A compressor low reynolds number airfoil optimization method, device, electronic equipment, storage medium and program product

Abstract

This application relates to the field of aero-engine technology, and in particular provides a method, apparatus, electronic device, storage medium, and program product for optimizing compressor airfoils at low Reynolds numbers. The method involves shaping the airfoil to obtain its shape; performing flow surface calculations on the shape to obtain the shape factor distribution of the blade surface turbulence; and adjusting the camber distribution of the airfoil until the shape factor value is less than or equal to the preset threshold when the shape factor value before a sudden increase in the shape factor distribution exceeds a preset threshold. Implementing the technical solution of this application can improve the aerodynamic stability of the airfoil under low Reynolds number conditions.

Description

Technical Field

[0001] This application relates to the field of aero-engine technology, and in particular to a method, apparatus, electronic equipment, storage medium, and program product for optimizing compressor low Reynolds number blade configurations. Background Technology

[0002] High altitude, low speed, and low Reynolds number have a significant impact on the performance and stability of aero-engine components. At high altitudes, the low air density and high kinematic viscosity create low Reynolds number conditions, leading to increased airflow friction drag, which in turn affects compressor performance, particularly causing a significant decrease in compressor aerodynamic stability.

[0003] Good basic airfoil design is the foundation for achieving compressor performance targets. Currently, there is relatively mature experience in airfoil design for different inflow conditions on the ground, but the aerodynamic stability of airfoil compressors under low Reynolds number conditions is still relatively poor. Summary of the Invention

[0004] This application is made in view of the above-mentioned problems. This application provides a method, apparatus, electronic equipment, storage medium, and program product for optimizing the low Reynolds number airfoil profile of a compressor.

[0005] In a first aspect, embodiments of this application provide a method for optimizing the airfoil profile for a compressor with low Reynolds number, including:

[0006] The leaf shape is shaped to obtain the desired leaf shape;

[0007] Perform flow surface calculations on the aforementioned design to obtain the shape factor distribution of the blade surface turbulence;

[0008] If the shape factor value before the sudden increase in the shape factor distribution is greater than a preset threshold, the curvature distribution of the leaf shape is adjusted until the shape factor value is less than or equal to the preset threshold.

[0009] Furthermore, according to a compressor low Reynolds number airfoil optimization method according to the first aspect of the present application, after adjusting the camber distribution of the airfoil until the shape factor value is less than or equal to the preset threshold, the method further includes:

[0010] Output the coordinates of the blade shape.

[0011] Furthermore, according to a compressor low Reynolds number airfoil optimization method according to the first aspect of the present application, the step of shaping the airfoil to obtain the airfoil shape includes:

[0012] Obtain the segmentation parameters and construction angle parameters of the middle arc. The segmentation parameters of the middle arc include the axial position of the dividing point of the front and rear middle arcs and the proportion of the bending angle of the front segment. The construction angle parameters include the inlet construction angle and the outlet construction angle.

[0013] Under the constraint of satisfying the first-order continuity of the middle arc, the middle arc is constructed according to the middle arc segmentation parameters and the construction angle parameters;

[0014] Obtain thickness control parameters, including leading edge thickness, trailing edge thickness, maximum thickness and its location;

[0015] The shape is generated based on the mid-arc line and the thickness control parameters.

[0016] Furthermore, according to a compressor low Reynolds number airfoil optimization method according to the first aspect of the present application, the step of performing flow surface calculation on the airfoil to obtain the shape factor distribution of the blade surface turbulence includes:

[0017] Within the S1 flow surface defined by the aforementioned shape, a high-altitude low Reynolds number inlet condition is established;

[0018] Solve the Euler equation over the main region to obtain the Euler solution;

[0019] For the turbulent near-wall region close to the blade surface, the boundary layer equations are solved in a coupled manner to obtain the boundary layer solution;

[0020] Based on the Euler solution and the boundary layer solution, the stable flow field solution of the S1 flow surface is obtained;

[0021] Based on the stable flow field solution, the shape factor distribution of the perturbation on the blade surface is extracted.

