Axial flow fan blade, design method and equipment thereof and medium

Abstract

The invention provides an axial flow fan blade, a design method and equipment thereof and a medium, and belongs to the technical field of axial flow fan design. The design method comprises the steps that at least one inherent geometric reference of the axial flow fan blade is obtained; on the basis of an inherent geometric reference, a reinforcing structure composed of a plurality of rib-shaped protruding parts which are separated from one another and are distributed in a network shape is generated on one surface of the axial flow fan blade through a preset parameterization rule. By means of the reinforcing structure, the structural strength of the root of the blade can be effectively enhanced, deformation of the blade is restrained, physical gaps exist between the rib-shaped protruding parts due to the fact that the rib-shaped protruding parts are separated from one another, and the gaps form channels along the surface of the blade. The channels can effectively comb and guide boundary layer airflow which is originally disordered and easy to separate near the blade root, so that the boundary layer airflow is more attached to the surface of the blade to flow, the local flow field is improved, and the flow loss is reduced.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of axial flow fan design, in particular to an axial flow fan blade, a design method, equipment and medium thereof. BACKGROUND

[0002] The axial flow fan has been widely used in industrial production and civil facilities due to its advantages of large flow, low pressure head, high efficiency, compact structure and convenient maintenance. However, in actual operation, the root area of the axial flow fan blade is a weak link in structure. Due to stress concentration, this area is prone to fatigue cracks under high speed and variable working conditions. At the same time, the centrifugal force and aerodynamic load borne by the blade during rotation will cause the blade to deform, which not only reduces the aerodynamic efficiency of the fan, but also seriously shortens the service life of the fan. SUMMARY

[0003] The present disclosure provides an axial flow fan blade, a design method, equipment and medium thereof, which can effectively enhance the structural strength of the blade root and inhibit the deformation of the blade.

[0004] The technical solution of the present disclosure is implemented as follows: In a first aspect, the present disclosure provides a design method of an axial flow fan blade, comprising: obtaining at least one inherent geometric datum of the axial flow fan blade; based on the inherent geometric datum, generating a reinforcing structure composed of a plurality of mutually separated network-shaped arranged rib-shaped protrusions on a surface of the axial flow fan blade through a preset parameterization rule, wherein the gaps between the plurality of rib-shaped protrusions form channels for guiding airflow.

[0005] In a second aspect, the present disclosure provides a design device of an axial flow fan blade, comprising an obtaining part and a generating part, wherein: the obtaining part is configured to obtain at least one inherent geometric datum of the axial flow fan blade; the generating part is configured to generate a reinforcing structure composed of a plurality of mutually separated network-shaped arranged rib-shaped protrusions on a surface of the axial flow fan blade through a preset parameterization rule based on the inherent geometric datum, wherein the gaps between the plurality of rib-shaped protrusions form channels for guiding airflow.

[0006] In a third aspect, the present disclosure provides a computing device comprising a processor and a memory storing computer executable instructions, when the processor executes the computer executable instructions, the design method of the axial flow fan blade as described in the first aspect is implemented.

[0007] In a fourth aspect, the disclosure provides a computer-readable storage medium storing at least one instruction for being executed by a processor to implement the design method of the axial flow fan blade according to the first aspect.

[0008] In a fifth aspect, the disclosure provides an axial flow fan blade, comprising a blade body designed by the design method of the axial flow fan blade according to the first aspect, and a reinforcing structure arranged on one surface of the blade body, the reinforcing structure comprising a plurality of mutually separated network-shaped rib-shaped protrusions, and gaps between the plurality of rib-shaped protrusions forming channels for guiding airflow.

[0009] The disclosure provides an axial flow fan blade and a design method, device and medium thereof; a reinforcing structure composed of a plurality of mutually separated network-shaped rib-shaped protrusions is generated on one surface of the axial flow fan blade based on an inherent geometric reference, which can effectively enhance the strength of the blade root structure and inhibit deformation of the blade. In addition, since the rib-shaped protrusions are mutually separated, there are physical gaps between the rib-shaped protrusions, and the gaps along the surface of the blade form channels, which can effectively comb and guide the boundary layer airflow near the blade root which is originally turbulent and easy to separate, so that it flows more closely to the surface of the blade, thereby improving the local flow field and reducing flow loss. BRIEF DESCRIPTION OF DRAWINGS

[0010] Figure 1 An application environment suitable for the technical solution of the disclosure is provided for the disclosure.

