Method and device for constructing thickness distribution of airfoil, airfoil and aero-engine

Abstract

The application discloses a kind of leaf type thickness distribution construction method, device, blade and aero-engine, leaf type thickness distribution includes that the front edge section of thickness distribution curve is oval arc, the second section of thickness distribution curve is concave circular arc, the third section of thickness distribution curve is convex circular arc and the trailing edge section of thickness distribution curve is circular arc, design parameter includes front edge length-width ratio e, front edge wedge angle, front edge thickness, maximum thickness, maximum thickness position and trailing edge thickness, the front edge section is tangent with the second section at front edge thickness position, the second section is tangent with the third section, and the third section is tangent with the trailing edge section.This method utilizes the geometric characteristics of concave circular arc to construct a segment of negative curvature thickness distribution law, realizes the deceleration of airflow in the first half of blade, controls wavefront Mach number, completes the controllable rotor blade thickness rapid construction of blade thickness growth rate on the basis of ensuring wedge angle, realizes the best aerodynamic performance under the condition of having enough structural strength stability.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular to a blade thickness distribution configuration method. In addition, the present application also relates to an apparatus comprising the blade thickness distribution configuration method, a blade and an aero-engine. BACKGROUND

[0002] The compressor is one of the core components of an aero-engine, and its performance largely determines the performance of the engine, while the blade design is the core content of the compressor design, which determines the performance of the compressor. The compressor blade design mainly includes three parts: the camber line design, the thickness design and the spatial position design of the blade center of gravity. The compressor blade needs to adapt to complex inlet conditions, guide and compress the airflow, and finally make the airflow flow out at a certain angle and speed at the outlet, requiring that the parameters of the gas do not change greatly during the entire flow process, and the gas needs to flow along the blade surface as much as possible. In addition, the conditions at the inlet and outlet of the compressor blade are constantly changing, and the change range is also very large, so the blade needs to adapt to the large range of change of the inlet and outlet conditions to achieve a good working state. In order to achieve this goal, the design of the camber line inlet and outlet is very critical, and the airflow needs to be finely guided and controlled at the inlet and outlet.

[0003] As shown in Figure 1 , a typical compressor blade is usually composed of a series of cross sections, as shown in Figure 2 , that is, the so-called blade profile, and one of the main configuration methods of the blade profile is to draw a series of circles along a curve, as shown in Figure 3 and Figure 4 , and the vertical lines of the curve are drawn through the centers of the series of circles, and the intersection points of the vertical lines and the circles form the upper and lower surfaces of the blade profile, and the curve is the so-called camber line, and the radius of the circle is the so-called thickness, and the change rule of the thickness from the inlet to the outlet is the so-called thickness distribution.

[0004] The existing rotor blade thickness distribution law mainly includes three types: thickness distribution represented by discrete points, such as C series and NACA65 series, the thickness design parameters of which are basically fixed and basically unadjustable, the available attack angle range of which is narrow, and the flow loss of the rotor inlet Mach number increases sharply after the critical point, which cannot meet the requirements of high Mach number compressors in efficiency and margin; the thickness distribution represented by a curve expressed by an analytical formula, such as the technical solution in the publication CN11545589A which adopts a cubic polynomial and a circular arc blade thickness, the thickness of which generally has only four conventional design parameters of leading edge thickness, trailing edge thickness, maximum thickness and maximum thickness position, and the adjustable amount is also small, which is difficult to meet the requirements of high-load compressors in efficiency and margin; and the thickness distribution in the technical solution in the publication CN112347579B which adopts a free curve form, the thickness distribution of which is usually expressed by a Bezier or B-spline curve, the design parameters of which are the control point coordinates of the Bezier or B-spline curve, and the design variables are too many, which consumes a large amount of time and calculation resources, greatly prolongs the design cycle and increases the research and development cost. SUMMARY

[0005] The application provides a blade thickness distribution construction method, device, blade and aero-engine, so as to solve the technical problems of few design variables and small adjustable amount or many design variables and long rotor blade design cycle and high research and development cost caused by high inlet Mach number of the compressor rotor blade in the prior art.

