Blade thickness distribution construction methods, construction devices, blades and aero engines

Abstract

This invention discloses a method, apparatus, blade, and aero-engine for constructing blade thickness distribution. The blade thickness distribution includes a leading edge segment with an elliptical thickness distribution curve, a second segment with a convex circular thickness distribution curve, a third segment with a concave circular thickness distribution curve, and a trailing edge segment with a circular arc shape. Design parameters include leading edge aspect ratio, leading edge thickness, maximum thickness, maximum thickness position / trailing edge thickness, and trailing edge wedge angle. The leading edge segment and the second segment are tangent at the leading edge thickness position, the second segment and the third segment are tangent, and the third segment and the trailing edge segment are tangent. Superior blade design adjustment capabilities are achieved through simple and efficient design parameter input. The trailing edge wedge angle is proposed as a design parameter to control the thickness growth rate of the third part, achieving optimal aerodynamic performance. The geometric characteristics of the concave circular arc are used to construct a rapidly contracting thickness distribution pattern, enabling controllable diffusion of airflow in the trailing half of the blade and achieving a low margin loss effect.

Description

Technical Field

[0001] This invention relates to the field of blade design technology, and in particular, to a method for constructing blade thickness distribution. Furthermore, this invention also relates to a design method incorporating the above-described blade thickness distribution construction method, and to an aero-engine. Background Technology

[0002] The compressor is one of the core components of an aero-engine, and its performance largely determines the engine's performance. Blade design is the core of compressor design, determining its performance. Compressor blade design mainly consists of three parts: the mid-curvature design, thickness design, and the spatial position design of the blade's center of gravity. Compressor blades need to adapt to complex inlet conditions, guiding and compressing the airflow, ultimately ensuring the airflow exits at a specific angle and velocity. This requires that the gas parameters not undergo significant abrupt changes throughout the flow process, and that the gas flow should follow the blade surface as closely as possible. Furthermore, the inlet and outlet conditions of the compressor blades are constantly changing, with a very wide range of variation. The blades need to adapt to these diverse inlet and outlet conditions to achieve optimal operating conditions. To achieve this goal, the design of the mid-curvature inlet and outlet is crucial, requiring precise guidance and control of the airflow at both the inlet and outlet.

[0003] Typical compressor blades, such as Figure 1 As shown, it typically consists of a series of cross sections, see reference. Figure 2 This refers to the so-called leaf shape, and one of the main methods for constructing a leaf shape is to draw a series of circles along a curve. (See reference...) Figure 3 and Figure 4 A perpendicular line is drawn from the center of a series of circles to the curve. The intersection of the perpendicular line and the circle forms the upper and lower surfaces of the leaf shape. This curve is called the middle arc line, the radius of the circle is called the thickness, and the variation of the thickness from the inlet to the outlet is called the thickness distribution.

[0004] Existing stator blade thickness distribution patterns can be mainly divided into three categories: Thickness distribution represented by discrete points, such as the C series and NACA65 series. The design parameters for this type of thickness are basically fixed and not adjustable, resulting in a narrow usable angle of attack range. After the stator inlet Mach number exceeds the critical value, flow losses increase sharply, making it impossible to meet the efficiency and margin requirements of high-load compressors. Thickness distribution represented by curves with multiple segments, expressed by analytical formulas, such as in publication number CN11545589A. The technical solutions employ cubic polynomial and circular arc blade thickness. These thicknesses typically have only four conventional design parameters: leading edge thickness, trailing edge thickness, maximum thickness, and maximum thickness position. The adjustable range is also relatively small, making it difficult to meet the efficiency and margin requirements of high-load compressors. Another example is the technical solution in publication number CN112347579B, which uses a free curve form of thickness distribution. This type of thickness distribution is usually represented by Bezier or B-spline curves. The design parameters are the coordinates of the control points of the Bezier or B-spline curves. There are too many design variables, which consumes a lot of time and computational resources, significantly prolongs the design cycle, and increases the R&D cost. Summary of the Invention

[0005] This invention provides a method, apparatus, blade, and aero-engine for constructing blade thickness distribution, in order to solve the technical problems in the prior art where the conditions at the inlet and outlet of compressor blades vary greatly, and the existing thickness distribution design methods have few design variables, resulting in small adjustment amounts or many design variables, resulting in long design cycles and high R&D costs.