[0022] Furthermore, according to a compressor low Reynolds number airfoil optimization method according to the first aspect of the present application, when the shape factor value before the sudden increase in the shape factor distribution is greater than a preset threshold, adjusting the camber distribution of the airfoil until the shape factor value is less than or equal to the preset threshold includes:

[0023] When the shape factor value before the sudden increase in the shape factor distribution is greater than the preset threshold, without changing the inlet construction angle, outlet construction angle and the boundary of the arc shape in the front and rear sections of the blade, the ratio of the arc bend angle in the front half of the blade to the total bend angle is changed until the shape factor value is less than or equal to the preset threshold.

[0024] Furthermore, according to the first aspect of the embodiments of this application, a compressor low Reynolds number blade optimization method is provided, wherein the preset threshold is 2.7.

[0025] Secondly, embodiments of this application provide a compressor low Reynolds number blade optimization device, comprising:

[0026] The shaping module is used to shape the leaf shape to obtain the desired leaf shape.

[0027] The calculation module is used to perform flow surface calculations on the design to obtain the shape factor distribution of the blade surface disturbance;

[0028] An optimization module is used to adjust the curvature distribution of the leaf shape when the shape factor value before a sudden increase in the shape factor distribution is greater than a preset threshold, until the shape factor value is less than or equal to the preset threshold.

[0029] Thirdly, embodiments of this application provide an electronic device, including a memory, a processor, and a computer program stored in the memory, wherein the processor executes the computer program to implement the steps of any of the above methods.

[0030] Fourthly, embodiments of this application provide a computer-readable storage medium having a computer program / instructions stored thereon, which, when executed by a processor, implements the steps of any of the above methods.

[0031] Fifthly, embodiments of this application provide a computer program product, including a computer program / instructions that, when executed by a processor, implement the steps of any of the methods described above.

[0032] As will be described in detail below, the compressor low Reynolds number airfoil optimization method according to embodiments of this application improves the aerodynamic stability of the airfoil under low Reynolds number conditions by performing airfoil shaping, calculating the flow surface based on the shape, and extracting the shape factor distribution. In the region before a sudden increase in the shape factor, the camber distribution is adjusted until the shape factor value meets the requirements. This also optimizes the anti-separation capability and overall aerodynamic performance of the rear section of the suction surface.

[0033] It should be understood that both the foregoing general description and the following detailed description are exemplary and intended to provide further illustration of the claimed technology. Attached Figure Description

[0034] The above and other objects, features, and advantages of this application will become more apparent from the more detailed description of the embodiments of this application in conjunction with the accompanying drawings. The accompanying drawings are used to provide a further understanding of the embodiments of this application and form part of the specification. They are used together with the embodiments of this application to explain this application and do not constitute a limitation thereof. In the accompanying drawings, the same reference numerals generally represent the same components or steps.

[0035] Figure 1 This is a flowchart illustrating a compressor low Reynolds number airfoil optimization method according to an embodiment of this application.

[0036] Figure 2 This is a flowchart illustrating the airfoil shaping process in a compressor low Reynolds number airfoil optimization method according to an embodiment of this application.

[0037] Figure 3 This is a schematic diagram of the airfoil shape in a compressor low Reynolds number airfoil optimization method according to an embodiment of this application.

[0038] Figure 4 This is a flowchart illustrating the acquisition of shape factor distribution in a compressor low Reynolds number airfoil optimization method according to an embodiment of this application.

[0039] Figure 5 This is a further illustration comparing the influence of shape factor on the velocity profile within the boundary layer in a compressor low Reynolds number blade optimization method according to an embodiment of this application.

[0040] Figure 6 This is a further illustration of the airfoil surface shape factor distribution in a compressor low Reynolds number airfoil optimization method according to an embodiment of this application, to meet the shape factor requirements.

