Method and system for rapidly generating compressor blade profile containing local geometric deviation

Abstract

The invention discloses a method for quickly generating a compressor blade profile containing local geometric deviation. The method comprises the following steps: determining a mean camber line point and thickness distribution according to geometric data of a suction surface and a pressure surface; determining parameterized expression of the mean camber line geometry according to the camber line points, and obtaining parameter expression of a thickness distribution curve according to the thickness distribution; generating pressure surface geometric points and suction surface geometric points containing local geometric deviation based on parameterized expression of mean camber line geometry and parameterized expression of the thickness distribution curve; a blade profile leading edge curve and a blade profile trailing edge curve are generated; and integrating the curve data to generate the blade profile containing the local geometric deviation. The blade obtained on the basis of the method contains the local geometric deviation, control over the machining deviation of the blade is facilitated, and the method has great significance in determining the influence of the typical geometric deviation of the blade on the aerodynamic characteristics of the gas compressor through simulation calculation.

Description

Technical Field

[0001] The present invention relates to the field of manufacturing blades of aviation gas turbine engines, and in particular to a method and a system for rapidly generating a compressor blade profile containing local geometric deviations. Background Art

[0002] The compressor is one of the core components of an aircraft gas turbine engine. At the same time, it is also one of the most difficult key components in an aircraft engine to process. The complexity of blade geometry makes it difficult to avoid geometric deviations during modeling, processing, and installation, resulting in typical deviations such as inlet geometric angle deviation and profile deviation. The geometric deviations generated when processing blades are directly reflected in the basic blade profile of the blade. Domestic and foreign research institutions have carried out a lot of aerodynamic research work at the blade profile level based on different forms of processing deviations, but have not yet clearly proposed a method for quickly generating compressor blade profiles containing local geometric deviations. Summary of the invention

[0003] In view of the research and analysis on the influence of typical geometric deviations of blades on the aerodynamic characteristics of compressors, the present invention proposes a method for quickly generating compressor blade profiles containing local geometric deviations, which can construct a geometric deviation blade profile that is actually representative and includes inlet geometric angle deviations and profile deviations, facilitating subsequent research.

[0004] In order to achieve the above object, the technical solution adopted by the present invention is: a method for quickly generating a compressor blade profile containing local geometric deviations, comprising the following steps: Determine the mid-arc point and thickness distribution based on the geometric data of the suction surface and the pressure surface; Determine the parametric expression of the mid-arc geometry according to the arc points, and obtain the parametric expression of the thickness distribution curve according to the thickness distribution; Generate pressure surface geometry points and suction surface geometry points including local geometry deviations based on the parametric expression of the mid-camber geometry and the parametric expression of the thickness distribution curve; Generate leading edge curve and trailing edge curve of blade profile; A compressor blade profile including local geometric deviations is generated based on pressure surface geometric points, suction surface geometric points, blade leading edge curve and trailing edge curve including local geometric deviations.

[0005] Furthermore, obtaining the geometric data of the suction surface and the pressure surface includes: dividing the original blade profile into four sections: a leading edge curve, a trailing edge curve, a suction surface curve and a pressure surface curve, and interpolating them using a B-spline interpolation algorithm to obtain relatively dense geometric data of the suction surface and the pressure surface.

[0006] Furthermore, determining the mid-arc point and thickness distribution according to the geometric data of the suction surface and the pressure surface includes: for each suction surface point, finding the pressure surface point closest to the point, the midpoint of the line connecting the two points is the point on the mid-arc line, and 1 / 2 of the length of the line is the blade thickness at the mid-arc point, repeating the above steps for all geometric points on the suction surface to obtain the complete distribution of the mid-arc point, connecting all the mid-arc points to obtain the mid-arc curve, and at the same time obtaining the blade thickness distribution, using the coordinate point (xm) composed of the mid-arc point coordinate and the blade thickness h m ,y h ) represents the blade thickness distribution.

