adjusting the geometric parameters of the main reinforcing layer.

[0069] It should be noted that the foregoing explanation of the method embodiments also applies to the apparatus of this embodiment, and the principle is the same, so it is not limited in this embodiment.

[0070] According to embodiments of this disclosure, this disclosure also provides an electronic device, a readable storage medium, and a computer program product.

[0071] Figure 3 A schematic block diagram of an example electronic device 300 that can be used to implement embodiments of the present disclosure is shown. The electronic device is intended to represent various forms of digital computers, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device may also represent various forms of mobile devices, such as personal digital processors, cellular phones, smartphones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely illustrative and are not intended to limit the implementation of the present disclosure described and / or claimed herein.

[0072] like Figure 3As shown, the electronic device 300 includes a computing unit 301, which can perform various appropriate actions and processes based on a computer program stored in ROM (Read-Only Memory) 302 or a computer program loaded from storage unit 308 into RAM (Random Access Memory) 303. The RAM 303 may also store various programs and data required for the operation of the electronic device 300. The computing unit 301, ROM 302, and RAM 303 are interconnected via a bus 304. An I / O (Input / Output) interface 305 is also connected to the bus 304.

[0073] Multiple components in electronic device 300 are connected to I / O interface 305, including: input unit 306, such as keyboard, mouse, etc.; output unit 307, such as various types of displays, speakers, etc.; storage unit 308, such as disk, optical disk, etc.; and communication unit 309, such as network card, modem, wireless transceiver, etc. Communication unit 309 allows electronic device 300 to exchange information / data with other devices through computer networks such as the Internet and / or various telecommunications networks.

[0074] The computing unit 301 can be a variety of general-purpose and / or special-purpose processing components with processing and computing capabilities. Some examples of the computing unit 301 include, but are not limited to, CPUs (Central Processing Units), GPUs (Graphics Processing Units), various special-purpose AI (Artificial Intelligence) computing chips, various computing units running machine learning model algorithms, DSPs (Digital Signal Processors), and any suitable processor, controller, microcontroller, etc. The computing unit 301 performs the various methods and processes described above, such as the blade section bending stiffness optimization method. For example, in some embodiments, the blade section bending stiffness optimization method can be implemented as a computer software program, which is tangibly contained in a machine-readable medium, such as storage unit 308. In some embodiments, part or all of the computer program can be loaded and / or installed on the electronic device 300 via ROM 302 and / or communication unit 309. When the computer program is loaded into RAM 303 and executed by the computing unit 301, one or more steps of the methods described above can be performed. Alternatively, in other embodiments, the computing unit 301 may be configured to perform the aforementioned blade section bending stiffness optimization method by any other suitable means (e.g., by means of firmware).

[0075] Various implementations of the systems and techniques described above herein can be implemented in digital electronic circuit systems, integrated circuit systems, FPGAs (Field Programmable Gate Arrays), ASICs (Application-Specific Integrated Circuits), ASSPs (Application-Specific Standard Products), SOCs (System-on-Chips), CPLDs (Complex Programmable Logic Devices), computer hardware, firmware, software, and / or combinations thereof. These various implementations may include implementations in one or more computer programs that can be executed and / or interpreted on a programmable system including at least one programmable processor, which may be a dedicated or general-purpose programmable processor, capable of receiving data and instructions from a storage system, at least one input device, and at least one output device, and transmitting data and instructions to the storage system, the at least one input device, and the at least one output device.

[0076] The program code used to implement the methods of this disclosure may be written in any combination of one or more programming languages. This program code may be provided to a processor or controller of a general-purpose computer, special-purpose computer, or other programmable data processing apparatus, such that when executed by the processor or controller, the program code causes the functions / operations specified in the flowcharts and / or block diagrams to be implemented. The program code may be executed entirely on a machine, partially on a machine, as a standalone software package partially on a machine and partially on a remote machine, or entirely on a remote machine or server.