[0006] According to one aspect of the application, a blade thickness distribution construction method is provided, which is applied to a compressor rotor blade, the blade thickness distribution includes a leading edge section with an elliptical arc-shaped thickness distribution curve, a second section with a concave circular arc-shaped thickness distribution curve, a third section with a convex circular arc-shaped thickness distribution curve, and a trailing edge section with a circular arc-shaped thickness distribution curve, the design parameters include a leading edge aspect ratio e, a leading edge wedge angle θ, a leading edge thickness t le , a maximum thickness T m , a maximum thickness position x m , and a trailing edge thickness t te , the leading edge section and the second section are tangent at the leading edge thickness t le position, the second section and the third section are tangent, and the third section and the trailing edge section are tangent.

[0007] As a preferred mode, the leading edge aspect ratio e is valued in the range of 1-2; the leading edge thickness t le , the maximum thickness T m , and the trailing edge thickness t te are determined according to the strength and frequency evaluation results; the maximum thickness position x m is valued in the range of 0.5-0.65; and the leading edge wedge angle θ is valued in the range of 0-3°.

[0008] As a preferred mode, the method for constructing the thickness distribution of the airfoil profile comprises the following contents:

[0009] S1. Constructing the first segment of the leading edge ellipse, setting the first quadrant point of the ellipse as the leading edge point A with coordinates (0, 0), the long axis a of the ellipse coincides with the horizontal coordinate, and the ellipse passes through point B (x1, t le ), and the tangent line of the ellipse at point B makes an angle of 1 / 2 of the leading edge wedge angle θ with the horizontal coordinate;

[0010] S2. Constructing the second segment, making the concave circular arc BD with the center O2 (x c2 , T c2 ) and the radius R2, the starting point of the circular arc is B (x1, t le ), and the circular arc is tangent to the first segment of the ellipse at point B, and the ending point of the circular arc is D (x2, T2);

[0011] S3. Constructing the third segment, making the convex circular arc DCE with the center O3 (x m , T c3 ) and the radius R3, the starting point of the circular arc is D (x2, T2), and the circular arc is tangent to the circular arc BD at point D, and the ending point of the circular arc is E (x3, t te ), and the circular arc passes through point C (x m , T m ), and point C is located to the right of point D;

[0012] S4. Constructing the trailing edge segment, making a circular arc with the center O4 (x c4 , 0), point E (x3, t te ), and point F (1, 0), the starting point of the circular arc is E (x3, t te ), and the ending point is F (1, 0), and the circular arc is tangent to the circular arc DCE at point E, and the radius of the circular arc is R4.

[0013] As a preferred mode, the method for constructing the thickness distribution of the airfoil profile further comprises:

[0014] S5. Parameter input, determining the leading edge aspect ratio e, the leading edge wedge angle θ, the leading edge thickness t le , the maximum thickness T m , the position of the maximum thickness x m , and the trailing edge thickness t te , based on the flow field conditions and the strength requirements;

[0015] S6. Leading edge segment solving, deriving the ellipse parameters and determining the ellipse equation according to the conditions that point A (0, 0) is the leftmost quadrant point of the ellipse, the long axis a coincides with the horizontal coordinate, the tangent line of the ellipse at point B (x1, t le ) makes an angle of 1 / 2 of the leading edge wedge angle θ with the horizontal coordinate, and a / b = e;

[0016] S7. Trailing edge segment solving, setting ∠CO3E = β, and deriving the equation of the circular arc according to the relationship 1 - x3 = t te (1 - sin β) / cos β to solve x3, x c4 and R4;

[0017] S8. Third segment solution, using the geometric relationship of the tangent of the circular arc DCE and the tangent of the trailing edge circular arc, to solve R3, T c3 ;

[0018] S9. Second segment solution, using the relationship of B(x1, t le ) and θ / 2 tangent, to solve T c2 with x c2 and radius R2, and the length of the line segment O2O3 = R2+R3, to solve x c2 , T c2 and R2;

[0019] S10. Curve integration, splicing four segment curves according to the tangent condition to generate a complete dimensionless thickness distribution.

