Blade profile thickness distribution construction method and device, blade and aero-engine

Abstract

The invention discloses a blade profile thickness distribution construction method and device, a blade and an aero-engine, and blade profile thickness distribution comprises a front edge section with a thickness distribution curve in an elliptic arc shape, a second section with a thickness distribution curve in a convex arc shape, a third section with a thickness distribution curve in a concave arc shape and a tail edge section in an arc shape. The design parameters comprise the length-width ratio of the leading edge, the thickness of the leading edge, the maximum thickness, the position of the maximum thickness / the thickness of the trailing edge and the wedge angle of the trailing edge, the leading edge section is tangent to the second section at the position of the thickness of the leading edge, the second section is tangent to the third section, and the third section is tangent to the trailing edge section. The excellent blade design adjusting capacity is achieved through simple and efficient design parameter input, the trailing edge wedge angle serves as the design parameter, the thickness increasing rate of the third part is controlled, and the optimal aerodynamic performance is achieved. A section of thickness distribution rule which shrinks rapidly is constructed by utilizing the geometrical characteristics of the concave arc, controllable diffusion of airflow at the rear half section of the blade is achieved, and the effect of allowance and low loss is achieved.

Description

TECHNICAL FIELD

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

[0002] A compressor is one of the core components of an aero-engine, and its performance largely determines the performance of the engine, while blade design is the core content of compressor design, which determines the performance of the compressor. Compressor blade design mainly includes three parts: camber line design, thickness design and spatial position design of blade center of gravity. Compressor blades need 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 in the entire flow process do not change greatly, 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 range of change is also very large. The blade needs to adapt to the large range of change of the inlet and outlet conditions to achieve 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] A typical compressor blade is shown in Figure 1 , which 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 construction methods of the blade profile is to draw a series of circles along a curve, as shown in Figure 3 and Figure 4 . The perpendicular lines of the centers of the series of 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. The change rule of the thickness from the inlet to the outlet is the so-called thickness distribution.

[0004] The existing stator blade thickness distribution mainly includes three types: discrete point representation, such as C series and NACA65 series, the thickness design parameters of which are basically fixed and cannot be adjusted, the available attack angle range is narrow, the flow loss increases sharply after the stator inlet Mach number crosses the critical value, and the efficiency and margin of high-load compressors cannot be met; the thickness distribution represented by a plurality of segments represented by an analytical formula, such as the technical solution of 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 efficiency and margin requirements of high-load compressors; and the thickness distribution of the technical solution of the publication CN112347579B which adopts a free curve form, the design parameters of which are the coordinates of the control points of the Bezier or B-spline curve, and the design variables are too many, which consumes a lot 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, a construction device, a blade and an aero-engine, to solve the technical problems of small adjustable amount caused by few design variables or long design cycle and high research and development cost caused by too many design variables in the prior art due to the large range of conditions of the inlet and outlet of the compressor blade.

[0006] According to one aspect of the application, a blade thickness distribution construction method is provided, which is applied to a compressor stator blade, the blade thickness distribution includes a leading edge section with an elliptical 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, the design parameters include a leading edge aspect ratio e, a leading edge thickness , a maximum thickness , a maximum thickness position , a trailing edge thickness , and a trailing edge wedge angle , the leading edge section and the second section are tangent at the leading edge thickness position, the second section and the third section are tangent, and the third section and the trailing edge section are tangent.

[0007] As a further improvement of the above technical solution, the leading edge thickness , the maximum thickness , and the trailing edge thickness are determined according to the strength and frequency evaluation results.

[0008] As a further improvement of the above technical solution, the leading edge aspect ratio e is in the range of 1-2; the maximum thickness position The trailing edge wedge angle is in the range of 0.25-0.35 The trailing edge wedge angle is in the range of 0-3°.

