CN116127628B

CN116127628B - A method and system for indirect generation of transverse blade profiles based on the thickness distribution of the mid-arc line.

Info

Publication number: CN116127628B
Application number: CN202211616250.9A
Authority: CN
Inventors: 李景银; 宫超玄; 孟凡杰; 李昆航; 齐文闯; 李鹏程
Original assignee: Xian Jiaotong University
Current assignee: Xian Jiaotong University
Priority date: 2022-12-15
Filing date: 2022-12-15
Publication date: 2026-04-10
Anticipated expiration: 2042-12-15
Also published as: CN116127628A

Abstract

The method and related apparatus for indirect generation of transonic airfoils based on mid-arc line and thickness distribution include: extracting the mid-arc line and thickness distribution based on the original airfoil; fitting the mid-arc line parameters by adding control points; fitting the thickness distribution parameters by adding control points; generating the mid-arc line, thickness distribution, and suction and pressure surface coordinates by calling the airfoil generation function based on the fitted parameters; generating an elliptical leading edge and a circular trailing edge, smoothly connecting them with the pressure and suction surfaces to generate a complete airfoil. The method controls the airfoil variation by superimposing the mid-arc line and thickness distribution. After obtaining the mid-arc line and thickness distribution of the airfoil, they are fitted to extract control points and control parameters. The mid-arc line and thickness distribution can be superimposed to generate the suction and pressure surfaces of the airfoil. To ensure a smooth connection, the slope is kept consistent at the connection point. An ellipse is used for the leading edge, and a circular arc is used for the trailing edge. Generating a complete airfoil is simple and convenient.

Description

Cross-pitch leaf type indirect generation method and system based on mean camber line plus thickness distribution

Technical Field

The invention belongs to the technical field of cross-pitch leaf pattern design, and particularly relates to a cross-pitch leaf pattern indirect generation method and system based on camber line thickening degree distribution.

Background

An axial-flow compressor is a multi-stage compression device with the airflow flowing direction consistent or nearly consistent with the rotating axial line direction of a working wheel, and is formed by alternately arranging a series of stator-rotors, and is commonly used for an aeroengine or a gas turbine. The blades of the axial flow compressor are important parts for realizing the conversion of the airflow function and changing the airflow direction of the airflow channel of the compressor. The blade profile of the blade is a basic unit for forming the blade, and the blade is formed by stacking the blade profiles along stacking lines.

The inlet relative Mach number under the partial blade height of the cross-sound compressor is larger than 1, so that the supersonic wave is achieved. The transonic stage has complex flow phenomena such as shock waves and mutual interference with boundary layers, leakage of movable blade tops and the like, and meanwhile, the shape of the front edge has important influence on the blade profile loss of the blade cascade and the stable operation working condition range of the blade cascade, and the problems bring great difficulty to the development process of the transonic stage. Therefore, the blade profile design method can meet the requirements of the cross-sound working condition.

The conventional design of the existing blade profile is to directly define the pressure surface and the suction surface of the blade profile by using curves, give out the coordinate and curvature requirements of control points on the pressure surface and the suction surface, and generate molded lines by using piecewise circular arcs, polynomials or spline functions.

In the other mode, the blade profile is designed through multiple circular arcs, and the blade profile is generated through splicing of 2 or more sections of circular arcs.

The current high-load blade profile mostly adopts a multi-arc blade profile, a free curve form blade profile without a definite curve form and constraint conditions, and the blade profile designed by the method has the following defects:

1) The loss is large, so that the efficiency of the compression part is low under the working condition of high rotating speed;

2) The variable attack angle range is narrower, so that the surge margin of the compression part is insufficient;

3) The increase of the lag angle is larger, so that the working state of the compression part is easy to deviate from the design value greatly;

4) And the transition at the multi-end arc connection part is unstable.

5) And the problem that the shape of the leading edge and the trailing edge of the blade is complex or the strength is insufficient by adopting a curve design method.

Disclosure of Invention

The invention aims to provide a method and a system for indirectly generating a cross-pitch blade profile based on mean camber line plus thickness distribution, which are used for solving the problems of higher loss, lower efficiency, narrower variable attack angle range, larger deviation of working state from a design value and insufficient transition unstable strength of a connecting part of a compression part under the working condition of high rotating speed in the prior art.