[0020] As a preferred mode, the blade profile thickness distribution construction method further comprises:

[0021] S11. Optimization design parameters, selecting appropriate variables to repeat steps S5-S10 through iteration to optimize the aerodynamic performance of the blade profile. As a preferred mode, the solving formula of step S8 is:

[0022] R3 = (x3 - x m ) / sin β

[0023] Tc3 = Tm - R3.

[0024] As a preferred mode, the solving formula of step S9 is:

[0025]

[0026] According to another aspect of the present application, there is also provided a blade profile thickness distribution construction device, comprising:

[0027] A computer readable storage medium for storing instructions executable by the processor;

[0028] A processor for executing the above-mentioned blade profile thickness distribution construction method.

[0029] According to another aspect of the present application, there is also provided a blade applying the above-mentioned blade profile thickness distribution construction method.

[0030] According to another aspect of the present application, there is also provided an aero-engine applying the above-mentioned blade.

[0031] The present application has the following beneficial effects:

[0032] The blade thickness of the present application is composed of four curves of the initial end leading edge ellipse, the second segment concave circular arc, the third segment convex circular arc and the trailing edge circular arc, compared with the prior art scheme taking the maximum thickness position as the division point, the division point of the second segment circular arc and the third segment circular arc of the present blade thickness distribution construction method is on the left side of the maximum thickness position, and the input parameters are only six variables of the leading edge length-width ratio, the leading edge wedge angle, the leading edge thickness, the maximum thickness, the maximum thickness distribution position and the trailing edge thickness, which are all key design parameters, and the superior blade design adjustment capability is realized through simple and efficient design parameter input, the present application proposes the leading edge wedge angle as the design parameter to control the thickness growth rate of the second part to realize the optimal aerodynamic performance under the condition of sufficient structural strength stability, the present blade thickness distribution construction method utilizes the geometric characteristics of the concave circular arc to construct a thickness distribution law of a negative curvature to realize the deceleration of the airflow in the first half of the blade, control the wavefront Mach number, complete the controllable rotor blade thickness rapid construction of the thickness growth rate on the basis of ensuring the wedge angle, realize the optimal aerodynamic performance under the condition of sufficient structural strength stability, and can be widely applied to the rotor blade, provide a certain thickness reference for the compressor rotor blade modeling under the high Mach number working condition, reduce the peak Mach number of the rotor suction surface and improve the efficiency.

[0033] In addition to the objects, features and advantages described above, the present application has other objects, features and advantages. The present application will be further described in detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0034] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application, illustrate the preferred embodiments of the application and assist in the explanation of the application. In the drawings:

[0035] Figure 1 is a schematic diagram of a typical compressor blade of the prior art;

[0036] Figure 2 is a schematic diagram of the blade profile section of the prior art;

[0037] Figure 3 is a schematic diagram of the blade profile construction method of the prior art Figure 1 ;

[0038] Figure 4 is a schematic diagram of the blade profile construction method of the prior art Figure 2 ;

[0039] Figure 5 is a schematic diagram of the blade profile thickness construction of the preferred embodiment of the present application;

[0040] Figure 6 is a schematic diagram of the blade thickness distribution of the preferred embodiment of the present application. DETAILED DESCRIPTION

[0041] The embodiments of the present application will be described in detail below with reference to the drawings, but the present application can be implemented in various ways as defined and covered by the following.

[0042] Figure 1 is a schematic diagram of a typical compressor blade of the prior art; Figure 2 is a schematic diagram of a blade profile section of the prior art; Figure 3 is a schematic diagram of a blade profile construction method of the prior art; Figure 4 is a schematic diagram of a blade profile construction method of the prior art Figure 2 ; Figure 5 is a schematic diagram of a blade profile thickness construction of a preferred embodiment of the present application; Figure 6 is a schematic diagram of a blade thickness distribution of a preferred embodiment of the present application.