[0041] Figure 7 This is a further illustration of the distribution of airfoil surface shape factors that do not meet the shape factor requirements in a compressor low Reynolds number airfoil optimization method according to an embodiment of this application.

[0042] Figure 8 This is a block diagram illustrating a compressor low Reynolds number blade optimization device according to an embodiment of this application.

[0043] Figure 9 This is a schematic diagram illustrating a computer program product according to an embodiment of this application.

[0044] Figure 10 This is a hardware block diagram illustrating an electronic device according to an embodiment of this application. Detailed Implementation

[0045] To make the objectives, technical solutions, and advantages of this application more apparent, exemplary embodiments according to this application will be described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of this application, and not all embodiments of this application. It should be understood that this application is not limited to the exemplary embodiments described herein.

[0046] See Figure 1 A method for optimizing compressor airfoil profiles with low Reynolds number includes:

[0047] S101, the leaf shape is shaped to obtain the desired leaf shape.

[0048] S102, perform flow surface calculations on the blade shape to obtain the shape factor distribution of the blade surface turbulence.

[0049] S103, when the shape factor value before the sudden increase in the shape factor distribution is greater than the preset threshold, adjust the curvature distribution of the leaf shape until the shape factor value is less than or equal to the preset threshold.

[0050] In this embodiment, the airfoil is first shaped to obtain its geometric shape. Then, flow surface calculations are performed based on this shape to obtain the shape factor distribution of the turbulence on the blade surface. Next, the maximum shape factor value before the point of sudden increase in shape factor is used to determine the airfoil's camber distribution. If this value is greater than a preset threshold, the camber distribution of the airfoil is adjusted. Through iterative optimization, until the maximum shape factor value is no greater than the preset threshold, the boundary layer velocity profile of the airfoil turbulence becomes fuller, improving the airfoil's anti-separation capability. This, in turn, helps improve the compressor's aerodynamic stability under low Reynolds number conditions, thereby obtaining a target airfoil that meets the boundary layer flow stability requirements under low Reynolds number conditions.

[0051] The preset threshold can be set according to requirements, for example, it can be set to 2.7.

[0052] After step S103, the method further includes: outputting the coordinates of the blade shape.

[0053] In one embodiment, see Figure 2 Step S101 includes:

[0054] S201, obtain the segmentation parameters and structural angle parameters of the middle arc. The segmentation parameters of the middle arc include the axial position of the dividing point of the middle arc between the front and rear segments and the proportion of the bending angle of the front segment. The structural angle parameters include the inlet structural angle and the outlet structural angle.

[0055] S202, under the constraint of satisfying the first-order continuity of the middle arc, construct the middle arc according to the segmentation parameters and construction angle parameters of the middle arc.

[0056] S203, obtain thickness control parameters, including leading edge thickness, trailing edge thickness, maximum thickness and its position.

[0057] S204 generates the shape based on the mid-curve and thickness control parameters.

[0058] In the embodiments of this application, see Figure 3 The middle arc 301 adopts a double-circular arc design. The designer can specify the segment parameters of the middle arc 301, including the axial position of the dividing point between the front and rear middle arc 301 segments |AS| / |AB|, and the ratio of the bend angle of the front half of the middle arc 301 to the total bend angle, Q = Δβ. AS / Δβ AB =(β) A -β S ) / (β A -β BThe structural angle parameters, including the inlet structural angle β, are provided by the designer. A and the outlet structural angle β B Under the constraint of ensuring the first-order continuity of the mid-arc 301 in both the first and second halves, the complete mid-arc 301 can be obtained. Generally speaking, β A and β B Given from upstream design; |AS| / |AB| and Δβ AS / Δβ AB Based on design experience, adjusting the above two parameters can change the distribution of the curvature of the mid-curve 301 along the chord direction, thereby changing the load distribution of the blade profile along the chord direction. After obtaining the mid-curve 301, given the leading and trailing edge thickness, maximum thickness, and maximum thickness position, the pressure and suction surfaces of the blade profile can be shaped to obtain the shape 302.