In order to achieve the above purpose, the present invention adopts the following technical scheme:

a cross-tone leaf type indirect generation method based on mean camber line plus thickness distribution comprises the following steps:

extracting a camber line and thickness distribution based on the original leaf profile;

adding control points to fit the mean camber line parameters;

Adding control points to fit thickness distribution parameters;

according to the fitted parameters, calling a blade profile generating function to generate a camber line, thickness distribution and coordinates of a suction surface and a pressure surface;

Generating an elliptic leading edge and a round trailing edge, and smoothly connecting the elliptic leading edge and the round trailing edge with a pressure surface and a suction surface to generate a complete blade profile.

Further, extraction of camber lines and thickness distribution is performed based on the original leaf profile:

and according to definition of the mean camber line, making an inscribed circle on the original leaf profile, then connecting circle centers of the inscribed circles to obtain the mean camber line, and obtaining thickness distribution at the corresponding circle centers of the inscribed circles, specifically, making normal line and intersection points of the suction surface and the pressure surface of the leaf profile through the circle centers of the inscribed circles, and obtaining the thickness distribution through connecting the points.

Further, adding control points to fit the mean camber line parameters:

adopting a Bezier curve to fit a mean camber line, wherein the order of the Bezier curve is a fourth order, the curve contains five control points p0 to p4 respectively, the control points p0 and p4 are fixed respectively, and the positions of the other three control points are optimized;

wherein the leaf chord length c=constant

The conversion yields the following 6 parameters as variables and gives the relevant meaning:

leading edge direction angle α and trailing edge direction angle β:

from the endpoints and tangential properties of the Bezier curve:

;

Same reason

;

The deflection change rule parameters j and k are e, f, g and i are the lengths of line segments;

deflection change law parameters h1, h2:

h1 represents the vertical distance from the point P2 to the straight line P0 Pd;

h2 represents the vertical distance from the point P2 to the straight line P4Pd, and the point Pd is the intersection point of the extension lines of the P0P1 and the P4P 3.

Further, the specific solving steps are that according to the coordinates of the control points p0 and pd, a straight line equation ax+by+C=0 of the two points is solved to obtain a straight line equation parameter, and then a deflection change rule parameter h1 is obtained according to the distance from the point to the straight line;

in the same way, according to the coordinates of the control points p4 and pd, a linear equation Dx+Ey+F=0 passing through the two points is obtained, and a deflection change rule parameter h2 is obtained

。

Further, adding control points to fit thickness distribution parameters:

The transonic leaf thickness distribution curve is formed by smoothly connecting two multi-order Bezier curves, the connection point is used as an extreme point of the curve, the derivatives on the left side and the right side are both 0, the ratio of the abscissa direction coordinate to the leaf chord length is the maximum thickness relative position;

Wherein maximum thickness=constant; trailing edge thickness=constant;

the following 7 parameters were extracted as variables:

End-to-end thickness profile cut angles θ1, θ2:

By utilizing the endpoint property and the tangential property of the Bezier curve, the method obtains

Is of the same kind

Maximum thickness relative position:;

the larger the m value is, the position of the maximum thickness of the blade moves towards the trailing edge;

Thickness distribution parameters x1, x2:

the larger x1 is, the slower the thickness change of the front half section of the blade is, the smaller x2 is, and the slower the thickness change of the rear half section of the blade is;

Thickness distribution parameter y1:

The greater y1, the greater the vane nose thickness;

front edge thickness r

The larger the r value, the smaller the ratio of the major and minor axes of the ellipse arc.