[0007] Furthermore, the parameter expression of the thickness distribution curve obtained according to the thickness distribution includes: the entire thickness distribution area is divided into multiple sections, and the coordinates of the control points on each thickness distribution section are (x 1 m ,y 1 h ); In the first section, the number of control points is 4. According to the thickness distribution curve, the coordinates of the 4 control points are (x 1 m1 ,y 1 h1 )、(x 1 m2 ,y 1 h2 )、(x 1 m3 ,y 1 h3 ) and (x 1 m4 ,y 1 h4 ), where the first point is the starting point of the mid-arc and the thickness at that point, and the fourth point is H i+1 The starting point of the segment thickness distribution, (x 1 m2 ,y 1 h2 ) and (x 1 m3 ,y 1 h3 ) is optimized with the minimum fitting error as the goal, and the analytical solution of the polynomial coefficients of the parameterized expression of the first segment thickness distribution curve is obtained by using the above constraints; The constraints required for the thickness distribution of the second to last segment are: Determine the starting and ending points of the thickness distribution curve of the corresponding segment: (x j m1 ,y j h1 ) and (x j m3 ,y jh3 ), and then the end point of the previous thickness distribution curve, that is, (x j m1 ,y j h1 ) is calculated and recorded as After obtaining the above three constraints, the intermediate control point (x j m2 ,y j h ), using the above constraints, the analytical solutions of the polynomial coefficients of the parameterized expression of the thickness distribution curves of other segments are obtained.

[0008] Furthermore, based on the parametric expression of the mid-camber geometry and the parametric expression of the thickness distribution curve, the pressure surface geometry points and the suction surface geometry points containing the local geometric deviations are generated: Based on any coordinate x between the leading edge point and the trailing edge point of the blade m , get the coordinates of the middle arc (x m ,y m ) and the blade thickness y at that point h ; The point on the center arc (x m ,y m ), solve to get the slope value y of the mid-arc at that point k , determine the direction of the line connecting the corresponding suction surface point and the pressure surface point according to the slope value, and in the middle arc coordinate (x m ,y m ) based on the superimposed thickness y h , obtain the geometric points of the pressure surface and suction surface of the reference blade; For the inlet geometric angle deviation, the blade profile is regenerated by modifying the parameters of the arc fitting polynomial in the first segment; For the profile deviation, the thickness at different mid-arc points of the original blade profile is directly enlarged in proportion, and other parameters are kept unchanged to generate a compressor blade profile containing the profile deviation.

[0009] Further, generating the leading edge curve and the trailing edge curve of the blade profile includes: generating four control points of the leading and trailing edge parts through the original blade profile geometric data and the distance and angle relationship, and then generating the leading and trailing edge curve expression through the cubic Bezier curve; The trailing edge curve expression is obtained by the same method.

[0010] In a second aspect, a compressor blade profile including local geometric deviations is provided, which is obtained by using the above-mentioned method for quickly generating a compressor blade profile including local geometric deviations.

[0011] On the other hand, the present invention provides a system for rapidly generating a compressor blade profile including local geometric deviations, including a calculation module, a parameterized expression module, a geometric point acquisition module, a curve generation module, and a blade generation module; The calculation module is used to determine the mid-arc point and thickness distribution according to the geometric data of the suction surface and the pressure surface; The parametric expression module is used to determine the parametric expression of the mid-arc geometry according to the arc points, and obtain the parametric expression of the thickness distribution curve according to the thickness distribution; The geometric point acquisition module generates pressure surface geometric points and suction surface geometric points including local geometric deviations based on the parametric expression of the mid-arc geometry and the parametric expression of the thickness distribution curve; The curve generation module is used to generate the leading edge curve and the trailing edge curve of the blade; The blade generation module generates a compressor blade profile containing local geometric deviations based on pressure surface geometric points, suction surface geometric points, blade leading edge curves and trailing edge curves containing local geometric deviations.

[0012] The present invention can also provide a computer device, including a processor and a memory, the memory is used to store a computer executable program, the processor reads the computer executable program from the memory and executes it, and when the processor executes the computer executable program, it can implement the method of the present invention for quickly generating a compressor blade profile containing local geometric deviations.

[0013] A computer-readable storage medium is also provided, in which a computer program is stored. When the computer program is executed by a processor, the method of the present invention for rapidly generating a compressor blade profile containing local geometric deviations can be implemented.

[0014] Compared with the prior art, the present invention has at least the following beneficial effects: This technology can quickly generate two-dimensional blade profiles with different geometric deviations by modifying the characteristic parameters of the camber line and thickness distribution analytical expression. It provides a method for quickly generating blade profiles with local geometric deviations to clarify the influence of typical blade geometric deviations on the aerodynamic characteristics of the compressor and determine the correlation between different processing deviations and the aerodynamic performance of the compressor. It is of great significance for guiding the design of compressor blade profiles. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 Flow chart for implementing the method of the present invention; Figure 2 This is a schematic diagram of the definitions of various parameters of the present invention. DETAILED DESCRIPTION

[0016] The present invention will be further described below in conjunction with the accompanying drawings.