[0059] In one embodiment, see Figure 4 Step S102 includes:

[0060] S401, within the S1 flow surface defined by its shape, sets up high-altitude low Reynolds number inlet conditions;

[0061] S402, Solve the Euler equation over the main region to obtain the Euler solution;

[0062] S403, for the turbulent near-wall region close to the blade surface, the boundary layer equation is solved in a coupled manner to obtain the boundary layer solution;

[0063] S404, based on the Euler solution and the boundary layer solution, obtain the stable flow field solution of the S1 flow surface;

[0064] S405, based on the steady flow field solution, extracts the shape factor distribution of the blade surface disturbance.

[0065] In this embodiment, S1 flow surface calculations are performed for the blade profile. The flow surface calculations are performed under high-altitude, low Reynolds number inlet conditions. The Euler equations are solved in the main flow region, and the boundary layer equations are solved in the near-wall region of the blade turbulence, yielding a stable solution for the S1 flow surface and the shape factor distribution of the blade surface turbulence. The shape factor is defined as the ratio H of the local boundary layer flow loss thickness δ1 to momentum loss thickness δ2. 12 =δ1 / δ2.

[0066] The flow loss thickness δ1 is defined as:

[0067] δ1=∫0 δ (1-ρV / ρ0U)dy

[0068] The momentum loss thickness δ2 is defined as follows:

[0069]

[0070] In the formula, δ is the local boundary layer thickness, which is taken as the normal distance to the vertical blade surface when the local velocity is 0.99 times the mainstream velocity; ρ0,U is the density and velocity of the fluid on the mainstream section; ρ,V is the actual density and velocity distribution of the fluid in the boundary layer; and y is the local surface normal of the blade.

[0071] See Figure 5 Smaller H 12 The effect of the value on the velocity profile within the boundary layer (left) relative to a larger H 12 The effect of H value on the velocity profile within the boundary layer (right). 12 The smaller the boundary layer, the more convex or fuller the velocity distribution within it.

[0072] In one embodiment, step S103 includes: when the shape factor value before the sudden increase in the shape factor distribution is greater than a preset threshold, without changing the inlet construction angle, outlet construction angle and the boundary of the arc shape in the front and rear sections of the blade, changing the ratio of the arc bend angle in the front half of the blade to the total bend angle until the shape factor value is less than or equal to the preset threshold.

[0073] Regarding sudden increases in shape factor, relevant techniques can be used for judgment. For example, if the growth rate of the shape factor between two consecutive points is greater than a growth rate threshold, then a sudden increase in the shape factor is judged. The growth rate threshold is set according to requirements, for example, 0.5.

[0074] Taking a preset threshold of 2.7 as an example, the shape factor value is determined before the small circle at the trailing edge of the suction surface of the blade (before the sudden increase in shape factor). If the shape factor is ≤2.7, the design optimization is completed, and the blade coordinates are output. A typical shape factor distribution diagram of a blade that meets the design requirements is shown below. Figure 6 As shown. A typical shape factor distribution diagram for blade types that do not meet design requirements is shown below. (If the shape factor > 2.7, it is not acceptable.) Figure 7 As shown), further adjustments to the blade curvature are made, and then proceed as follows: Figure 3 The iterative optimization process of reshaping the airfoil and calculating the S1 flow surface continues until the shape factor is ≤2.7, at which point the iteration ends and the required airfoil coordinates are output. The reshaping of the airfoil does not change the inlet and outlet construction angles β. A and β B Without changing the boundary between the front and rear arc shapes |AS| / |AB|, only the ratio of the arc angle in the front half to the total arc angle, Q=Δβ, is changed. AS / Δβ AB The specific iterative formula is: Q i+1 =Q i +n*Q, where the superscript i is the iteration number identifier and n is the relaxation factor, which is 0.001.