[0009] As a further improvement of the above technical solution, the airfoil thickness distribution configuration method comprises the following contents: S1. Configure the leading edge ellipse segment, set 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, and the ellipse passes through point B ( ); S2. Configure the second segment, and make a convex circular arc BCD with O2 ( ) as the center and R2 as the radius, the starting point of the circular arc being B ( ), the ending point being D ( ), and passing through the maximum thickness point C ( ), and the D point being located to the right of the C point; S3. Configure the third segment, and make a concave circular arc DE with O3 ( ) as the center and R3 as the radius, the starting point of the circular arc being D ( ), the ending point being E ( ), and being tangent to the circular arc of the second segment at the D point and tangent to the circular arc of the trailing edge segment at the E point; S4. Configure the trailing edge segment, and make a circular arc EF with O4 ( ) as the center and R4 as the radius, the starting point of the circular arc being E ( ), the ending point being F (1, 0), the circular arc being tangent to the circular arc of the third segment at the E point, and the tangent line of the E point and the horizontal coordinate forming an angle of .

[0010] As a further improvement of the above technical solution, the airfoil thickness distribution configuration method further comprises: S5. Parameter input, determine the leading edge length-width ratio e, the leading edge thickness , the maximum thickness , the maximum thickness position , the trailing edge thickness , and the trailing edge wedge angle based on the flow field conditions and the strength requirements; S6. Leading edge segment solving, set the angle between the tangent line of the B point and the horizontal axis as ω, and determine the relationship between x1 and ω according to the geometric relationship of the ellipse passing through the origin, the long axis a and the short axis b and the length-width ratio e; S7. Second segment solving, use the geometric relationship and the relationship between x1 and ω determined in S6 to solve the parameters such as x1, ω and a, and calculate the center ( ) and the radius R2, , ; S8. Determine the trailing edge segment, and the trailing edge thickness The cosine value of the wedge angle θ determines the radius R4, , , and the coordinates of point E are obtained by solving S9. The third segment is solved by setting , and the coordinates of point D can be expressed as a function of , , by the trigonometric relationship between the coordinates of points D and E, the length L, and the angle between DE and the horizontal axis , the equations are solved simultaneously to obtain , and the geometric relationship between the chord length and the radius is used to determine the center of the third circular arc ( ) and the radius R3, ; S10. Curve integration, the four segments of the curve are spliced according to the tangent condition to generate a complete dimensionless thickness distribution.

[0011] As a further improvement of the above technical solution, the airfoil thickness distribution construction method further comprises: S11. Optimizing design parameters, selecting appropriate variables and repeating steps S5-S10 through iteration to optimize the aerodynamic performance of the airfoil.

[0012] According to another aspect of the present application, a kind of airfoil thickness distribution construction device is also provided, comprising: Computer readable storage medium for storing instructions executable by processor; Processor for executing any of the above described airfoil thickness distribution construction method.

[0013] According to another aspect of the present application, a kind of blade is also provided, which applies any of the above described airfoil thickness distribution construction method.

[0014] According to another aspect of the present application, an aero-engine is also provided, which comprises the above airfoil thickness distribution construction method.

[0015] The present application has the following advantages: ​The blade thickness of the structure is composed of four curves of the initial end leading edge ellipse, the second convex circular arc, the third concave 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 circular arc and the third circular arc of the blade thickness distribution structure method is on the right side of the maximum thickness position. The input parameters of the blade thickness distribution structure method are only six variables of the leading edge length-width ratio, the leading edge thickness, the maximum thickness, the maximum thickness distribution position, the trailing edge thickness and the trailing edge wedge angle, which are all key design parameters. The superior blade design adjustment capability is realized through simple and efficient design parameter input. The trailing edge wedge angle is taken as the design parameter to control the thickness growth rate of the third part to realize the optimal aerodynamic performance. The blade thickness distribution structure method utilizes the geometric characteristics of the concave circular arc to construct a thickness distribution law of rapid contraction to realize controllable pressure expansion of the airflow in the rear half of the blade, and finally realizes the effect of low loss with wide margin, and is suitable for the stator shaping under the condition of high Mach number.