[0006] According to one aspect of the present invention, a method for constructing a blade thickness distribution is provided, applied to a compressor stator blade. The blade thickness distribution includes a leading edge segment with an elliptical thickness distribution curve, a second segment with a convex circular thickness distribution curve, a third segment with a concave circular thickness distribution curve, and a trailing edge segment with a circular thickness distribution curve. The design parameters include the leading edge aspect ratio e and the leading edge thickness. Maximum thickness Location of maximum thickness and trailing edge thickness and tail edge wedge angle The leading edge segment and the second segment differ in leading edge thickness. The two segments are tangent to each other; the second segment is tangent to the third segment, and the third segment is tangent to the tail edge segment.

[0007] As a further improvement to the above technical solution, the leading edge thickness Maximum thickness Trailing edge thickness The value is determined based on the intensity and frequency assessment results.

[0008] As a further improvement to the above technical solution, the aspect ratio e of the leading edge is taken in the range of 1-2; the location of maximum thickness. The value is taken in the range of 0.25 to 0.35, and the tail edge wedge angle is... Values ​​are taken in the range of 0 to 3°.

[0009] As a further improvement to the above technical solution, the method for constructing the blade thickness distribution includes the following:

[0010] S1. Construct the leading edge elliptical segment, setting the first quadrant point of the ellipse as the leading edge point A, with coordinates (0, 0). The major axis a of the ellipse coincides with the x-coordinate, and the ellipse passes through point B. );

[0011] S2. Construct the second segment, using O2 ( Draw a convex circular arc BCD with center R1 and radius R2, starting at point B. The endpoint is D ( ). ), and through the point of maximum thickness C ( Point D is located to the right of point C;

[0012] S3. Construct the third segment, using O3 ( Draw a concave circular arc DE with center at point D and radius R3, starting at point D. The endpoint is E ( The arc is tangent to the second segment's arc at point D, and tangent to the trailing edge segment's arc at point E.

[0013] S4. Construct the trailing edge segment, using O4 ( Draw an arc EF with center R4 and radius R4, starting at point E. The endpoint is F(1, 0), and it is tangent to the arc of the third segment at point E. The angle between the tangent at point E and the x-coordinate is... .

[0014] As a further improvement to the above technical solution, the method for constructing the blade thickness distribution further includes:

[0015] S5. Parameter Input: Determine the leading edge aspect ratio e and leading edge thickness based on flow field conditions and intensity requirements. Maximum thickness Location of maximum thickness and trailing edge thickness Tail edge wedge angle ;

[0016] S6. Solving the leading edge segment: Let the angle between the tangent at point B and the horizontal axis be ω. Based on the geometric relationship of the ellipse passing through the origin, major axis a, minor axis b, and the aspect ratio e, determine the relationship between x1 and ω.

[0017] S7. The second step involves solving using geometric relationships. Solve the system of equations with the relationship between x1 and ω determined by S6 to obtain parameters such as x1, ω, and a, and calculate the center of the circle. ) and radius R2, , ;

[0018] S8. Determine the trailing edge segment based on the trailing edge thickness. The radius R4 is determined by the cosine of the wedge angle θ. , and solve We obtain the coordinates of point E;

[0019] S9. Solving the third section, let... Then the coordinates of point D can be expressed as The function, The coordinates of points D and E, the length L, and the angle between DE and the horizontal axis are used to determine the coordinates of these points. Solve the simultaneous equations based on the trigonometric function relationships between them. By combining the geometric relationship between chord length and radius, the center of the third arc segment is determined. ) and radius R3, ;

[0020] S10. Curve integration: The four curve segments are spliced ​​together according to the tangency condition to generate a complete dimensionless thickness distribution.

[0021] As a further improvement to the above technical solution, the method for constructing the blade thickness distribution further includes:

[0022] S11. Optimize design parameters and select appropriate variables. Repeat steps S5-S10 to iterate and optimize the aerodynamic performance of the blade profile.

[0023] According to another aspect of the present invention, a blade thickness distribution structure device is also provided, comprising:

[0024] A computer-readable storage medium for storing instructions that can be executed by a processor;

[0025] A processor for executing any of the blade thickness distribution construction methods described above.

[0026] According to another aspect of the present invention, a blade is also provided, which applies any of the blade thickness distribution construction methods described above.

[0027] According to another aspect of the present invention, an aero-engine is also provided, which includes the above-described blade thickness distribution construction method.