Further, according to the fitted parameters, a blade profile generating function is called to generate a camber line, thickness distribution and coordinates of a suction surface and a pressure surface:

Controlling the pitch arc line of the transonic and subsonic blade profiles and the thickness distribution rule of the transonic blade profiles in the optimization process, and obtaining the coordinates of the pitch arc line of the blade profiles and the thickness distribution control points:

mean camber line mid 1= [ P0x P1x P2x P3x P4x; P0y P1y P2y P3y P y ];

Left segment of thickness distribution houdu = [ P0xl P1xl P2xl P3xl P4xl; P0yl P1yl P2yl P3yl P4yl ];

Houdu 12= [ P0xr P1xr P2xr P3xr; P0yr P1yr P2yr P3yr ];

calling a blade profile generating function first blade to generate camber line, thickness distribution and pressure surface suction surface coordinates:

the method comprises the steps of equally dividing a mean camber line and thickness distribution 60, calling a Bessel function to generate a control curve of the mean camber line and the thickness distribution, and carrying out spline interpolation to obtain coordinate points, wherein suction surface coordinates and pressure surface coordinates are obtained through base point coordinates plus-minus trigonometric functions.

Further, generating an elliptic leading edge and a round trailing edge, and smoothly connecting the elliptic leading edge and the round trailing edge with a pressure surface and a suction surface to generate a complete blade profile:

The generation of the elliptic front edge is obtained by adopting a simultaneous elliptic equation and a long-axis equation:

and maintaining the slope consistency at the connecting point to obtain the span-pitch blade profile with the camber line thickening distribution, the elliptic front edge and the circular tail edge.

Further, a pitch-spanned leaf type indirect generation system based on pitch arc thickening distribution comprises:

The data extraction module is used for extracting the camber line and the thickness distribution based on the original leaf profile;

The parameter fitting module is used for adding control points to fit the mean camber line parameters;

the coordinate generation module is used for calling a blade profile generation function to generate a camber line, thickness distribution and coordinates of the suction surface and the pressure surface according to the fitted parameters;

and the blade profile generating module is used for generating an elliptic front edge and a round tail edge, so that the elliptic front edge and the round tail edge are smoothly connected with the pressure surface and the suction surface, and a complete blade profile is generated.

Further, a computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, the processor implementing the steps of a cross-pitch leaf pattern indirect generation method based on a mean camber line plus thickness distribution when the computer program is executed.

Further, a computer readable storage medium stores a computer program which, when executed by a processor, implements the steps of a cross-pitch leaf pattern indirect generation method based on a mean camber line plus thickness distribution.

Compared with the prior art, the invention has the following technical effects:

The invention is mainly used for parameterizing and modeling a transonic blade, and based on the construction mode of mean camber line and thickness distribution of the blade, aiming at the characteristics of large thickness change, complex mean camber line and the like of the transonic blade, the change of the blade profile is controlled by superposing the thickness distribution by the mean camber line, after the mean camber line and the thickness distribution of the blade profile are obtained, 13 control variables are extracted, the mean camber line and the thickness distribution can be superposed to generate a suction surface and a pressure surface of the blade profile, the front edge adopts an ellipse, and the tail edge adopts an arc to generate a complete blade profile.

1) The method is used for the cross-sound working condition, is suitable for various working conditions, and has the advantages that the thickness of the blade profile front edge designed by the method is small, and shock waves are weakened to a certain extent;

2) The invention carries out parameterization treatment on the blade profile parameters, and totally controls the camber line and the thickness distribution by using 13 control variables, thereby meeting the characteristics of large thickness change of the cross-pitch blade and complex camber line;

3) The blade profile curve generated by the method is smooth and continuous, and meanwhile, the problems of strange blade profile, low strength and the like generated by other modeling methods are solved.

4) The reason that the design requirement of the cross-pitch blade is high is mainly that the influence of shock waves exists, and the influence of the shock waves can be controlled by the blade profile designed by the design method through numerical calculation verification (CFD), so that the strength of the shock waves is weakened to a certain extent, and the loss is reduced.

Drawings

FIG. 1 is a flow chart of mean camber line plus thickness profile generation.

Fig. 2 is a graph of the extraction of the camber line of a leaf pattern.

Fig. 3 is an extraction diagram of a profile thickness distribution.

Fig. 4 is a schematic view of a camber line shape of a blade profile.

FIG. 5 is a schematic view of a profile thickness profile modeling.

FIG. 6 is a comparison of performance curves of a cross-tone leaf model prototype versus a representative solution.