[0016] In addition to the objects, features and advantages described above, the present application has other objects, features and advantages. The present application will be described in further detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0017] The drawings constituting a part of this application are used to provide further understanding of the present application, the schematic embodiments of the present application and the description thereof are used to explain the present application, and do not constitute improper limitation on the present application. In the drawings: 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 1 ; 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 the blade profile thickness construction of the preferred embodiment of the present application; Figure 6 is a schematic diagram of the blade thickness distribution of the preferred embodiment of the present application. DETAILED DESCRIPTION

[0018] 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 different ways as defined and covered below.

[0019] 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 3is a schematic diagram of a prior art airfoil profile construction method; Figure 4 is a schematic diagram of a prior art airfoil profile construction method Figure 2 ; Figure 5 is a schematic diagram of an airfoil profile thickness construction of a preferred embodiment of the present application; Figure 6 is a schematic diagram of an airfoil thickness distribution of a preferred embodiment of the present application; As Figures 4 to 6 shown, the airfoil thickness distribution construction method of the present embodiment is applied to a compressor stator blade, the airfoil thickness distribution includes a leading edge section with an elliptical 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, the design parameters include a leading edge aspect ratio e, a leading edge thickness t1, a maximum thickness t2, a maximum thickness position x2, and a trailing edge thickness t3, a trailing edge wedge angle θ, the leading edge section is tangent to the second section at the leading edge thickness position t1, the second section is tangent to the third section, and the third section is tangent to the trailing edge section.

[0020] It can be understood that the thickness distribution curve constructed by the present airfoil thickness distribution construction method is composed of four curves, i.e., a leading edge ellipse, a second section convex circular arc, a third section concave circular arc, and a trailing edge circular arc, compared to the prior art scheme which takes the maximum thickness position as a dividing point, the dividing point of the second section circular arc and the third section circular arc of the present airfoil thickness distribution construction method is on the right side of the maximum thickness position, the input parameters of the present airfoil thickness distribution construction method are only six variables, i.e., the leading edge aspect ratio, the leading edge thickness, the maximum thickness, the maximum thickness position, the trailing edge thickness, and the trailing edge wedge angle, all of which are key design parameters, and the present airfoil thickness distribution construction method realizes superior blade design adjustment ability through simple and efficient design parameter input, and proposes to take the trailing edge wedge angle as a design parameter to control the thickness growth rate of the third section to achieve the best aerodynamic performance, the present airfoil thickness distribution construction method utilizes the geometric characteristics of the concave circular arc to construct a section of rapidly shrinking thickness distribution law to realize controllable pressure recovery of the airflow in the second half of the blade, and finally realizes the effect of low loss with wide margin, which is suitable for stator blade shaping under high Mach number conditions.

[0021] Further, the leading edge thickness t1, the maximum thickness t2, and the trailing edge thickness t3 are used to control the strength and stiffness of the blade, and thus the values are determined according to the strength and frequency evaluation results.

[0022] Further, the leading edge aspect ratio e determines the thickness growth rate of the leading edge, and its value is in the range of 1-2, the maximum thickness position x2 determines the position of the maximum thickness, and its value is in the range of 0.3-0.7, the trailing edge thickness t3 determines the thickness of the trailing edge, and its value is in the range of 0.1-0.3, and the trailing edge wedge angle θ determines the thickness growth rate of the trailing edge, and its value is in the range of 0-10°. ​​​​​​​​​The flow loss and margin of the airfoil type have certain influence, and the test value is in the range of 0.25-0.35; the tail 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°.