[0043] With reference to the drawings, the present embodiment provides a blade profile thickness distribution construction method applied to a compressor rotor blade, the blade profile thickness distribution comprising a leading edge section with an elliptic arc-shaped thickness distribution curve, a second section with a concave circular arc-shaped thickness distribution curve, a third section with a convex circular arc-shaped thickness distribution curve, and a trailing edge section with a circular arc-shaped thickness distribution curve, the design parameters comprising a leading edge aspect ratio e, a leading edge wedge angle θ (i.e. the included angle of the tangent line at the intersection point of the leading edge section and the second section), a leading edge thickness t le , a maximum thickness T m , a maximum thickness position x m , and a trailing edge thickness t te , the leading edge section and the second section being tangent at the leading edge thickness t le position, the second section and the third section being tangent, and the third section and the trailing edge section being tangent.

[0044] It can be understood that the thickness distribution curve constructed by the present blade thickness distribution construction method is composed of four curves of the starting end leading edge ellipse, the second segment concave circular arc, the third segment convex circular arc and the trailing edge circular arc. Compared with the prior art scheme taking the maximum thickness position as the demarcation point, the demarcation point of the second segment circular arc and the third segment circular arc of the present blade thickness distribution construction method is on the left side of the maximum thickness position, and the input parameters are only six variables of the leading edge length-width ratio, the leading edge wedge angle, the leading edge thickness, the maximum thickness, the maximum thickness distribution position and the trailing edge thickness, which are all key design parameters. The present blade thickness distribution construction method realizes superior blade design adjustment capability through simple and efficient design parameter input. The present blade thickness distribution construction method proposes the leading edge wedge angle as a design parameter to control the thickness growth rate of the second part, so as to realize the best aerodynamic performance under the condition of sufficient structural strength stability. The present blade thickness distribution construction method uses the geometric characteristics of the concave circular arc to construct a thickness distribution law with negative curvature, realizes the deceleration of airflow in the first half of the blade, controls the wavefront Mach number, and completes the controllable thickness rapid construction of the rotor blade on the basis of ensuring the wedge angle, realizes the best aerodynamic performance under the condition of sufficient structural strength stability, and can be widely applied to rotor blades, provides a certain thickness reference for compressor rotor blade modeling under high Mach number working conditions, reduces the peak Mach number of the rotor suction surface, and improves the efficiency.

[0045] In some embodiments, the leading edge length-width ratio e determines the thickness growth rate of the leading edge, and is in the range of 1-2; the leading edge thickness t le , the maximum thickness T m , the trailing edge thickness t te is used to control the strength and stiffness of the blade, so that whether the value is appropriate is judged according to the strength and frequency evaluation results, and the value is determined; the maximum thickness position x m has a certain influence on the flow loss and margin of the blade, and is in the range of 0.5-0.65; the leading edge wedge angle θ controls the thickness growth rate of the first half of the blade, so as to realize the best aerodynamic performance under the condition of sufficient structural strength stability, and is in the range of 0-3°.

[0046] It should be understood that the thickness construction method of the present embodiment is based on the symmetric distribution of the mean camber line, that is, the thickness distribution on both sides of the mean camber line is consistent, so the coordinate relationship of the four circular arcs is analyzed according to the positional relationship of the drawings;

[0047] In some embodiments, the blade thickness distribution construction method includes the following contents:

[0048] S1. Constructing a leading edge ellipse segment, setting the first quadrant point of the ellipse as the leading edge point A, the coordinates of which are (0, 0), the long axis a of the ellipse coincides with the horizontal coordinate, the ellipse passes through point B (x1, t le ), and the angle between the tangent line of the ellipse at point B and the horizontal coordinate is 1 / 2 of the leading edge wedge angle θ;

[0049] S2. Constructing the second segment, making a concave circular arc BD with the center O2(x c2 , T c2 ) and radius R2, the starting point of the circular arc being B(x1, t le ) and tangent to the first segment ellipse at point B, and the ending point of the circular arc being D(x2, T2);

[0050] S3. Constructing the third segment, making a convex circular arc DCE with the center O3(x m , T c3 ) and radius R3, the starting point of the circular arc being D(x2, T2) and tangent to the circular arc BD at point D, and the ending point of the circular arc being E(x3, t te ), the circular arc passing through point C(x m , T m ), and point C being located to the right of point D;