[0028] The present invention has the following beneficial effects:

[0029] The blade thickness in this design consists of four curves: an elliptical leading edge, a second convex arc, a third concave arc, and a trailing edge arc. Compared to existing technologies that use the maximum thickness position as the dividing point, this blade thickness distribution method uses the dividing point between the second and third arcs to the right of the maximum thickness position. The input parameters for this blade thickness distribution method are only six variables: leading edge aspect ratio, leading edge thickness, maximum thickness, maximum thickness distribution position, trailing edge thickness, and trailing edge wedge angle. These are all key design parameters. It achieves superior blade design adjustment capabilities through simple and efficient design parameter input. It proposes using the trailing edge wedge angle as a design parameter to control the thickness growth rate of the third part to achieve optimal aerodynamic performance. This blade thickness distribution method utilizes the geometric characteristics of the concave arc to construct a rapidly contracting thickness distribution pattern, achieving controllable diffusion of airflow in the trailing half of the blade, ultimately achieving a low margin loss effect. It is suitable for stator blade designs at high Mach numbers.

[0030] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0031] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0032] Figure 1 This is a schematic diagram of a typical compressor blade in existing technology;

[0033] Figure 2 This is a schematic diagram of the cross-section of a blade in the prior art;

[0034] Figure 3 This is a schematic diagram of the existing blade construction method. Figure 1 ;

[0035] Figure 4 This is a schematic diagram of the existing blade construction method. Figure 2 ;

[0036] Figure 5 This is a schematic diagram of the blade thickness structure according to a preferred embodiment of the present invention;

[0037] Figure 6 This is a schematic diagram of the blade thickness distribution according to a preferred embodiment of the present invention. Detailed Implementation

[0038] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0039] Figure 1 This is a schematic diagram of a typical compressor blade in existing technology; Figure 2 This is a schematic diagram of the cross-section of a blade in the prior art; Figure 3 This is a schematic diagram of the existing blade construction method; Figure 4 This is a schematic diagram of the existing blade construction method. Figure 2 ; Figure 5 This is a schematic diagram of the blade thickness structure according to a preferred embodiment of the present invention; Figure 6 This is a schematic diagram of the blade thickness distribution according to a preferred embodiment of the present invention;

[0040] like Figures 4 to 6 As shown, the blade thickness distribution construction method of this embodiment is applied to compressor stator blades. The blade thickness distribution includes a leading edge segment with an elliptical thickness distribution curve, a second segment with a convex circular thickness distribution curve, a third segment with a concave circular thickness distribution curve, and a trailing edge segment with a circular thickness distribution curve. The design parameters include the leading edge aspect ratio e and the leading edge thickness. Maximum thickness Location of maximum thickness and trailing edge thickness Tail edge wedge angle (That is, the angle between the tangent line of the third segment and the tangent point of the trailing edge), the leading edge segment and the second segment have different leading edge thicknesses. The two segments are tangent to each other; the second segment is tangent to the third segment, and the third segment is tangent to the tail edge segment.

[0041] Understandably, the thickness distribution curve constructed by this blade thickness distribution construction method consists of four segments: an ellipse at the leading edge, a second convex arc, a third concave arc, and a trailing edge arc. Compared to existing technologies that use the maximum thickness position as the dividing point, the dividing point between the second and third arcs in this blade thickness distribution construction method is to the right of the maximum thickness position. The input parameters for this blade thickness distribution construction method are only six variables: leading edge aspect ratio, leading edge thickness, maximum thickness, maximum thickness distribution position, trailing edge thickness, and trailing edge wedge angle. These are all key design parameters. It achieves superior blade design adjustment capabilities through simple and efficient design parameter input. It proposes using the trailing edge wedge angle as a design parameter to control the thickness growth rate of the third part to achieve optimal aerodynamic performance. This blade thickness distribution construction method utilizes the geometric characteristics of the concave arc to construct a rapidly contracting thickness distribution pattern, achieving controllable diffusion of airflow in the rear half of the blade, ultimately achieving a low margin loss effect, and is suitable for stator blade designs under high Mach number conditions.

[0042] Furthermore, leading edge thickness Maximum thickness Trailing edge thickness Used to control the strength and stiffness of the blades, the appropriateness of the values ​​is determined based on the strength and frequency evaluation results.