[0017] like Figure 1As shown, the present invention provides a method for quickly generating a compressor blade profile including a local geometric deviation, which specifically includes the following steps: Step 1: interpolation of original leaf profile data; like Figure 2 The blade profile shown is divided into four sections: leading edge curve, trailing edge curve, suction surface curve and pressure surface curve. For the original relatively discrete blade profile geometric points, the B-spline interpolation algorithm is first used to interpolate them to obtain relatively dense suction surface and pressure surface geometric data.

[0018] Step 2: Determine the mid-arc point and thickness distribution; After obtaining the geometric data of the suction surface and pressure surface, for each suction surface point, find the pressure surface point closest to the point. The midpoint of the line connecting the two points is the point on the mid-arc line, and 1 / 2 of the length of the line is defined as the blade thickness at the mid-arc line point. Repeat the above steps for all geometric points on the suction surface to obtain the complete distribution of the mid-arc line points. Connect all the mid-arc line points to obtain the mid-arc line curve. The point on the mid-arc line is recorded as (x m ,y m At the same time, the blade thickness distribution is also obtained, using the coordinate point (x m ,y h ) represents the blade thickness distribution.

[0019] For the above method of determining the median arc and thickness, the angle between the line connecting the suction surface point and the pressure surface point and the local tangent of the median arc is fixed. The slope of the line connecting the suction surface point and the pressure surface point is calculated using the geometric coordinates of the suction surface point and the pressure surface point, which is recorded as tanα1. The slope of the local tangent direction of the median arc is calculated using the geometric coordinates of each point on the median arc, which is recorded as tanα2. The angle between α1 and α2 is fixed, and tanα1-tanα2 must also be fixed. The difference between the two is recorded as Cα. The coordinate point x of the median arc is m and the slope tanα2 at that point (expressed in y k represents) the coordinate point (x m ,y k ) is distributed as Figure 2 shown.