[0011] Figure 2 A design method flowchart of an axial flow fan blade is provided for the disclosure.

[0012] Figure 3 A flowchart of the pre-preparation process is provided for the disclosure.

[0013] Figure 4 A parameter diagram for implementing the pre-preparation process is provided for the disclosure.

[0014] Figure 5 A blade model diagram obtained after the pre-preparation process is provided for the disclosure.

[0015] Figure 6 A diagram for generating the main rib centerline is provided for the disclosure.

[0016] Figure 7 A diagram for generating the side rib centerline is provided for the disclosure.

[0017] Figure 8A schematic diagram of a rib line consisting of one main rib and six side ribs provided for the present disclosure.

[0018] Figure 9 A preliminary rib entity schematic diagram provided for the present disclosure.

[0019] Figure 10 A method flowchart of bias curved surface cutting provided for the present disclosure.

[0020] Figure 11 A bias curved surface schematic diagram provided for the present disclosure.

[0021] Figure 12 A schematic diagram of an axial flow fan blade provided for the present disclosure.

[0022] Figure 13 A stress simulation result schematic diagram provided for the present disclosure.

[0023] Figure 14 A deformation simulation result schematic diagram provided for the present disclosure.

[0024] Figure 15 Another stress simulation result schematic diagram provided for the present disclosure.

[0025] Figure 16 Another deformation simulation result schematic diagram provided for the present disclosure.

[0026] Figure 17 A flow-static pressure curve comparison diagram provided for the present disclosure.

[0027] Figure 18 An efficiency-static pressure curve comparison diagram provided for the present disclosure.

[0028] Figure 19 A schematic diagram of a design device of an axial flow fan blade provided for the present disclosure.

[0029] Figure 20 Another schematic diagram of a design device of an axial flow fan blade provided for the present disclosure. DETAILED DESCRIPTION

[0030] The technical solutions in the present disclosure will be described clearly and completely below in combination with the drawings in the present disclosure.

[0031] It should be noted that in the description of the present disclosure, the terms "comprising", "containing" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such a process, method, article or device. Without more limitations, the element defined by the statement "comprising a" does not exclude the presence of other identical elements in the process, method, article or device including the element. The terms "embodiments of the present disclosure", "embodiments of the present application" or "the present disclosure" and the like used throughout the description refer to the technical solutions of the present disclosure.

[0032] Figure 1 An application environment suitable for the technical solutions of the present disclosure is provided. The core of the application environment is a computing device 100, which can be a high-performance graphics workstation, a node in a server cluster, or a personal computer with sufficient computing power. The computing device 100 runs a set of professional CAD software, and the user interface 110 of the CAD software is displayed on the display 120. The user can interact with the CAD software through input devices such as keyboard 130 and mouse 140 to design and modify three-dimensional models, such as the axial flow fan blade 115 shown in FIG. 1B. The design method proposed in the present disclosure can be provided as an embedded functional module or an independent plug-in of the CAD software. Figure 1

[0033] Further, the computing device 100 includes, but is not limited to, one or more processors 910, memories 920, input / output (I / O) interfaces 930, and storage devices 940, which are connected and communicate with each other through a system bus 950.

[0034] The processor 910 can be a central processing unit (CPU), a graphics processing unit (GPU), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or any combination of these processing units. In the implementation of the present disclosure, the processor 910 is the core of executing instructions, responsible for executing computer program instructions stored in the memory 920 to complete complex three-dimensional geometric modeling, parameterized calculation, constraint solving, and graphic rendering tasks.

[0035] ​The memory 920 can include a volatile memory, such as a Random Access Memory (RAM), used as the temporary working space of the processor 910, and a non-volatile memory, such as a Read-Only Memory (ROM) or a flash memory. The storage device 940, such as a Solid-State Drive (SSD) or a mechanical Hard Disk Drive (HDD), is used for long-term storage of data and programs. In the present embodiment, an operating system and a CAD software program (embodied as computer executable instructions) implementing the design method of the present disclosure are stored in the storage device 940 and loaded into the memory 920 for execution by the processor 910 when needed.

[0036] The I / O interface 930 is responsible for communication between the computing device 100 and external devices, and is connected to, for example, the display 120, the keyboard 130, the mouse 140, and the like as shown in the application environment. Figure 1

[0037] In the application environment as shown in Figure 1 , the present disclosure provides a design method for an axial flow fan blade. Figure 2 A flowchart of the design method for the axial flow fan blade is shown. The method can be implemented by the computing device 100, in particular by the processor 910.