[0043] Furthermore, the aspect ratio e of the leading edge determines the thickness growth rate of the leading edge, which ranges from 1 to 2; the location of the maximum thickness... It has a certain impact on the flow loss and margin of the blade profile, and has been verified to be taken in the range of 0.25~0.35; the trailing edge wedge angle θ controls the thickness growth rate of the rear half of the blade to achieve the best aerodynamic performance, and is taken in the range of 0~3°.

[0044] It should be understood that the thickness distribution of the blade is symmetrical from top to bottom, and the thickness distribution curve of the upper or lower half should be analyzed.

[0045] In this embodiment, the method for constructing the blade thickness distribution includes the following:

[0046] S1. Construct the leading edge elliptical segment, setting the first quadrant point of the ellipse as the leading edge point A, with coordinates (0, 0). The major axis a of the ellipse coincides with the x-coordinate, and the ellipse passes through point B. );

[0047] S2. Construct the second segment, using O2 ( Draw a convex circular arc BCD with center R1 and radius R2, starting at point B. The endpoint is D ( ). ), and through the point of maximum thickness C ( Point D is located to the right of point C;

[0048] S3. Construct the third segment, using O3 ( Draw a concave circular arc DE with center at point D and radius R3, starting at point D. The endpoint is E ( The arc is tangent to the second segment's arc at point D, and tangent to the trailing edge segment's arc at point E.

[0049] S4. Construct the trailing edge segment, using O4 ( Draw an arc EF with center R4 and radius R4, starting at point E. The endpoint is F(1, 0), and it is tangent to the arc of the third segment at point E. The angle between the tangent at point E and the x-coordinate is... .

[0050] It should be understood that by constructing the leading edge elliptical segment, the second segment, the third segment, and the trailing edge segment, the geometric characteristics of the concave circular arc are used to construct a rapidly contracting thickness distribution pattern, thereby achieving controllable diffusion of airflow in the rear half of the blade. Subsequently, the design can be completed quickly through parameter input, resulting in a short design cycle, high efficiency, and low cost.

[0051] In this embodiment, the method for constructing the blade thickness distribution further includes:

[0052] S5. Parameter Input: Determine the leading edge aspect ratio e and leading edge thickness based on flow field conditions and intensity requirements. Maximum thickness Location of maximum thickness and trailing edge thickness Tail edge wedge angle ;

[0053] Specifically, leading edge thickness Maximum thickness Trailing edge thickness Used to control the strength and stiffness of the blade, the appropriateness of the value is determined based on the strength and frequency evaluation results; the leading edge aspect ratio 'e' determines the leading edge thickness growth rate, which is within the range of 1-2; the location of maximum thickness... The flow loss and margin of the blade profile have a certain impact, and the value is verified to be in the range of 0.25~0.35; the trailing edge wedge angle θ controls the thickness growth rate of the rear half of the blade to achieve the best aerodynamic performance, and the value is in the range of 0~3°.

[0054] S6. Solving the leading edge segment: Let the angle between the tangent at point B and the horizontal axis be ω. Based on the geometric relationship of the ellipse passing through the origin, major axis a, minor axis b, and the aspect ratio e, determine the relationship between x1 and ω.

[0055] Specifically, for the leading edge segment / elliptical 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. Let ω be the angle between the tangent at point B and the horizontal axis. Differentiating the ellipse equation, using the relationship between the derivative and the tangent, x1 can be expressed as a function of ω. Thus, the only unknown in the ellipse equation is ω, while the other parameters e, ... Input values ​​for the design;

[0056] S7. The second step involves solving the problem using geometric relationships. Solve the system of equations with the relationship between x1 and ω determined by S6 to obtain parameters such as x1, ω, and a, and calculate the center of the circle. ) and radius R2, , ;

[0057] Specifically, it can be known from geometric relationships that The angle between CB and the x-axis is From the trigonometric function relationship, we know By solving the system of equations with the relationship between x1 and ω determined in S6, we can obtain the parameters x1, ω, and a. The curve of the first segment of the ellipse is now determined. From trigonometric relationships, we can obtain... , At this point, the radius and center of the second curve segment have been determined.

[0058] S8. Determine the trailing edge segment based on the trailing edge thickness. The radius R4 is determined by the cosine of the wedge angle θ. , and solve We obtain the coordinates of point E;

[0059] Specifically, as can be seen from the definition of the trailing edge wedge angle... , , The value can also be determined by the radius of the fourth arc. caudal wedge angle The relational expression allows us to determine the coordinates of point E.