[0077] In the context of this disclosure, a machine-readable medium can be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, apparatus, or device. A machine-readable medium can be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium can be, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatus, or devices, or any suitable combination of the foregoing. More specific examples of machine-readable storage media include electrical connections based on one or more wires, portable computer disks, hard disks, RAM, ROM, EPROM (Electrically Programmable Read-Only Memory) or flash memory, optical fiber, CD-ROM (Compact Disc Read-Only Memory), optical storage devices, magnetic storage devices, or any suitable combination of the foregoing.

[0078] To provide interaction with a user, the systems and techniques described herein can be implemented on a computer having: a display device for displaying information to the user (e.g., a CRT (Cathode-Ray Tube) or LCD (Liquid Crystal Display) monitor); and a keyboard and pointing device (e.g., a mouse or trackball) through which the user provides input to the computer. Other types of devices can also be used to provide interaction with the user; for example, feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form (including sound input, voice input, or tactile input).

[0079] The systems and technologies described herein can be implemented in computing systems that include backend components (e.g., as data servers), or computing systems that include middleware components (e.g., application servers), or computing systems that include frontend components (e.g., user computers with graphical user interfaces or web browsers through which users can interact with implementations of the systems and technologies described herein), or any combination of such backend, middleware, or frontend components. The components of the system can be interconnected via digital data communication of any form or medium (e.g., communication networks). Examples of communication networks include LANs (Local Area Networks), WANs (Wide Area Networks), the Internet, and blockchain networks.

[0080] Computer systems can include clients and servers. Clients and servers are generally geographically separated and typically interact via communication networks. The client-server relationship is created by computer programs running on the respective computers and having a client-server relationship with each other. A server can be a cloud server, also known as a cloud computing server or cloud host, a hosting product within the cloud computing service system that addresses the shortcomings of traditional physical hosts and VPS (Virtual Private Server) services, such as high management difficulty and weak business scalability. Servers can also be servers for distributed systems or servers incorporating blockchain technology.

[0081] It's important to note that artificial intelligence (AI) is the study of enabling computers to simulate certain human thought processes and intelligent behaviors (such as learning, reasoning, thinking, and planning). It encompasses both hardware and software technologies. AI hardware technologies generally include sensors, dedicated AI chips, cloud computing, distributed storage, and big data processing. AI software technologies primarily include computer vision, speech recognition, natural language processing, machine learning / deep learning, big data processing, and knowledge graph technologies.

[0082] The various numerical designations such as "first," "second," etc., used in this disclosure are merely for ease of description and are not intended to limit the scope of the embodiments of this disclosure, nor do they indicate a sequential order.

[0083] At least one of the features described in this disclosure can also be described as one or more, and multiple features can be two, three, four or more, and this disclosure does not impose any limitations. In the embodiments of this disclosure, for a technical feature, the technical features in that technical feature are distinguished by "first", "second", "third", "A", "B", "C" and "D", etc., and there is no sequential order or size order among the technical features described by "first", "second", "third", "A", "B", "C" and "D".

[0084] It should be understood that the various forms of processes shown above can be used to rearrange, add, or delete steps. For example, the steps described in this disclosure can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution disclosed in this disclosure can be achieved, and this is not limited herein.

[0085] The specific embodiments described above do not constitute a limitation on the scope of protection of this disclosure. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this disclosure should be included within the scope of protection of this disclosure.