[0038] Referring to Figure 2 , in step S210, at least one inherent geometric reference of the axial flow fan blade is obtained.

[0039] In the present disclosure, the inherent geometric reference refers to a geometric feature determined by the basic aerodynamic shape of the blade itself, which is not arbitrarily set by humans. It provides a stable and repeatable reference frame for the generation of the subsequent reinforcing structure. In the present disclosure, the inherent geometric reference is the included angle between the leading edge and the trailing edge of the blade root. Specifically, on the axial projection plane of the impeller, two rays are drawn from the impeller center point O to the leading edge point LE and the trailing edge point TE, which are the intersection lines of the blade root and the hub, respectively. The included angle between the two rays is the . This included angle is selected as the reference because it directly reflects the airflow deflection and blade twist characteristics at the blade root, and is one of the most essential geometric properties of the blade.

[0040] In step S220, based on the inherent geometric reference, a reinforcing structure composed of a plurality of mutually separated, network-like arranged rib-shaped protrusions is generated on one surface of the axial flow fan blade through a pre-set parameterization rule.

[0041] Specifically, after obtaining the inherent geometric reference (for example, the included angle ​After that, the present disclosure utilizes a series of deterministic mathematical relationships (i.e., parametric rules) to generate the reinforcing structure on one surface of the blade. For example, the reinforcing structure is generated on the pressure surface that bears the major aerodynamic load.

[0042] In some examples, as shown in Figure 8 , the reinforcing structure is not a monolithic entity, but is composed of a plurality of rib-like protrusions, which include main ribs and side ribs, and are arranged in a network on the surface of the blade. Moreover, the rib-like protrusions are separated from each other, so that there are physical gaps between the rib-like protrusions.

[0043] Specifically, continuing to refer to Figure 6 , the gaps formed between the rib-like protrusions constitute channels along the surface of the blade. When the axial flow fan is running, the channels can effectively comb and guide the originally turbulent and easily separated boundary layer flow near the blade root to flow more closely to the surface of the blade. Thus, the rib-like protrusions generated on the surface of the blade in the present disclosure achieve the dual effects of structural reinforcement and aerodynamic optimization. In detail, the rib-like protrusions themselves serve as reinforcing ribs, which significantly improve the mechanical strength and stiffness of the blade root; and the channels between them improve the local flow field and reduce flow loss. In this way, the technical contradiction in some existing related solutions that increasing structural support often sacrifices aerodynamic performance is solved.

[0044] Figure 2 As shown in the technical solution, the reinforcing structure composed of a plurality of rib-like protrusions arranged in a network and separated from each other is generated on one surface of the blade of the axial flow fan based on the inherent geometric reference, which can effectively enhance the structural strength of the blade root and inhibit the deformation of the blade. In addition, since the rib-like protrusions are separated from each other, there are physical gaps between the rib-like protrusions, which constitute channels along the surface of the blade. The channels can effectively comb and guide the originally turbulent and easily separated boundary layer flow near the blade root to flow more closely to the surface of the blade, thereby improving the local flow field and reducing flow loss.

[0045] In some embodiments, before implementing the design method shown in Figure 2 , the present disclosure further provides a pre-preparation process for converting the macroscopic performance requirements of the axial flow fan into microcosmic blade geometric design parameters. Through the pre-preparation process, a three-dimensional blade model for implementing the design method shown in Figure 2 can be obtained, that is, the technical solution shown in Figure 2 is to generate the reinforcing structure composed of rib-like protrusions arranged in a network based on the three-dimensional blade model obtained in the pre-preparation process. Specifically, as shown in Figure 3 , the pre-preparation process includes: S310: Determine the performance parameters and geometric limit parameters.

[0046] In this disclosure, performance parameters may include the static pressure required for the axial flow fan to overcome system resistance in a real-world scenario. The air volume required in a real-world scenario, i.e., airflow. And the fan speed required to meet the first two requirements. (Unit: RPM)

[0047] Geometric limiting parameters may include the impeller hub radius. Casing radius and the number of leaves .

[0048] S320: Based on performance parameters and geometric constraints, the geometric parameters required to construct a two-dimensional airfoil section are calculated using aerodynamic formulas.