Fig. 7 is a graph comparing suction side mach number clouds of a cross-tone vane model prototype and representative versions.

Detailed Description

The invention is further described below with reference to the accompanying drawings:

Referring to fig. 1 to 5, the invention is mainly used for parameterizing and modeling a transonic blade, and based on the construction modes of camber lines and thickness distribution of the blade, aiming at the characteristics of large thickness change, complex camber lines and the like of the transonic blade, the change of a blade profile is controlled by superposing the thickness distribution by the camber lines, after the camber lines and the thickness distribution of the blade profile are obtained, 13 control variables are extracted, the suction surface and the pressure surface of the blade profile can be generated by superposing the camber lines and the thickness distribution, the front edge adopts an ellipse, and the tail edge adopts an arc to generate a complete blade profile.

The variation of the blade profile is controlled by superposing the thickness distribution on the camber line, after the camber line and the thickness distribution of the blade profile are obtained, the camber line and the thickness distribution are fitted, a control point and a control parameter are extracted, the camber line and the thickness distribution can be superposed to generate a suction surface and a pressure surface of the blade profile, in order to ensure smooth connection, the slope is kept consistent at a connecting point, the front edge adopts an ellipse, the tail edge adopts an arc, and the integral blade profile is generated.

Each step of the leaf pattern generation flow is described in detail below.

1) Extraction of camber line and thickness distribution based on original leaf profile

Firstly, the extraction of the camber line and the thickness distribution of the original leaf profile is needed. According to the definition of the mean camber line, an inscribed circle needs to be made on the original leaf profile, and then the center of the inscribed circle is connected to obtain the mean camber line (shown in fig. 2). The thickness distribution can be obtained at the center of the corresponding inscribed circle (see fig. 3).

2) Adding control points to fit the mean camber line parameters

The schematic diagram of the camber line shape of the blade shape is shown in fig. 4.

Because the order of the Bezier curve fitting the mean camber line is four-order, the curve contains five control points, namely p0 to p4, and the point pd in the figure is the intersection point of extended lines of p0p1 and p4p 3. In order to ensure that the chord length of the blade profile is kept unchanged in the optimization process, control points p0 and p4 are respectively fixed, and the other three control points are optimized.

Wherein the leaf chord length c=constant

leading edge direction angle α and trailing edge direction angle β:

From the endpoints and tangent of the Bezier curve, we can get:

;

Same reason

;

deflection change law parameters h1, h2:

h2 represents the vertical distance from point P2 to line P4 Pd.

The specific solving step is that according to the coordinates of the control points p0 and pd, the straight line equation ax+by+C=0 of the two points is solved to obtain the straight line equation parameter, then the deflection change rule parameter h1 is obtained according to the distance from the point to the straight line,

In the same way, according to the coordinates of the control points p4 and pd, a straight line equation Dx+Ey+F=0 passing through the two points is obtained, and a deflection change rule parameter h2 can be obtained

3) Fitting thickness distribution parameters by adding control points

A schematic diagram of the profile thickness profile is shown in FIG. 5.

The transonic leaf profile thickness distribution curve is formed by smoothly connecting two multi-order Bezier curves, the connecting point is used as an extreme point of the curve, the derivatives on the left side and the right side are both 0, and the ratio of the abscissa direction coordinate to the leaf profile chord length is the maximum thickness relative position. The left side of the curve is represented by a four-order Bezier curve, which comprises five control points Ph0-Ph4, and the right part is represented by a three-order Bezier curve, which comprises four control points Ph4 and Pt1-Pt 3.

Wherein maximum thickness=constant; trailing edge thickness=constant;

because the thickness distribution rule is complex, curve control points are more, and the following 7 parameters are extracted as variables for simplifying the model:

End-to-end thickness profile cut angles θ1, θ2:

by utilizing the endpoint property and the tangential property of the Bezier curve, the method can obtain

Is of the same kind

Maximum thickness relative position:;

Thickness distribution parameters x1, x2:

The larger x1, the slower the thickness variation of the front half of the blade, and the smaller x2, the slower the thickness variation of the rear half of the blade;

Thickness distribution parameter y1:

The greater y1, the greater the vane nose thickness;

front edge thickness r

4) Calling a blade profile generating function to generate a camber line, thickness distribution and coordinates of a suction surface and a pressure surface;

the method selects 13 parameters as blade profile optimization variables, and controls the pitch rate and subsonic blade profile camber line and the pitch rate blade profile thickness distribution rule in the optimization process.