[0075] See Figure 8 A compressor low Reynolds number blade optimization device, comprising:

[0076] The shaping module 801 is used to shape the leaf shape to obtain the desired leaf shape.

[0077] Calculation module 802 is used to perform flow surface calculations on the blade shape to obtain the shape factor distribution of the blade surface disturbance;

[0078] The optimization module 803 is used to adjust the curvature distribution of the leaf shape when the shape factor value before the sudden increase in the shape factor in the shape factor distribution is greater than a preset threshold, until the shape factor value is less than or equal to the preset threshold.

[0079] In one embodiment, the device includes an output module for outputting the coordinates of the blade shape.

[0080] In one embodiment, the shaping module 801, used to shape the leaf shape to obtain the desired leaf shape, specifically performs the following:

[0081] Obtain the segmentation parameters and construction angle parameters of the middle arc. The segmentation parameters of the middle arc include the axial position of the dividing point of the middle arc between the front and rear segments and the proportion of the bending angle of the front segment. The construction angle parameters include the inlet construction angle and the outlet construction angle.

[0082] Under the constraint of satisfying the first-order continuity of the mid-arc, the mid-arc is constructed according to the mid-arc segmentation parameters and construction angle parameters.

[0083] Obtain thickness control parameters, including leading edge thickness, trailing edge thickness, maximum thickness and its location;

[0084] The shape is generated based on the mid-curve and thickness control parameters.

[0085] In one embodiment, the calculation module 802, when performing flow surface calculations on the blade shape to obtain the shape factor distribution of the blade surface disturbance, specifically performs the following:

[0086] Within the S1 flow surface defined by the shape, high-altitude low Reynolds number inlet conditions are set;

[0087] Solve the Euler equation over the main region to obtain the Euler solution;

[0088] For the turbulent near-wall region close to the blade surface, the boundary layer equations are solved in a coupled manner to obtain the boundary layer solution;

[0089] Based on the Euler solution and the boundary layer solution, the stable flow field solution of the S1 flow surface is obtained;

[0090] Based on the steady flow field solution, the shape factor distribution of the turbulence on the blade surface is extracted.

[0091] In one embodiment, the optimization module 803 is used to adjust the curvature distribution of the leaf shape when the shape factor value before a sudden increase in the shape factor distribution is greater than a preset threshold, until the shape factor value is less than or equal to the preset threshold. Specifically, it is used to:

[0092] When the shape factor value before the sudden increase in the shape factor distribution is greater than the preset threshold, without changing the inlet construction angle, outlet construction angle and the boundary of the arc shape in the front and rear sections of the blade, the ratio of the arc bend angle in the front half of the blade to the total bend angle is changed until the shape factor value is less than or equal to the preset threshold.

[0093] In one embodiment, the preset threshold is 2.7.

[0094] An exemplary embodiment of this application also provides an electronic device, including: at least one processor; and a memory communicatively connected to the at least one processor. The memory stores a computer program executable by the at least one processor, which, when executed by the at least one processor, causes the electronic device to perform a method according to an embodiment of this application.

[0095] Exemplary embodiments of this application also provide a non-transitory computer-readable storage medium storing a computer program, wherein the computer program, when executed by a computer's processor, is used to cause the computer to perform a method according to an embodiment of this application.

[0096] refer to Figure 9 An exemplary embodiment of this application also provides a computer program product 900, including a computer program 901, wherein the computer program, when executed by a computer's processor, is used to cause the computer to perform a method according to an embodiment of this application.

[0097] refer to Figure 10 The present invention describes a structural block diagram of an electronic device 1000 that can serve as a server or client of this application, which is an example of a hardware device that can be applied to various aspects of this application. The electronic device is intended to represent various forms of digital electronic computer devices, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device can 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 application described and / or claimed herein.