[0049] In this disclosure, combined with Figure 4 The geometric parameters required to construct a two-dimensional airfoil section include: Tangential velocity This parameter represents the component of velocity along the direction of rotation at different radii of the blades in an axial flow fan. The calculation formula is:

[0050] in, This represents the angular velocity of the fan's rotation. This indicates the impeller diameter.

[0051] Axial velocity This parameter represents the average velocity of the airflow along the axial direction of the axial flow fan. Its calculation formula is:

[0052] Import angle This parameter represents the absolute angle at which the airflow enters the blade.

[0053] Outlet airflow angle This parameter represents the absolute angle at which the airflow leaves the blade. In this disclosure, this angle is derived based on the classical Euler equation, specifically, static pressure... satisfy Based on this formula, the exit angle can be obtained. ,in, This represents air density. In actual physical phenomena, airflow does not flow along the suction surface of the fan blades as ideally as it would in reality. Instead, due to boundary layers, adverse pressure gradients, and other factors, the airflow will detach from the fan blades prematurely. In this case, to maintain the airflow angle in the physical field... The design must remain unchanged; therefore, the exit geometry of the blades must be adjusted during blade shaping. Less than the exit geometry angle Approximately 3 degrees, in this disclosure, this 3 degrees is a design empirical value.

[0054] Installation corner This parameter is the angle between the blade chord line and the axial direction of the axial flow fan. Its calculation formula is: .

[0055] String The length of the line connecting the leading and trailing edges of the blade (i.e., the impeller chord) is given by the following formula:

[0056] In the above formula, This is the lift coefficient, typically taken as an empirical value of 0.8 to 1.2; The average radius is, i.e. .

[0057] S330: After determining the above geometric parameters, a parametric cubic Bézier curve is used to generate the airfoil's centerline. Its parametric equation is:

[0058] In the parametric equations above, there are four control points. , , , They are defined as , , , , This represents the maximum camber. Using the above parametric equations, the centerline shape of the airfoil can be determined.

[0059] S340: After obtaining the centerline of the airfoil, the suction surface thickness and pressure surface thickness are set on both sides of the centerline respectively, thereby determining the complete two-dimensional airfoil section with a specific blade height.

[0060] Specifically, for airfoil wind turbine blades, the thickness of the airfoil cross-section is not uniformly distributed from the leading edge to the trailing edge, such as... Figure 4 As shown. The thickness of the blade directly affects its aerodynamic performance. Therefore, this disclosure, considering factors such as blade size, structural strength, and material cost, sets the suction surface thickness as d1 and the pressure surface thickness as d2. The suction surface thickness is then determined to be within the range of 1.2%L ≤ d1 ≤ 12%L, and the pressure surface thickness is determined to be within the range of 1.2%L ≤ d2 ≤ 10%L. The final blade is shown below. Figure 5 As shown It can be understood that by spatially stacking multiple two-dimensional airfoil sections at different blade heights according to a preset stacking rule, a shape that can be used as... Figure 2 The three-dimensional blade model is used as the basis for designing the technical solution shown.

[0061] In some embodiments, the ribbed protrusions in the reinforcing structure include at least one main rib and at least one side rib offset relative to the main rib. The main rib forms the basis of the entire reinforcing structure and serves as a reference for setting the side ribs. Specifically, when generating the reinforcing structure, the geometric properties of the main rib are first determined. Then, the geometric properties of all side ribs are derived from the geometric properties of the main rib and preset parameters.

[0062] The geometric position of the main rib is not arbitrarily set, but is related to the inherent geometric reference of the blade itself. Specifically, this geometric reference is the angle formed between the leading edge and trailing edge of the blade root on the axial projection plane of the blade (here, axial refers to the plane with the wind turbine's rotation axis as the normal). .like Figure 6 As shown, after obtaining this included angle Subsequently, the geometric position of the main ribs is determined by rotating the projected profile of the leading edge of the blade within a preset blade height range around the impeller center by an angle β. After this rotation, the centerline of the main ribs can be obtained as follows: Figure 6 The bold line in the text is shown.

[0063] exist Figure 6 In this context, the rotation angle β is not an empirical or arbitrarily set value, but rather related to... Figure 6 The included angle It satisfies the following mathematical relationship:

[0064] Based on the above mathematical relationship, the layout of the main ribs is deterministically bound to the most basic aerodynamic geometric features of the blade.