The coordinates of the control points of the camber line and the thickness distribution of the blade profile can be obtained:

mean camber line mid 1= [ P0x P1x P2x P3x P4x; P0y P1y P2y P3y P y ];

Houdu 12= [ P0xr P1xr P2xr P3xr; P0yr P1yr P2yr P3yr ];

specifically, the mean camber line and the thickness distribution 60 are equally divided, a Bessel function is called to generate a control curve of the mean camber line and the thickness distribution, and spline interpolation is carried out to obtain a coordinate point. The suction surface coordinates and the pressure surface coordinates are obtained by adding and subtracting trigonometric functions from the base point coordinates.

5) Generating an elliptic leading edge and a round trailing edge, and smoothly connecting the elliptic leading edge and the round trailing edge with a pressure surface and a suction surface to generate a complete blade profile.

To ensure smooth connection, the equation composed of the circle and the pressure surface of the suction surface is solved to obtain the coordinates of the tail edge

In order to ensure smooth connection, the slope is kept consistent at the connection point, and the span-pitch blade profile with the camber line thickening distribution, the elliptic front edge and the circular tail edge can be obtained through the steps.

In order to verify the design method, CFD numerical calculation is adopted for verification, two-dimensional numerical simulation analysis is respectively carried out on the German DLR original blade grating and the blade profile designed by the method, the numerical simulation result shows that the total pressure loss coefficient of the blade profile designed by the method is reduced compared with that of the original blade profile, as shown in figure 6, and meanwhile, the intensity of the blade profile surface shock wave designed by the method is weakened, as shown in figure 7, as shown in Mach number cloud.

In still another embodiment of the present invention, a pitch contour indirect generation system based on pitch arc thickening distribution is provided, which can be used to implement the pitch contour indirect generation method based on pitch arc thickening distribution, and specifically, the system includes:

The division of the modules in the embodiments of the present invention is schematically only one logic function division, and there may be another division manner in actual implementation, and in addition, each functional module in each embodiment of the present invention may be integrated in one processor, or may exist separately and physically, or two or more modules may be integrated in one module. The integrated modules may be implemented in hardware or in software functional modules.

In yet another embodiment of the present invention, a computer device is provided that includes a processor and a memory for storing a computer program including program instructions, the processor for executing the program instructions stored by the computer storage medium. The processor may be a central processing unit (Central Processing Unit, CPU), other general purpose processor, digital signal processor (DIGITAL SIGNAL Processor, DSP), application Specific Integrated Circuit (ASIC), off-the-shelf Programmable gate array (Field-Programmable GATEARRAY, FPGA) or other Programmable logic device, discrete gate or transistor logic, discrete hardware components, etc., which are a computing core and a control core of the terminal adapted to implement one or more instructions, and in particular to load and execute one or more instructions in a computer storage medium to implement a corresponding method flow or a corresponding function, or the processor according to embodiments of the present invention may be used for operation of a cross-tone leaf pattern indirect generation method based on camber line thickening distribution.

In yet another embodiment of the present invention, a storage medium, specifically a computer readable storage medium (Memory), is a Memory device in a computer device, for storing a program and data. It is understood that the computer readable storage medium herein may include both built-in storage media in a computer device and extended storage media supported by the computer device. The computer-readable storage medium provides a storage space storing an operating system of the terminal. Also stored in the memory space are one or more instructions, which may be one or more computer programs (including program code), adapted to be loaded and executed by the processor. The computer readable storage medium herein may be a high-speed RAM memory or a non-volatile memory (non-volatile memory), such as at least one magnetic disk memory. One or more instructions stored in a computer-readable storage medium may be loaded and executed by a processor to implement the corresponding steps in the above-described embodiments with respect to a cross-pitch leaf pattern indirect generation method based on a camber line thickening profile.