[0051] S4. Constructing the trailing edge segment, making a circular arc with the center O4(x c4 , 0), point E(x3, t te ) and point F(1, 0), the starting point of the circular arc being E(x3, t te ) and the ending point being F(1, 0), and the circular arc being tangent to the circular arc DCE at point E, and the radius of the circular arc being R4;

[0052] It should be understood that the method realizes the deceleration of the airflow in the front half of the blade, controls the wavefront Mach number, and completes the controllable rotor blade thickness rapid construction of the blade thickness growth rate on the basis of ensuring the wedge angle by utilizing the geometric characteristics of the concave circular arc to construct a thickness distribution law of a negative curvature.

[0053] In some embodiments, the blade profile thickness distribution construction method further comprises:

[0054] S5. Parameter input, determining the leading edge aspect ratio e, the leading edge wedge angle θ, the leading edge thickness t le , the maximum thickness T m , the maximum thickness position x m , and the trailing edge thickness t te based on the flow field conditions and strength requirements;

[0055] Specifically, the leading edge aspect ratio e determines the thickness growth rate of the leading edge, and is valued in the range of 1-2; the leading edge thickness t le , the maximum thickness T m , and the trailing edge thickness t te are used to control the strength and stiffness of the blade, so the values are determined according to whether the strength and frequency evaluation results are appropriate; and the maximum thickness position x mThe flow loss and margin of the blade profile are affected to a certain extent, and the value is taken in the range of 0.5 to 0.65. The leading edge wedge angle θ controls the thickness growth rate of the front half of the blade to achieve the best aerodynamic performance under the condition of sufficient structural strength and stability, and the value is taken in the range of 0 to 3°.

[0056] S6. Solving for the leading edge segment: Given that point A(0, 0) is the leftmost quadrant point of the ellipse, the major axis a coincides with the x-coordinate, and the ellipse lies at B(x1, t... le Given the conditions that the angle between the tangent at point () and the x-coordinate is 1 / 2 of the leading edge wedge angle θ, and a / b = e, the ellipse parameters are derived, and the equation of the ellipse is determined.

[0057] Specifically, for the elliptical leading edge segment, using the aspect ratio e, b can be expressed as a function of a, simplifying the ellipse equation. Since point B lies on the ellipse, a can be expressed as a function of x1, further simplifying the ellipse equation; the angle between the tangent at point B and the horizontal axis is θ / 2. Differentiating the ellipse equation and using the relationship between the derivative and the tangent, x1 can be expressed as a function of θ. Therefore, the ellipse equation for the leading edge segment can be derived from θ, e, and t. le The values ​​represent input values, and the solution is obtained based on the equation of the preceding edge ellipse.

[0058] S7. Solving for the trailing edge segment: Let ∠CO3E = β, according to the relation... 1-x3=t te Solve for x3 using (1-sinβ) / cosβ. c4 and R4;

[0059] Specifically, let ∠CO3E = β, then the angle between CE and the x-coordinate is β / 2. From trigonometric relationships, we know 1 - x³ = t te (1-sinβ) / cosβ, Solving the system of equations simultaneously yields β and x3, R4 = t. te / cosβ,x c4 =1-t te / cosβ, based on this fourth arc segment, the solution is obtained;

[0060] S8. The third step involves solving for R3 and T using the geometric relationships of the tangency of the circular arcs DCE and the tangency of the trailing edge arcs. c3 ;

[0061] Specifically, according to the relation R3 = (x3 - x m ) / sinβ、T c3 =T m -R3 solves for R3 and T c3 ;

[0062] S9. Solving the second section, using B(x1, t) le The relationship between tangency and θ / 2 is expressed in x.c2 represents T c2 and the length of the line segment O2O3 = R2+R3, solve x c2 , T c2 and R2;

[0063] Specifically, according to the relationship Solve x c2 , T c2 and R2;

[0064] S10. Curve integration, four curve segments are spliced according to the tangent condition to generate a complete dimensionless thickness distribution; through repeated iteration, appropriate variables can be selected to complete the thickness design of the blade under the condition of fixed wedge angle.