[0023] It should be understood that the thickness distribution of the blade is symmetrical up and down, and the thickness distribution curve of the upper half or the lower half is analyzed; In this embodiment, the method for constructing the thickness distribution of the airfoil type comprises the following contents: S1. Constructing the front edge elliptical segment, setting the first quadrant point of the ellipse as the front edge point A, the coordinates of which are (0, 0), the long axis a of the ellipse coincides with the horizontal coordinate, and the ellipse passes through point B( ); S2. Constructing the second segment, making a convex circular arc BCD with O2( ) as the center and R2 as the radius, the starting point of the circular arc being B( ), the ending point being D( ), and passing through the maximum thickness point C( ), and the D point being located to the right of the C point; S3. Constructing the third segment, making a concave circular arc DE with O3( ) as the center and R3 as the radius, the starting point of the circular arc being D( ), the ending point being E( ), and being tangent to the circular arc of the second segment at the D point and tangent to the circular arc of the tail edge segment at the E point; S4. Constructing the tail edge segment, making a circular arc EF with O4( ) as the center and R4 as the radius, the starting point of the circular arc being E( ), the ending point being F(1, 0), and being tangent to the circular arc of the third segment at the E point, and the tangent at the E point being at an angle of .

[0024] It should be understood that by constructing the front edge elliptical segment, the second segment, the third segment and the tail edge segment, the geometric characteristics of the concave circular arc are used to construct a thickness distribution rule of rapid contraction, so as to realize controllable pressure recovery of the airflow in the rear half of the blade; subsequently, the design can be quickly completed through parameter input, and the design cycle is short, the efficiency is high, and the cost is low.

[0025] In this embodiment, the method for constructing the thickness distribution of the airfoil type further comprises: S5. Parameter input, determining the front edge length-width ratio e, the front edge thickness , the maximum thickness , the maximum thickness position , the tail edge thickness , and the tail edge wedge angle based on the flow field conditions and the strength requirements; Specifically, the front edge thickness , the maximum thickness , trailing edge thickness The strength and stiffness of the blade are controlled, and the value is determined according to the strength and frequency evaluation results; the front edge length-width ratio e determines the thickness growth rate of the front edge, and the value is in the range of 1-2; the maximum thickness position The flow loss and margin of the airfoil have a certain influence, and the value is in the range of 0.25-0.35 after verification; 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°; S6. The front edge segment is solved, 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 long axis a and the short axis b and the length-width ratio e; Specifically, for the front edge segment / elliptical segment, the length-width ratio e can be used to express b as a function of a, simplifying the elliptical equation. By using point B on the ellipse, a can be expressed as a function of x1, simplifying the elliptical equation. Let the angle between the tangent line of point B and the horizontal axis be ω, and the derivative of the elliptical equation is used. By using the relationship between the derivative and the tangent value, x1 can be expressed as a function of ω. At this point, the unknown quantity of the elliptical equation is only ω, and the other parameters e, are design input values; S7. The second segment is solved, and the relationship between x1 and ω determined in S6 is used to solve x1, ω, a and other parameters. , , , ; Specifically, from the geometric relationship , the angle between CB and the horizontal coordinate is , and from the trigonometric relationship , the relationship between x1 and ω determined in S6 is used to solve x1, ω, a and other parameters, and the curve of the first elliptical segment is determined; from the trigonometric relationship , , at this point, the radius and center of the second segment curve have been determined; S8. The trailing edge segment is determined, and the radius R4, is determined by the trailing edge thickness , , and is solved, and the coordinates of point E are obtained; Specifically, from the definition of the trailing edge wedge angle , , The value of the fourth segment arc radius , the trailing edge wedge angle can also be expressed by the relationship, and the coordinates of point E can be solved; S9. The third segment is solved, let , then the coordinates of point D can be expressed as function, , through the coordinates of points D and E, the length L and the angle between DE and the horizontal axis The trigonometric relationship between them, solving simultaneous equations , combined with the geometric relationship between the chord length and the radius, determine the center of the third arc ( ) with radius R3, ; Specifically, in the second arc, the arc ends at intersection D , assuming that the angle between the radius of the line that intersects the center of the circle and the numerical direction is , from the geometric relationship, its value is equal to the exit tangent angle of the second arc, and the horizontal coordinate of the arc exit point is It can be expressed as the coordinates of the center of the second segment Add the radius of the second arc Multiply the angle The sine value of the arc is the ordinate of the center of the second circle plus the radius of the second arc. Multiply the angle The cosine value of , from which we can get two related equations; Specifically, in the third arc, the chord length of the DE segment is , according to D and E The coordinate values ​​of two points can determine the length This is the third formula. Draw a perpendicular line to segment DE through the center of the third arc. According to the geometric relationship of the right triangle and the diagram, the acute angle formed by the center of the circle is half the included angle. Subtract wedge angle , then the third arc It will be equal to half the length of the chord of segment DE divided by the sine of the angle. This is the fourth formula; It should be understood that the coordinates of the center of the third arc are Equal to its E coordinate Add arc radius Multiply the wedge angle The sine value of the third arc center coordinates Equal to coordinates Add arc radius Multiply the wedge angle The cosine value of the fifth and sixth types; among them, the trailing edge wedge angle is a known given quantity, the angle The third arc center and D The coordinate relationship is determined, which is the seventh formula; by combining the above seven relationships, we can solve 、 、 、 、 、 、 Seven variables; at this point, all analytical expressions of the curves have been determined, and the dimensionless thickness distribution of the blade can be solved; S10. Curve integration: splice the four curve segments according to the tangency condition to generate a complete dimensionless thickness distribution.