It will be appreciated by those skilled in the art that embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.

The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.

These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.

These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.

Finally, it should be noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the above embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made to the specific embodiments of the present invention without departing from the spirit and scope of the present invention, and any modifications and equivalents are intended to be included in the scope of the claims of the present invention.

Claims

1. The method for indirectly generating the cross-pitch leaf pattern based on the mean camber line plus thickness distribution is characterized by comprising the following steps of:

adding control points to fit the mean camber line parameters;

Adding control points to fit thickness distribution parameters;

Generating an elliptic front edge and a round tail edge, and enabling the elliptic front edge and the round tail edge to be smoothly connected with a pressure surface and a suction surface to generate a complete blade profile;

adding control points to perform fitting of the mean camber line parameters:

wherein the leaf chord length c=constant

leading edge direction angle α and trailing edge direction angle β:

from the endpoints and tangential properties of the Bezier curve:

;

Same reason

;

deflection change law parameters h1, h2:

h2 represents the vertical distance from the point P2 to the straight line P4Pd, and the point Pd is the intersection point of the extension lines of the P0P1 and the P4P 3;

and adding control points to fit thickness distribution parameters:

Wherein maximum thickness=constant; trailing edge thickness=constant;

the following 7 parameters were extracted as variables:

End-to-end thickness profile cut angles θ1, θ2:

Maximum thickness relative position:

Thickness distribution parameters x1, x2:

Thickness distribution parameter y1:

front edge thickness r:

。

2. The method for indirectly generating a cross-pitch leaf pattern based on camber line and thickness distribution according to claim 1, wherein the extraction of camber line and thickness distribution is performed based on an original leaf pattern:

3. The indirect generation method of the cross-pitch leaf pattern based on the mean camber line and thickness distribution according to claim 1 is characterized in that the specific solving step comprises the steps of solving a straight line equation ax+by+C=0 of two points according to the coordinates of control points p0 and pd to obtain a straight line equation parameter, and then solving a deflection change rule parameter h1 according to the distance from the point to the straight line;

。

4. The method for indirectly generating a cross-pitch airfoil based on camber line and thickness distribution according to claim 3, wherein a airfoil generating function is called to generate camber line, thickness distribution and suction surface and pressure surface coordinates according to fitted parameters:

mean camber line mid 1= [ P0x P1x P2x P3x P4x; P0y P1y P2y P3y P y ];

Houdu 12= [ P0xr P1xr P2xr P3xr; P0yr P1yr P2yr P3yr ];

5. The indirect generation method of the cross-pitch blade profile based on the camber line plus thickness distribution according to claim 1, wherein an elliptic leading edge and a circular trailing edge are generated so as to be smoothly connected with a pressure surface and a suction surface, and a complete blade profile is generated:

6. An indirect generation system of cross-pitch leaf pattern based on camber line thickening degree distribution, which is characterized by comprising:

the blade profile generating module is used for generating an elliptic front edge and a round tail edge, so that the elliptic front edge and the round tail edge are smoothly connected with the pressure surface and the suction surface to generate a complete blade profile;

adding control points to perform fitting of the mean camber line parameters:

wherein the leaf chord length c=constant

leading edge direction angle α and trailing edge direction angle β:

from the endpoints and tangential properties of the Bezier curve:

;

Same reason

;

deflection change law parameters h1, h2:

and adding control points to fit thickness distribution parameters:

Wherein maximum thickness=constant; trailing edge thickness=constant;

the following 7 parameters were extracted as variables:

End-to-end thickness profile cut angles θ1, θ2:

Maximum thickness relative position:

Thickness distribution parameters x1, x2:

Thickness distribution parameter y1:

front edge thickness r:

。

7. A computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, characterized in that the processor, when executing the computer program, carries out the steps of the method for indirect generation of a cross-pitch contour based on a mean camber line plus thickness distribution according to any one of claims 1 to 5.

8. A computer readable storage medium storing a computer program, wherein the computer program when executed by a processor implements the steps of the pitch contour indirect generation method based on mean camber line plus thickness distribution according to any one of claims 1 to 5.