[0098] Electronic device 1000 includes a computing unit 1001, which can perform various appropriate actions and processes according to a computer program stored in read-only memory (ROM) 1002 or a computer program loaded into random access memory (RAM) 1003 from storage unit 1008. The RAM 1003 may also store various programs and data required for device operation. The computing unit 1001, ROM 1002, and RAM 1003 are interconnected via bus 1004. Input / output (I / O) interface 1005 is also connected to bus 1004.

[0099] Multiple components in electronic device 1000 are connected to I / O interface 1005, including: input unit 1006, output unit 1007, storage unit 1008, and communication unit 1009. Input unit 1006 can be any type of device capable of inputting information to electronic device 1000. Input unit 1006 can receive input digital or character information and generate key signal inputs related to user settings and / or function control of electronic device. Output unit 1007 can be any type of device capable of presenting information and may include, but is not limited to, a display, speaker, video / audio output terminal, vibrator, and / or printer. Storage unit 1008 may include, but is not limited to, disk and optical disk. Communication unit 1009 allows electronic device 1000 to exchange information / data with other devices through computer networks such as the Internet and / or various telecommunications networks, and may include, but is not limited to, modems, network cards, infrared communication devices, wireless communication transceivers, and / or chipsets, such as Bluetooth™ devices, WiFi devices, WiMax devices, cellular communication devices, and / or the like.

[0100] The computing unit 1001 can be various general-purpose and / or special-purpose processing components with processing and computing capabilities. Some examples of the computing unit 1001 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various special-purpose artificial intelligence (AI) computing chips, various computing units running machine learning model algorithms, a digital signal processor (DSP), and any suitable processor, controller, microcontroller, etc. The computing unit 1001 performs the various methods and processes described above. For example, in some embodiments, the methods of the embodiments of this application can be implemented as a computer software program, which is tangibly contained in a machine-readable medium, such as storage unit 1008. In some embodiments, part or all of the computer program can be loaded and / or installed on the electronic device 1000 via ROM 1002 and / or communication unit 1009. In some embodiments, the computing unit 1001 can be configured to perform the methods of the embodiments of this application by any other suitable means (e.g., by means of firmware).

[0101] The basic principles of this application have been described above with reference to specific embodiments. However, it should be noted that the advantages, benefits, and effects mentioned in this application are merely examples and not limitations, and should not be considered as essential features of each embodiment of this application. Furthermore, the specific details disclosed above are for illustrative and facilitative purposes only, and are not limitations. These details do not limit the application to the necessity of employing the aforementioned specific details for implementation.

[0102] The block diagrams of devices, apparatuses, devices, and systems involved in this application are merely illustrative examples and are not intended to require or imply that they must be connected, arranged, or configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, devices, and systems can be connected, arranged, and configured in any manner. Words such as “comprising,” “including,” “having,” etc., are open-ended terms meaning “including but not limited to,” and are used interchangeably with them. The terms “or” and “and” as used herein refer to the terms “and / or,” and are used interchangeably with them unless the context clearly indicates otherwise. The term “such as” as used herein refers to the phrase “such as but not limited to,” and is used interchangeably with it.

[0103] Additionally, as used herein, the “or” used in a list of items beginning with “at least one” indicates a separate list, such that a list of, for example, “at least one of A, B, or C” means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word “exemplary” does not imply that the described example is preferred or better than other examples.

[0104] It should also be noted that in the system and method of this application, the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered as equivalent solutions of this application.

[0105] Various changes, substitutions, and modifications can be made to the technology herein without departing from the teachings defined by the appended claims. Furthermore, the scope of the claims is not limited to the specific aspects of the processes, machines, manufactures, events, means, methods, and actions described above. Currently existing or later-developed processes, machines, manufactures, events, means, methods, or actions that perform substantially the same function or achieve substantially the same result as the corresponding aspects herein can be utilized. Therefore, the appended claims include such processes, machines, manufactures, events, means, methods, or actions within their scope.