[0060] S9. Solving the third section, let... Then the coordinates of point D can be expressed as The function, The coordinates of points D and E, the length L, and the angle between DE and the horizontal axis are used to determine the coordinates of these points. Solve the simultaneous equations based on the trigonometric function relationships between them. By combining the geometric relationship between chord length and radius, the center of the third arc segment is determined. ) and radius R3, ;

[0061] Specifically, in the second arc, the intersection point D of the arc ends Assume that the angle between the radius of the line connecting it to the center of the circle and the numerical direction is... According to geometric relationships, its value is equal to the exit tangential angle of the second arc segment, and the x-coordinate of its exit point is... This can be represented as the coordinates of the center of the second segment of the circle. Add the radius of the second arc Multiply by the included angle The sine value, whose ordinate is the sum of the ordinate of the center of the second circle and the radius of the second arc. Multiply by the included angle From the cosine value of the cosine, we can obtain two related formulas;

[0062] Specifically, in the third arc, the chord length of line segment DE is... According to D and E The length can be determined by the coordinates of two points. This is the third equation. Draw a perpendicular line from the center of the third arc to line segment DE. From the right triangle and the geometric relationship shown in the diagram, we know that the acute angle formed by the centers is one-half of the included angle. Subtract wedge angle Then the third arc It will be equal to half the length of the chord of line segment DE divided by the sine of that angle; this is the fourth equation.

[0063] It should be understood that the coordinates of the center of the third arc... Equal to its E coordinate Add radius of arc Multiplying the wedge angle The sine value, the coordinates of the center of the third arc. equal to coordinates Add radius of arc Multiplying the wedge angle The cosine value, this is the fifth and sixth equations; among them, the tail edge wedge angle Given a quantity, the included angle It can be derived from the center of the third arc and D The coordinate relationship is determined; this is the seventh equation. Solving the above seven equations simultaneously yields the solution. , , , , , , Seven variables; at this point, all the analytical expressions for the curves have been determined, and the dimensionless thickness distribution of the blades can be solved.

[0064] S10. Curve integration: The four curve segments are spliced ​​together according to the tangency condition to generate a complete dimensionless thickness distribution.

[0065] Furthermore, the method for constructing the blade thickness distribution also includes:

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

[0067] Through repeated iterations, appropriate variables can be selected to complete the blade thickness design while keeping the wedge angle fixed.

[0068] This blade thickness distribution construction method possesses excellent blade design adjustment capabilities and simple, efficient design parameter input. It provides blade shapes with controllable blade thickness growth rate, achieving a controllable diffusion blade thickness distribution. It also controls the wedge angle formed by the trailing edge tangent to adapt to the shape required by shock waves and controls the leading edge thickness to meet the required leading edge thickness. The resulting blade thickness distribution achieves both a continuous, smooth, and abrupt blade surface and a controllable thickness growth rate through concave-convex circular arc thickness distribution, making it suitable for stator blade designs at high Mach numbers. This design method utilizes the geometric characteristics of concave circular arcs to construct a rapidly contracting thickness distribution pattern, achieving controllable diffusion of airflow in the trailing half of the blade. It proposes the trailing edge wedge angle as a design parameter to control the blade thickness growth rate to achieve optimal aerodynamic performance, ultimately achieving the effects of widening the margin and reducing low losses, making it suitable for stator blade designs at high Mach numbers.

[0069] On the other hand, a preferred embodiment of the present invention also provides a blade thickness distribution structure device, which can be from a computer, server, smart mobile device, virtual reality device, augmented reality device, etc. The structure device of the preferred embodiment of the present invention may include:

[0070] A computer-readable storage medium for storing instructions executable by a processor; it may store computer-readable instructions and / or data, and may include memory and storage devices.

[0071] A processor is used to execute the above-described blade thickness distribution construction method; it can execute instructions stored in a computer-readable storage medium to implement the aforementioned method; in some embodiments, the processor may include at least one hardware processor, such as a microcontroller, microprocessor, reduced instruction set computer (RISC), application-specific integrated circuit (ASIC), application-specific instruction set processor (ASIP), central processing unit (CPU), graphics processing unit (GPU), physical processor (PPU), microcontroller, digital signal processor (DSP), field-programmable array (FPGA), advanced reduced instruction set system (ARM), programmable logic device (PLD), any circuit or processor capable of performing at least one function, or any combination thereof.