[0065] In this disclosure, the reinforcing structure (including main ribs and side ribs) is distributed within a region extending from the blade root along the blade height direction to within 60% of the total blade height, as defined in the aforementioned preset blade height range. "60% blade height" is selected as the upper limit of the reinforcing structure's effect. Specifically, the aforementioned preset blade height range includes the region from the blade root to the lower middle section. This region is where stress is most concentrated under centrifugal force and aerodynamic loads, and it is also the most vulnerable area for fatigue fracture in practical applications. Furthermore, this region is also where airflow separation is likely to occur, resulting in poor flow field performance. Based on this, this disclosure limits the reinforcing structure to this range, which not only improves the mechanical strength and stiffness of the blade root but also avoids unnecessary disturbances to the upper part of the blade, which is more sensitive to aerodynamic performance and has a better flow field, thus maximizing the cost-effectiveness ratio.

[0066] like Figure 7 As shown, in this disclosure, the side reinforcements are symmetrically or asymmetrically distributed on both sides of the main reinforcements, forming a network that works together to bear loads. The geometric properties of the side reinforcements are derived from the geometric properties of the main reinforcements and preset parameters.

[0067] Specifically, the positional attribute of the side ribs, namely the offset distance between the side ribs and the main ribs, is generated after the main ribs are offset to both sides along the hub surface by a preset arc length d. This offset distance d is parameterized as the chord length at the blade root. L A percentage, that is , where the parameters The range of values ​​for has been optimized, and is preferably 0. .

[0068] The angular attribute of the side reinforcement, namely the rotation angle of the side reinforcement, is the rotation angle of the side reinforcement relative to the chord length of the main reinforcement. Angle with the vertical direction The length is increased or decreased regularly. For the Nth pair of lateral ribs (N≥1), its chord length... Angle relative to the vertical direction Specifically: when the side reinforcement shifts along the front edge direction, the shift rotation angle is... The preferred range of b is When the side reinforcement shifts along the leading edge, the shift rotation angle is... The preferred range of b is .

[0069] The length attribute of the side reinforcement, namely the chord length of the side reinforcement. Relative to the chord length of the main reinforcement Perform a regular reduction. For the Nth pair of lateral ribs (N≥1), its chord length is: the chord length of the lateral rib along the leading edge direction is... The preferred range for the scaling factor x is: The chord length of the lateral ribs along the tail edge direction is... The preferred range for the scaling factor y is: .

[0070] Based on the above definitions of the geometric properties of the main and side reinforcement bars, the position, orientation, and dimensions of the entire reinforced structure can be precisely controlled using a few parameters and mathematical formulas.

[0071] For example, when the number of side reinforcement pairs N=3, it can generate something like this. Figure 8 The diagram shows a reinforced structure with seven reinforcement bars, consisting of one main bar and six side bars. This parametric method eliminates reliance on the designer's experience, ensuring design accuracy, repeatability, and optimizability, thus improving design efficiency. After defining the centerlines of the main reinforcement and side reinforcement using the parameterization method described in the above embodiments, it is necessary to convert these centerlines into a solid structure with a certain width and height.

[0072] Specifically, the curves of each rib are used as the centerline, and a predetermined width (e.g., 1.5% of the chord length L of each rib) is extended to both sides to form a strip-shaped region. This strip-shaped region is then stretched axially until it completely intersects the pressure surface of the blade, forming a preliminary rib structure. Figure 9 As shown.

[0073] However, if these stretched ribs are directly subjected to a simple Boolean operation (such as geometric union) with the blade pressure surface, it will result in sharp, near-90-degree ridges or stepped transitions at the junction of the ribs and the blade surface. From an aerodynamic perspective, this geometric discontinuity severely disrupts the boundary layer flow on the blade surface, becoming a cause of airflow separation, thereby generating vortices, increasing aerodynamic drag, and reducing wind turbine efficiency.

[0074] Based on this, when converting the main ribs and side ribs into a solid structure according to their centerlines, a smooth transition can be achieved between the rib-like protrusions and the blade surface using an offset curved surface cutting method. For example... Figure 10 As shown, the method specifically includes the following steps: S1001: Generate an offset surface.

[0075] In this disclosure, the original pressure surface of the blade is offset outward (i.e., away from the blade body) by a predetermined small distance along the normal direction at each point, thereby generating a new, geometrically smoother offset surface, such as... Figure 11 As shown. This offset distance is not an arbitrary value, but rather an optimized selection; for example, it can be set between 5% and 15% of the blade chord length L. Choosing this range ensures a sufficiently smooth transition zone while avoiding excessive impact on the effective reinforcement height of the ribs.