[0065] Further, the blade thickness distribution construction method further comprises:

[0066] S11. Optimize the design parameters, select appropriate variables and repeat steps S5-S10 to optimize the aerodynamic performance of the blade through iteration.

[0067] It should be understood that, according to Figure 6 The thickness distribution obtained by the present construction method and the existing design method is compared, wherein the abscissa is the relative chord length and the ordinate is the dimensionless thickness. The present blade thickness distribution construction method proposes to take the leading edge wedge angle as a design parameter to control the thickness growth rate of the second part, so as to achieve the best aerodynamic performance under the condition of sufficient structural strength stability, and the input parameters are only six variables, i.e. the leading edge aspect ratio, the leading edge wedge angle, the leading edge thickness, the maximum thickness, the maximum thickness distribution position and the trailing edge thickness, all of which are key design parameters. The superior blade design adjustment capability is achieved through simple and efficient design parameter input. The analytical method is used as the numerical solution method of the present blade thickness construction method, which is convenient, fast, simple and effective. The present blade thickness distribution construction method utilizes the geometric characteristics of concave circular arcs to construct a segment of negative curvature thickness distribution law, to realize the deceleration of airflow in the first half of the blade, control the wavefront Mach number, complete the controllable rotor blade thickness rapid construction of the thickness growth rate on the basis of ensuring the wedge angle, and achieve the best aerodynamic performance under the condition of sufficient structural strength stability. It can be widely applied to rotor blades and provides a certain thickness reference for compressor rotor blade modeling under high Mach number working conditions, while reducing the peak Mach number of the rotor suction surface and improving the efficiency. Compared with the method of controlling the thickness values of other positions of the blade through control points on the basis of ensuring the maximum thickness conversion value based on the maximum thickness position and its thickness conversion value, the present method has more accurate design feature control;

[0068] In another aspect, the preferred embodiment of the present application also provides a profile construction device of the airfoil thickness distribution, which can be a computer, a server, a smart mobile device, a virtual reality device, an augmented reality device, etc. The profile construction device of the preferred embodiment of the present application can include:

[0069] a computer readable storage medium for storing instructions executable by the processor; the computer readable storage medium can store computer readable instructions and / or data, and can include a memory and a storage;

[0070] a processor for executing the profile construction method of the airfoil thickness distribution; the processor can execute the instructions stored in the computer readable storage medium to implement the foregoing method; in some embodiments, the processor can include at least one hardware processor, such as a microcontroller, a microprocessor, a reduced instruction set computer (RISC), an application specific integrated circuit (ASIC), an application specific instruction set processor (ASIP), a central processing unit (CPU), a graphics processing unit (GPU), a physics processing unit (PPU), a single chip microcomputer, a digital signal processor (DSP), a field programmable gate array (FPGA), an advanced reduced instruction set computer (ARM), a programmable logic device (PLD), any circuit or processor capable of performing at least one function, or any combination thereof.

[0071] In another aspect, the preferred embodiment of the present application also provides a blade applying the profile construction method of the airfoil thickness distribution.

[0072] In another aspect, the preferred embodiment of the present application also provides an aero-engine applying the blade.

[0073] In the description of the present application, it should be noted that the terms "upper", "lower", "front", "back", etc. indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0074] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixedly connected, or detachably connected, or integrally connected; it can be mechanically connected, or electrically connected; it can be directly connected, or indirectly connected through an intermediate medium, or it can be the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0075] The above merely provides the preferred embodiments of the present application, and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the principles and technical scope of the present application shall fall into the scope of the present application.