[0026] Furthermore, the blade profile thickness distribution configuration method further includes: S11. Optimize the design parameters, select appropriate variables, and repeat steps S5-S10 to optimize the aerodynamic performance of the blade through iteration; After repeated iterations, appropriate variables can be selected to complete the blade thickness design with a fixed wedge angle.

[0027] This blade thickness distribution construction method has good blade design adjustment capabilities and simple and efficient design parameter input, providing a blade shape with controllable blade thickness growth and rate, realizing controllable diffusion blade thickness distribution, and controlling the wedge angle formed by the trailing edge tangent to adapt to the shape required by the shock wave, and can control the leading edge thickness to adapt to the needs of the leading edge thickness; the obtained blade thickness distribution can not only achieve continuous and smooth blade surface without mutations, but also achieve controllable thickness growth rate through concave and convex arc thickness distribution, which is suitable for stator blade shaping under high Mach number conditions; this design method uses the geometric characteristics of the concave arc to construct a rapidly contracting thickness distribution law, realizes controllable expansion of the airflow in the rear half of the blade, and proposes the trailing edge wedge angle as a design parameter to control the thickness growth rate of the blade to achieve optimal aerodynamic performance, and ultimately achieve the effect of widening the margin and reducing low losses, which is suitable for stator blade shaping under high Mach number conditions.

[0028] On the other hand, a preferred embodiment of the present invention further provides a blade profile thickness distribution configuration device, which can be a computer, a server, a smart mobile device, a virtual reality device, an augmented reality device, etc. The configuration device of the preferred embodiment of the present invention may include: Computer-readable storage media for storing instructions executable by a processor; computer-readable instructions and / or data may be stored, and computer-readable storage media may include memory and storage; The processor is configured to execute the above-mentioned method for constructing a blade thickness distribution. The processor can execute instructions stored in a computer readable storage medium to implement the above-mentioned 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 physical processing unit (PPU), a single-chip system, a digital signal processor (DSP), a field programmable gate array (FPGA), an advanced reduced instruction set computer system (ARM), a programmable logic device (PLD), any circuit or processor capable of executing at least one function, or the like, or any combination thereof.

[0029] In another aspect, the preferred embodiments of the present application also provide a blade to which the method for constructing a blade thickness distribution is applied.

[0030] In another aspect, the preferred embodiments of the present application also provide an aero-engine to which the method for constructing a blade thickness distribution is applied.

[0031] In the description of the present application, it should be noted that the terms "upper", "lower", "front", "back", and the like indicate the orientation or positional relationship shown in the drawings, and are only used to facilitate the description of the present application and simplify 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.

[0032] 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 fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be direct connection, or indirect connection through an intermediate medium; it can be internal communication of 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.