[0020] Step 3: Parametric expression of the mid-arc geometry; The present invention uses a piecewise polynomial to fit the mid-arc points generated in step 2 to obtain a parameterized expression of the mid-arc. As an example, a 12-segment polynomial is used to fit the mid-arc points, and each segment of the curve is denoted as L i (i=1,2,3…N), the mid-arc point on each curve is (x i m ,y i m). A cubic polynomial is used to fit the arc points, and a total of 12 cubic polynomials are used. For each cubic polynomial, 4 constraints are required to determine its coefficients. The polynomial expression is recorded as ,but: (1) The number of control points in the first segment is 3, which is recorded as (x 1 m1 ,y 1 m1 )、(x 1 m2 ,y 1 m2 )、(x 1 m3 ,y 1 m3 ). The first control point (x 1 m1 ,y 1 m1 ) is the starting point of the middle arc and also the starting point of the segment area. The slope at the first control point controlled by the inlet geometry angle is recorded as the slope. The coordinates and slope of the first point are used as the two constraints for polynomial fitting in blade fitting. The third control point (x 1 m3 ,y 1 m3 ) is the end point coordinate of the segment. The coordinate of this point is used as a constraint condition for polynomial fitting in blade fitting. For the second control point (x 1 m2 ,y 1 m2 ), using its coordinates as the last constraint of the polynomial fitting, but in the original blade fitting (x 1 m2 ,y 1 m2 ) is not given in advance, but is optimized with the minimum fitting error as the goal. Using the above four constraints, the analytical solution of the polynomial coefficients of the arc parameterization expression in the first paragraph can be obtained: (2) For the second to eleventh sections, three control points are also selected. The first control point is L i-1 The end point of the segment curve, the third control point is L i+1 The starting point of the segment curve, the second control point is also optimized with the minimum fitting error as the goal. The above three points are recorded in order as (x i m1 ,y i m1 )(xi m2 ,y i m2 )(x i m3 ,y i m3 ), unlike the first section, in the middle section, the slope of the first point is not used as a constraint during the arc fitting process, but the second-order derivative of the first point is used as a constraint. i-1 The expression of the segment is derived to ensure the continuity of the second-order curvature of the middle arc at the junction of each segment. Using the above four constraints, the analytical solution of the polynomial coefficients of the parameterized expression of the middle arc of any intermediate segment can be obtained: (3) When the last segment is generated, two control points are taken and recorded as (x 12 m1 ,y 12 m1 )(x 12 m2 ,y 12 m2 ), the second point is the end point on the median arc. In addition to the coordinates of the two control points mentioned above, the second-order derivative at the first point is used here, and the first-order derivative of the last point is obtained by using the expression in paragraph 11 as the other two constraints. As an example, the second-order derivative at the first point is here, where the first-order derivative of the last point is specified by the slope value corresponding to the blade outlet geometry angle. Using the above four constraints, the polynomial coefficients of the parametric expression of the median arc in the last paragraph can be obtained: (4) Step 4: Parametric expression of thickness distribution; The parameter expression method of the thickness distribution curve is similar to that of the mid-arc curve. Since the thickness distribution in the entire interval is relatively smooth, the entire thickness distribution area is divided into four sections. Here, H is used j (j=1,2,3…N) represents the jth thickness distribution, and the coordinates of the control points on each thickness distribution are (x 1 m ,y 1 h ), the thickness distribution of each segment is recorded as : (5) In the first section, the number of control points is 4. According to the thickness distribution curve, the coordinates of the 4 control points are (x 1 m1 ,y 1 h1 )、(x 1 m2 ,y1 h2 )、(x 1 m3 ,y 1 h3 ) and (x 1 m4 ,y 1 h4 ), where the first point is the starting point of the mid-arc and the thickness at that point, and the fourth point is H i+1 The starting point of the segment thickness distribution, (x 1 m2 ,y 1 h2 ) and (x 1 m3 ,y 1 h3 ) is optimized with the minimum fitting error as the goal. Using the above constraints, the analytical solution of the polynomial coefficients of the parameterized expression of the first segment thickness distribution curve can be obtained: (6) The constraints required for the thickness distribution of the second to fourth segments are different from those of the first segment. The first step is to determine the starting and ending points of the thickness distribution curve of the corresponding segment: (x j m1 ,y j h1 ) and (x j m3 ,y j h3 ), and then the end point of the previous thickness distribution curve, that is, (x j m1 ,y j h1 ) is calculated and recorded as After obtaining the above three constraints, the intermediate control point (x j m2 ,y j h ), using the above constraints, the analytical solution of the polynomial coefficients of the parameterized expression of the thickness distribution curve of other segments can be obtained: (7) Step 5: Generate pressure surface geometry points and suction surface geometry points including local geometric deviations; After obtaining the parametric expression of the camber line and thickness distribution, given any coordinate x between the leading edge point and the trailing edge point of the blade m , you can get the coordinates of the middle arc (x m ,y m ), and the blade thickness y at this point can be obtained h, the point on the center arc (x m ,y m ), the slope value y of the mid-arc at this point has been solved k According to the slope value, the direction of the line connecting the corresponding suction surface point and the pressure surface point can be determined. m ,y m ) based on the superimposed thickness y h , the geometric points of the pressure and suction surfaces of the reference blade can be obtained.

[0021] For the inlet geometric angle deviation, the blade profile is regenerated by modifying the parameters of the arc fitting polynomial in the first section. Assume that the three control points determined in the process of generating the arc fitting polynomial in the first section are (x 1 m1 ,y 1 m1 )、(x 1 m2 ,y 1 m2 ) and (x 1 m3 ,y 1 m3 ), the first control point (x 1 m1 ,y 1 m1 ) is the starting point of the middle arc and also the starting point of the segment area. The slope of the mid-arc at the first control point is recorded as a constraint condition for fitting the polynomial in the deviation blade profile fitting. By superimposing the inlet geometric angle deviation on the original blade profile inlet geometric angle, the blade profile containing the inlet geometric angle deviation can be generated by changing the slope of the first control point, and the geometric coordinates of the first point are no longer used as constraints for generating the fitting polynomial. The third control point (x 1 m3 ,y 1 m3 ) is the end point coordinate of the segment, is the slope at the third control point. The coordinates and slope of this point are used as two constraints of the polynomial fitting in the deviation leaf profile fitting. 1 m2 ,y 1 m2 ), using its coordinates as the last constraint condition of the polynomial fitting, in the deviation leaf profile fitting (x 1 m2 ,y 1 m2 ) value remains the same as the original blade profile.

[0022] For the profile deviation, the thickness of the original blade at different mid-arc points is directly enlarged proportionally, and other parameters are kept unchanged to generate a compressor blade with profile deviation.