[0076] S1002: Use an offset curved surface to cut the ribbed protrusions.

[0077] Specifically, after generating the offset surface, the initial rib solid with sharp edges, formed by stretching as described in the aforementioned technical solution, is trimmed using the offset surface as a cutting tool or trimming boundary. In CAD software, this is typically achieved through commands such as surface cut or solid trimming.

[0078] Through this operation, the top and sides of the ribbed structure are smoothly trimmed, and the connection between it and the leaf body is no longer a sharp intersection line, but rather forms a smooth transition zone with continuously varying curvature. For example...Figure 12 As shown, the final contour line smoothly transitions from the original pressure surface to the top of the rib, effectively eliminating stress concentration points and airflow separation points.

[0079] pass Figure 9 The proposed solution not only resolves the geometric and functional contradictions between the discrete reinforcing structure and the continuous aerodynamic surface, but also ensures the reliability of the structural connections and the smooth and aesthetically pleasing appearance. More importantly, it guides the airflow to smoothly bypass the reinforcing structure, preserving the flow field quality on the blade surface to the maximum extent. This achieves a synergistic improvement in both structural reinforcement and aerodynamic optimization.

[0080] Based on the foregoing technical solution, this disclosure also provides an axial flow fan blade obtained through the aforementioned axial flow fan blade design method. Please refer to [link to relevant documentation]. Figure 12 The axial flow fan blade 800 includes a blade body 810, on one surface (e.g., the pressure surface) of the blade body 810, a reinforcing structure 820 as described in this disclosure is provided. Figure 12 In this structure, the reinforcing structure 820 consists of multiple mutually separated, network-arranged rib-like protrusions, and the gaps between these rib-like protrusions form channels 830 for guiding and combing airflow near the leaf roots.

[0081] Based on the aforementioned technical solution, this disclosure illustrates the effectiveness of the technical solution through the following testing process.

[0082] First, this disclosure presents a finite element simulation analysis of the structural strength and deformation resistance of a blade before and after implementing the aforementioned design method. The simulation results are as follows: Figures 13 to 16 As shown, where, Figure 13 and Figure 14 These are the stress diagram and deformation diagram of the blade before the aforementioned technical methods were applied. Figure 15 and Figure 16 These are stress and deformation diagrams of the blade after the aforementioned technical methods have been applied. Through comparison... Figure 13 and Figure 15 It can be seen that at a rated speed of 1500 rpm, the blades obtained using the aforementioned design method exhibit a 18% reduction in maximum equivalent stress. This can be compared with... Figure 14 and Figure 16 It can be seen that at the rated speed of 1500 rpm, the blade obtained by the aforementioned design method has a maximum deformation that is reduced by 30.8%.

[0083] In addition to structural strength, this disclosure also includes simulation analysis of the aerodynamic performance of the blade before and after implementing the aforementioned design method. The simulation results are as follows: Figure 17 and 18 As shown, where, Figure 17The flow-static pressure curves of the blades before and after implementing the aforementioned design method are shown. Figure 18 The efficiency-static pressure curves of the blades before and after implementing the aforementioned design method are shown. From Figure 17 and Figure 18 It can be seen that after implementing the aforementioned design method, the aerodynamic performance of the blades was not sacrificed. On the contrary, the poor flow field at the blade root was improved, thus enhancing the overall aerodynamic performance of the fan.

[0084] Based on the same concept as the aforementioned technical solutions, see Figure 19 The illustration shows the composition of a design apparatus 1900 for an axial flow fan blade provided in this disclosure. The apparatus 1900 includes an acquisition section 1901 and a generation section 1902, wherein... Acquisition section 1901 is configured to acquire at least one inherent geometric reference of the axial flow fan blades; The generation section 1902 is configured to generate a reinforcing structure on one surface of an axial fan blade based on an inherent geometric reference and through preset parameterization rules. This structure consists of multiple mutually separated, network-arranged rib-like protrusions, wherein the gaps between the multiple rib-like protrusions form channels for guiding airflow.

[0085] In some examples, the reinforcing structure includes at least one main reinforcement bar and at least one side reinforcement bar offset relative to the main reinforcement bar.

[0086] In some examples, the inherent geometric reference includes the angle formed between the leading and trailing edges of the blade root, and the geometric position of the main rib is determined based on this angle using a preset functional relationship.