[0033] The above description is only for the preferred embodiments of the present application and is not intended to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A blade thickness distribution construction method, applied to compressor stator blades, characterized in that: The blade thickness distribution includes a leading edge section with an elliptical thickness distribution curve, a second section with a convex arc thickness distribution curve, a third section with a concave arc thickness distribution curve, and a trailing edge section with an arc thickness distribution curve. The design parameters include the leading edge aspect ratio e, the trailing edge wedge angle , leading edge thickness , maximum thickness , maximum thickness position and trailing edge thickness , the leading edge section and the second section are at the leading edge thickness The second segment is tangent to the third segment, and the third segment is tangent to the trailing edge segment.

2. The blade profile thickness distribution configuration method according to claim 1, characterized in that: Leading edge thickness , maximum thickness , trailing edge thickness The value is determined based on the intensity and frequency assessment results.

3. The blade profile thickness distribution configuration method according to claim 2, characterized in that: The leading edge aspect ratio e is in the range of 1-2; the maximum thickness position The value range is 0.25~0.35, and the trailing edge wedge angle The value range is 0~3°.

4. The blade profile thickness distribution configuration method according to claim 3, characterized in that: The blade profile thickness distribution construction method includes the following contents: S1. Construct the leading edge ellipse segment, set the first quadrant point of the ellipse as the leading edge point A, the coordinates are (0, 0), the major axis a of the ellipse coincides with the horizontal coordinate, and the ellipse passes through point B ( ); S2. Construct the second segment, with O2 ( ) as the center and R2 as the radius to make a convex arc BCD. The starting point of the arc is B( ), the end point is D ( ) and passes through the maximum thickness point C ( ), point D is to the right of point C; S3. Construct the third segment, with O3 ( ) as the center and R3 as the radius to make a concave arc DE. The starting point of the arc is D ( ), the end point is E ( ), it is tangent to the arc of the second segment at point D, and tangent to the arc of the trailing edge segment at point E; S4. Construct the trailing edge segment, with O4 ( ) as the center and R4 as the radius to make an arc EF. The starting point of the arc is E ( ), the end point is F(1,0), and it is tangent to the arc of the third segment at point E. The angle between the tangent line at point E and the horizontal coordinate is .

5. The blade profile thickness distribution configuration method according to claim 4, characterized in that: The blade thickness distribution construction method: S5. Parameter input, determine the leading edge aspect ratio e and leading edge thickness based on flow field conditions and strength requirements , maximum thickness , maximum thickness position , trailing edge thickness and trailing edge wedge angle ; S6. Solve the leading edge segment. Let the angle between the tangent line at point B and the horizontal axis be ω. Based on the geometric relationship between the ellipse passing through the origin, the major axis a, the minor axis b, and the aspect ratio e, determine the relationship between x1 and ω. S7. Solve the second section using geometric relationships , and the relationship between x1 and ω determined by S6 are used to solve the parameters x1, ω, a, etc., and calculate the center of the circle ( ) with radius R2, , ; S8. Determine the trailing edge segment by the trailing edge thickness The radius R4 is determined by the cosine of the wedge angle θ. , , and solve , get the coordinates of point E; S9. Solve the third paragraph, let , then the coordinates of point D can be expressed as function, , through the coordinates of points D and E, the length L and the angle between DE and the horizontal axis The trigonometric relationship between them, solving simultaneous equations , combined with the geometric relationship between the chord length and the radius, determine the center of the third arc ( ) with radius R3, ; S10. Curve integration: splice the four curve segments according to the tangency condition to generate a complete dimensionless thickness distribution.

6. The blade profile thickness distribution configuration method according to claim 5, characterized in that: The blade profile thickness distribution configuration method further includes: S11. Optimize the design parameters, select appropriate variables, and repeat steps S5-S10 to optimize the aerodynamic performance of the blade through iteration.

7. A blade thickness distribution structure device, characterized in that: include: a computer-readable storage medium for storing instructions executable by a processor; A processor, configured to execute the blade profile thickness distribution construction method according to any one of claims 1 to 6.

8. A blade, characterized in that: The blade thickness distribution construction method according to any one of claims 1 to 6 is applied.

9. An aircraft engine, characterized in that: The blade according to claim 8 is used.

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