Claims

1. A method for optimizing the bending stiffness of a blade cross section, characterized in that, include: Establish a basic reinforcement layer for the blade cross section; Based on the structural analysis algorithm, the initial bending stiffness corresponding to the basic reinforcement layer is obtained and compared with the target bending stiffness. When the initial bending stiffness does not reach the target bending stiffness, a main reinforcing layer is provided at the first preset position of the blade section; At least one geometric parameter of the main reinforcing layer is iteratively adjusted, and the bending stiffness of the current blade section is recalculated after each adjustment until the deviation between the bending stiffness of the current blade section and the target bending stiffness meets the preset tolerance. If the bending stiffness of the current blade section still does not meet the preset tolerance after the geometric parameters of the main reinforcing layer reach its process limit, at least one auxiliary reinforcing layer is added at a second preset position different from the first preset position. With the geometric parameters of the main reinforcing layer fixed, the geometric parameters of the at least one auxiliary reinforcing layer are iteratively adjusted to continue to make the bending stiffness of the current blade section approach the target bending stiffness.

2. The method according to claim 1, characterized in that, The basic reinforcement layer for establishing the blade cross-section includes: A bidirectional fiber-reinforced composite material is used, laid along the chord length direction of the blade cross section from the leading edge to the trailing edge of the blade to form a closed shell structure.

3. The method according to claim 1, characterized in that, The method for obtaining the initial bending stiffness corresponding to the basic reinforcement layer based on the structural analysis algorithm includes: The bending stiffness components of the blade cross section in the flapping direction and the oscillation direction are calculated and obtained respectively.

4. The method according to claim 1, characterized in that, The iterative adjustment of at least one geometric parameter of the main enhancement layer includes: The thickness of the main reinforcing layer is adjusted incrementally by a preset thickness increment; Once the laying thickness reaches the limit thickness of a single process, the laying width of the main reinforcing layer is adjusted incrementally with a preset width increment.

5. The method according to claim 4, characterized in that, After adding at least one auxiliary reinforcement layer, the method further includes: According to a preset priority order, the geometric parameters of each auxiliary reinforcement layer are iteratively adjusted in sequence. Among them, the reinforcement layer closer to the leading edge of the blade is given priority to enter the parameter adjustment process over the reinforcement layer farther from the leading edge of the blade.

6. The method according to claim 1, characterized in that, Also includes: If the bending stiffness of the current blade section still does not meet the preset tolerance after adjusting the geometric parameters of all reinforcing layers to their process limits, then the material upgrade step is executed. The material upgrading steps include: Replace the material used in at least one reinforcing layer with a reinforcing material having a higher elastic modulus; After the material replacement, the process restarts from the step of iteratively adjusting the geometric parameters of the main reinforcing layer.

7. A device for optimizing the bending stiffness of a blade cross section, characterized in that, include: Establish a unit to create the basic reinforcement layer for the blade section; The comparison unit is used to obtain the initial bending stiffness corresponding to the basic reinforcement layer based on the structural analysis algorithm, and compare it with the target bending stiffness. The setting unit is used to set a main reinforcing layer at a first preset position on the blade section when the initial bending stiffness does not reach the target bending stiffness. The first adjustment unit is used to iteratively adjust at least one geometric parameter of the main reinforcement layer, and recalculate the bending stiffness of the current blade section after each adjustment until the deviation between the bending stiffness of the current blade section and the target bending stiffness meets the preset tolerance. An additional unit is provided to add at least one auxiliary reinforcement layer at a second preset position different from the first preset position if the bending stiffness of the current blade section still does not meet the preset tolerance after the geometric parameters of the main reinforcement layer reach its process limit. The second adjustment unit is used to iteratively adjust the geometric parameters of the at least one auxiliary reinforcement layer while keeping the geometric parameters of the main reinforcement layer fixed, so as to continue to make the bending stiffness of the current blade section approach the target bending stiffness.

8. An electronic device, characterized in that, include: At least one processor; as well as A memory communicatively connected to the at least one processor; wherein, The memory stores instructions that can be executed by the at least one processor to enable the at least one processor to perform the method of any one of claims 1-6.

9. A non-transitory computer-readable storage medium storing computer instructions, characterized in that, The computer instructions are used to cause the computer to perform the method according to any one of claims 1-6.

10. A computer program product, characterized in that, Includes a computer program that, when executed by a processor, implements the method according to any one of claims 1-6.

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