[0106] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use this application. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein can be applied to other aspects without departing from the scope of this application. Therefore, this application is not intended to be limited to the aspects shown herein, but rather to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0107] The above description has been given for purposes of illustration and description. Furthermore, this description is not intended to limit the embodiments of this application to the forms disclosed herein. Although numerous exemplary aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.

Claims

1. A method of low Reynolds number profile optimization for a compressor, characterized in that, include: The leaf shape is shaped to obtain the desired leaf shape; Perform flow surface calculations on the aforementioned design to obtain the shape factor distribution of the blade surface turbulence; If the shape factor value before the sudden increase in the shape factor distribution is greater than a preset threshold, the curvature distribution of the leaf shape is adjusted until the shape factor value is less than or equal to the preset threshold.

2. The method of claim 1, wherein, After adjusting the curvature distribution of the leaf shape until the shape factor value is less than or equal to a preset threshold, the method further includes: Output the coordinates of the blade shape.

3. The method of claim 1, wherein, The process of shaping the leaf to obtain the desired leaf shape includes: Obtain the segmentation parameters and construction angle parameters of the middle arc. The segmentation parameters of the middle arc include the axial position of the dividing point of the front and rear middle arcs and the proportion of the bending angle of the front segment. The construction angle parameters include the inlet construction angle and the outlet construction angle. Under the constraint of satisfying the first-order continuity of the middle arc, the middle arc is constructed according to the middle arc segmentation parameters and the construction angle parameters; Obtain thickness control parameters, including leading edge thickness, trailing edge thickness, maximum thickness and its location; The shape is generated based on the mid-arc line and the thickness control parameters.

4. The method of claim 1, wherein, The step of performing flow surface calculations on the blade design to obtain the shape factor distribution of the blade surface disturbance includes: Within the S1 flow surface defined by the aforementioned shape, a high-altitude low Reynolds number inlet condition is established; Solve the Euler equation over the main region to obtain the Euler solution; For the turbulent near-wall region close to the blade surface, the boundary layer equations are solved in a coupled manner to obtain the boundary layer solution; Based on the Euler solution and the boundary layer solution, the stable flow field solution of the S1 flow surface is obtained; Based on the stable flow field solution, the shape factor distribution of the perturbation on the blade surface is extracted.

5. The method of claim 1, wherein, When the shape factor value before a sudden increase in the shape factor distribution is greater than a preset threshold, adjusting the curvature distribution of the leaf shape until the shape factor value is less than or equal to the preset threshold includes: When the shape factor value before the sudden increase in the shape factor distribution is greater than the preset threshold, without changing the inlet construction angle, outlet construction angle and the boundary of the arc shape in the front and rear sections of the blade, the ratio of the arc bend angle in the front half of the blade to the total bend angle is changed until the shape factor value is less than or equal to the preset threshold.

6. The method of claim 1, wherein, The preset threshold is 2.

7.

7. A device for optimization of low Reynolds number blade profile of a compressor, characterized in that, include: The shaping module is used to shape the leaf shape to obtain the desired leaf shape. The calculation module is used to perform flow surface calculations on the design to obtain the shape factor distribution of the blade surface disturbance; An optimization module is used to adjust the curvature distribution of the leaf shape when the shape factor value before a sudden increase in the shape factor distribution is greater than a preset threshold, until the shape factor value is less than or equal to the preset threshold.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory, characterized in that, The processor executes a computer program to implement the steps of the method according to any one of claims 1 to 6.

9. A computer-readable storage medium having a computer program / instructions stored thereon, characterized in that, When the computer program / instructions are executed by the processor, they implement the steps of the method described in any one of claims 1 to 6.

10. A computer program product comprising computer programs / instructions, characterized in that, When the computer program / instructions are executed by the processor, they implement the steps of the method described in any one of claims 1 to 6.

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