Claims

1. A method of constructing a profile thickness distribution for an impeller blade of a compressor rotor, characterized by, The thickness distribution of the airfoil profile comprises a leading edge section with an elliptic arc-shaped thickness distribution curve, a second section with a concave circular arc-shaped thickness distribution curve, a third section with a convex circular arc-shaped thickness distribution curve, and a trailing edge section with a circular arc-shaped thickness distribution curve, and the design parameters comprise a leading edge aspect ratio e, a leading edge wedge angle θ, a leading edge thickness t le , a maximum thickness T m , a maximum thickness position x m , and a trailing edge thickness t te The leading edge section is tangent to the second section at the leading edge thickness t le , the second section is tangent to the third section, and the third section is tangent to the trailing edge section; the leading edge aspect ratio e is in the range of 1-2; the leading edge thickness t le , the maximum thickness T m , and the trailing edge thickness t te are determined according to the strength and frequency evaluation results; the maximum thickness position x m is in the range of 0.5-0.65; the leading edge wedge angle θ is in the range of 0-3°; and the thickness distribution construction method of the airfoil profile comprises the following contents: S1. Constructing a front edge ellipse segment, setting the first quadrant point of the ellipse as the front edge point A, the coordinate of which is (0, 0), the long axis a of the ellipse coincides with the horizontal coordinate, the ellipse passes through point B (x1, t le ), and the included angle between the tangent line of the ellipse at point B and the horizontal coordinate is 1 / 2 of the front edge wedge angle θ; S2. Constructing the second segment, making a concave circular arc BD with the center O2(x c2 , T c2 ) and the radius R2, the starting point of the circular arc is B(x1, t le ), and the circular arc is tangent to the first segment at point B, and the ending point of the circular arc is D(x2, T2); S3. Construct the third segment, which is a convex circular arc DCE with center O3(x m , T c3 ) and radius R3. The starting point of the arc is D(x2, T2), and the arc is tangent to BD at point D. The ending point of the arc is E(x3, T te ), and the arc passes through point C(x m , T m ), which is located to the right of point D. S4. Construct the trailing edge segment, make a circular arc through the center O4(x c4 , 0), point E(x3, t te ), and point F(1, 0), with the starting point at E(x3, t te ) and the end point at F(1, 0), and with the point E tangent to the circular arc DCE, with a radius of R4.

2. The profile construction method of claim 1, wherein The method further comprises: S5. Parameter input, determine the leading edge aspect ratio e, the leading edge wedge angle θ, the leading edge thickness t based on the flow field conditions and the intensity requirement le , the maximum thickness T m , the maximum thickness position x m , and the trailing edge thickness t te ; S6. The front edge segment is solved, according to the point A (0, 0) as the leftmost quadrant point of the ellipse, the long axis a coincides with the horizontal coordinate, the tangent of the ellipse at B (X1, t le ) is 1 / 2 of the front edge wedge angle θ, and a / b = e, the ellipse parameters are derived to determine the ellipse equation; S7. The trailing edge segment is solved for, setting ∠CO3E = β, according to the relationship 1 - x3= t te (1 - sin β) / cos β to solve for x3, x c4 and R4; S8. The third paragraph is solved, using the geometric relationship of the tangent of the circular arc DCE and the tangent of the trailing edge circular arc, to solve R3, T c3 ; S9. Second segment solution, using B(x1, t le ) and the tangent of θ / 2, express T c2 in terms of x c2 , R2, and the length of segment O2O3 = R2+R3, solve for x c2 , T c2 , and R2; S10. Curve integration, connecting four curves according to the tangent condition to generate a complete dimensionless thickness distribution.

3. The profile construction method of claim 2, wherein The method further comprises: S11. Optimizing design parameters, selecting appropriate variables to repeat steps S5-S10 through iteration to optimize the aerodynamic performance of the blade profile.

4. The profile construction method of claim 2, wherein The solving formula of step S8 is: R3 = (x3 - x m ) / sinβ T c3 = T m - R3.

5. The profile construction method of claim 2, wherein The solving formula of step S9 is:

6. An airfoil thickness distribution configuration device characterized by comprising: The method comprises: A computer readable storage medium for storing instructions executable by a processor; A processor for executing the blade profile thickness distribution construction method according to any one of claims 1-5.

7. A blade, characterized in that The application has the blade profile thickness distribution construction method according to any one of claims 1-5.

8. An aeroengine characterised in that, The application has the blade according to claim 7.

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