[0072] On the other hand, a preferred embodiment of the present invention also provides a blade that applies a blade thickness distribution construction method.

[0073] On the other hand, a preferred embodiment of the present invention also provides an aero-engine that applies the above-described blade thickness distribution construction method.

[0074] In the description of this invention, it should be noted that the terms "upper", "lower", "front", "rear", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0075] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0076] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method of constructing a profile thickness distribution, applied to a compressor stator blade, characterized by, The thickness distribution of the blade profile includes a leading edge section with an elliptic arc-shaped thickness distribution curve, a second section with a convex circular arc-shaped thickness distribution curve, a third section with a concave circular arc-shaped thickness distribution curve, and a trailing edge section with a circular arc-shaped thickness distribution curve, and the design parameters include a leading edge length-width ratio e, a trailing 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, and the thickness distribution configuration method of the blade 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, and the ellipse passes through point B (x1, t le ); S2. Construct the second segment to make a convex circular arc BCD with O2(x m ,T c2 ) as the center and R2 as the radius, with the starting point B(x1, t le ) and the ending point D(x2, T2), and passing through the maximum thickness point C(x m ,T m ), with D located to the right of C. S3. Construct the third segment as a concave circular arc DE with center at O3(x c3 ,T c3 ) and radius R3, with starting point at D(x2, T2) and ending point at E(x3, T te ), tangent to the circular arc of the second segment at point D and tangent to the circular arc of the trailing edge segment at point E. S4. Construct the tail edge section, making a circular arc EF with O4(x c4 ,0) as the center and R4 as the radius, the starting point of the circular arc being E(x3,t te ) and the end point being F(1,0), the circular arc being tangent to the circular arc of the third section at point E, the tangent at point E making an angle of θ / 2 with the horizontal coordinate. S5. Parameter input, determine the leading edge aspect ratio e, the leading edge thickness t based on the flow field conditions and the strength requirement le , the maximum thickness T m , the maximum thickness position x m , the trailing edge thickness t te and the trailing edge wedge angle θ; S6. The front edge section is solved, assuming that the angle between the tangent line of point B and the horizontal axis is ω, and the relationship between x1 and ω is determined according to the geometric relationship of the ellipse passing through the origin, the major axis a and the minor axis b, and the aspect ratio e; S7. Second segment solution, using geometric relations (T m -t le ) / (x m -x1) = tan(ω / 2), and the relation of x1 and ω determined in S6, solve for x1, ω, a parameters, calculate the center (x c2 , T c2 ) and radius R2, R2 = (x m -x1) / sin(ω / 2), T c2 = T m -R2; S8. Determine the trailing edge segment, from the trailing edge thickness t te Determine the radius R4 from the cosine of the wedge angle θ, R4 = t te / cos(θ / 2), x c4 = 1 - t te / cos(θ / 2), and solve for x3 to get the E point coordinates; S9. The third section is solved, assuming that ∠CO2D = α, and then the coordinates of point D can be expressed as a function of α, = β = a - θ / 2, through the coordinates of D, E two points, length L and DE and the angle between the horizontal axis (β + θ) / 2 between the trigonometric relations, the equation is solved a, combined with the geometric relationship between the chord and the radius of the third segment of the circle center (x c3 , T c3 ) and radius R3, R3 = (L / 2) / sin(β / 2); S10. The curves are integrated, and the four sections of curves are spliced according to the tangent condition to generate a complete dimensionless thickness distribution.

2. The profile construction method of claim 1, wherein front edge thickness t le , maximum thickness T m , trailing edge thickness t te The values are determined according to the strength and frequency evaluation.

3. The profile construction method of claim 2, wherein The aspect ratio e of the leading edge is in the range of 1-2; Maximum thickness position x m The trailing edge wedge angle θ is in the range of 0 to 3°.

4. The profile construction method of claim 3, wherein The airfoil thickness distribution construction method further comprises: S11. The design parameters are optimized, appropriate variables are selected, and steps S5-S10 are repeated through iteration to optimize the aerodynamic performance of the airfoil.

5. An airfoil thickness distribution configuration device characterized by comprising: Comprise: A computer-readable storage medium for storing instructions executable by a processor; A processor for executing the airfoil thickness distribution construction method according to any one of claims 1-4.

6. A vane characterised in that, The application has the airfoil thickness distribution construction method according to any one of claims 1-4.

7. An aeroengine characterised in that, The application has the blade according to claim 6.

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