[0087] In some examples, the geometric position of the main rib is determined by rotating the projected profile of the blade leading edge within a predetermined blade height range about the impeller center by an angle, wherein the rotation angle and the included angle satisfy a preset mathematical relationship.

[0088] In some examples, at least one of the properties of the side reinforcement, such as position, angle, and length, is generated based on the corresponding property of the main reinforcement using a set of preset parametric offsets or scaling factors.

[0089] See in some examples Figure 20 The device 1900 also includes a smoothing portion 1903 configured to bias the surface of the blade outward to generate a biased surface; and to use the biased surface to cut the ribbed protrusion to form a smooth transition between the ribbed protrusion and the blade surface.

[0090] In some examples, the reinforcing structure is distributed in the area extending from the leaf root along the leaf height to within 60% of the total leaf height.

[0091] This disclosure also provides a computer-readable storage medium storing at least one instruction that is executed by a processor to implement the axial fan blade design method described in the above embodiments.

[0092] This disclosure also provides a computer program product including computer instructions stored in a computer-readable storage medium; a processor of a computing device reads the computer instructions from the computer-readable storage medium and executes the computer instructions, causing the computing device to perform the design method for axial flow fan blades described in the above embodiments.

[0093] Those skilled in the art will recognize that the functions described in this disclosure in one or more of the examples above can be implemented using hardware, software, firmware, or any combination thereof. When implemented in software, these functions can be stored in a computer-readable medium or transmitted as one or more instructions or code on a computer-readable medium. Computer-readable media include computer storage media and communication media, wherein communication media include any medium that facilitates the transfer of a computer program from one place to another. Storage media can be any available medium accessible to a general-purpose or special-purpose computer.

[0094] It should be noted that the technical solutions described in this disclosure can be combined arbitrarily as long as they do not conflict.

[0095] The above description is merely a specific embodiment of this disclosure, but the scope of protection of this disclosure is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this disclosure should be included within the scope of protection of this disclosure.

Claims

1. A design method for axial flow fan blades, characterized in that, The method includes: Obtain at least one inherent geometric reference for the axial flow fan blades; Based on the inherent geometric reference, and through preset parameterization rules, a reinforcing structure is generated on one surface of the axial flow fan blade, consisting of multiple mutually separated, network-arranged rib-like protrusions, wherein the gaps between the multiple rib-like protrusions form channels for guiding airflow.

2. The design method according to claim 1, characterized in that, The reinforcing structure includes at least one main reinforcement bar and at least one side reinforcement bar offset relative to the main reinforcement bar.

3. The design method according to claim 2, characterized in that, The inherent geometric reference includes the angle formed between the leading and trailing edges of the blade root, and the geometric position of the main rib is determined based on the angle through a preset functional relationship.

4. The design method according to claim 3, characterized in that, The geometric position of the main rib is determined by rotating the projected profile of the leading edge of the blade within a predetermined blade height range around the impeller center by an angle, wherein the angle and the included angle satisfy a preset mathematical relationship.

5. The design method according to claim 2, characterized in that, At least one of the attributes of the side reinforcement, such as position, angle, and length, is generated based on the corresponding attribute of the main reinforcement through a set of preset parameterized offsets or scaling factors.

6. The design method according to claim 1, characterized in that, The design method further includes: The surface of the blade is offset outward to generate an offset surface; The offset curved surface is used to cut the ribbed protrusion to form a smooth transition between the ribbed protrusion and the blade surface.

7. The design method according to claim 1, characterized in that, The reinforcing structure is distributed in the area extending from the leaf root along the leaf height direction to within 60% of the total leaf height.

8. A computing device, characterized in that, The computing device includes a processor and a memory storing computer-executable instructions, wherein when the processor executes the computer-executable instructions, it implements the design method for axial flow fan blades as described in any one of claims 1 to 7.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores at least one instruction, which is executed by a processor to implement the design method for axial fan blades as described in any one of claims 1 to 7.

10. An axial flow fan blade, comprising a blade body, characterized in that, The blade body is designed by the design method of axial flow fan blade according to any one of claims 1 to 7, and a reinforcing structure is provided on one surface of the blade body. The reinforcing structure includes a plurality of mutually separated, network-arranged rib-like protrusions, and the gaps between the plurality of rib-like protrusions form channels for guiding airflow.

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