[0023] Step 6: Generate the leading and trailing edges of the blade; The present invention generates four control points of the front and rear edge parts through original blade geometry data and distance and angle relationships, and then generates a front and rear edge curve expression through a cubic Bezier curve.

[0024] Taking the front edge curve as an example, when calculating, first set the first point of the middle arc line to the center of the front edge (x le0 ,y le0 ), the minimum distance between the leading edge of the original blade and the center of the circle is obtained by traversal method, which is recorded as radius R le The point closest to the suction surface and pressure surface curves is obtained on the original leading edge and recorded as control point 1 (x le1 ,y le1 ) and control point 4 (x le4 ,y le4 ), and then solve the slopes of the suction surface and pressure surface at the junction with the leading edge, and find the control point 2 (x le2 ,y le2 ) and control point 3 (x le3 ,y le3 ), which ensures that the generated leading edge curve is curvature continuous with the suction surface and pressure surface, and the control point 2 (x le2 ,y le2 ) and control point 3 (x le3 ,y le3 ) The distance from control point 1 and control point 4 is based on the radius R le The specific value is obtained by optimizing with the minimum fitting error as the goal. After obtaining the above four control points, a Bezier curve that can parametrically express the leading edge curve can be generated.

[0025] The fitting method for the trailing edge curve is the same as that for the leading edge curve.

[0026] A compressor blade profile including local geometric deviations is generated based on pressure surface geometric points, suction surface geometric points, blade leading edge curve and trailing edge curve including local geometric deviations.

[0027] Based on the concept of the method, the present invention also provides a system for quickly generating a compressor blade profile including local geometric deviations, including a calculation module, a parameterized expression module, a geometric point acquisition module, a curve generation module, and a blade generation module; The calculation module is used to determine the mid-arc point and thickness distribution according to the geometric data of the suction surface and the pressure surface; The parametric expression module is used to determine the parametric expression of the mid-arc geometry according to the arc points, and obtain the parametric expression of the thickness distribution curve according to the thickness distribution; The geometric point acquisition module generates pressure surface geometric points and suction surface geometric points including local geometric deviations based on the parametric expression of the mid-arc geometry and the parametric expression of the thickness distribution curve; The curve generation module is used to generate the leading edge curve and the trailing edge curve of the blade; The blade generation module generates a compressor blade profile containing local geometric deviations based on pressure surface geometric points, suction surface geometric points, blade leading edge curves and trailing edge curves containing local geometric deviations.

[0028] The present invention can also provide a computer device, including a processor and a memory, the memory is used to store a computer executable program, the processor reads the computer executable program from the memory and executes it, and when the processor executes the computer executable program, it can implement the method of quickly generating a compressor blade profile containing local geometric deviations described in the present invention.

[0029] On the other hand, the present invention provides a computer-readable storage medium, in which a computer program is stored. When the computer program is executed by a processor, the method of the present invention for rapidly generating a compressor blade profile containing local geometric deviations can be implemented.

[0030] The computer device may be a laptop computer, a desktop computer or a workstation.

[0031] The processor may be a central processing unit (CPU), a digital signal processor (DSP), an application specific integrated circuit (ASIC), or an off-the-shelf field programmable gate array (FPGA).

[0032] The memory of the present invention may be an internal storage unit of a laptop computer, a desktop computer or a workstation, such as a memory or a hard disk; or an external storage unit, such as a mobile hard disk or a flash memory card.

[0033] Computer-readable storage media may include computer storage media and communication media. Computer storage media include volatile and non-volatile, removable and non-removable media implemented by any method or technology for storing information such as computer-readable instructions, data structures, program modules or other data. Computer-readable storage media may include: read-only memory (ROM), random access memory (RAM), solid-state drive (SSD) or optical disk, etc. Among them, random access memory may include resistance random access memory (ReRAM) and dynamic random access memory (DRAM).

[0034] The above contents are only for explaining the technical idea of ​​the present invention and cannot be used to limit the protection scope of the present invention. Any changes made on the basis of the technical solution in accordance with the technical idea proposed by the present invention shall fall within the protection scope of the claims of the present invention.

Claims

1. A method for rapidly generating a compressor blade profile including local geometric deviations, characterized in that: The following steps are involved: Determine the mid-arc point and thickness distribution based on the geometric data of the suction surface and the pressure surface; Determine the parametric expression of the mid-arc geometry according to the arc points, and obtain the parametric expression of the thickness distribution curve according to the thickness distribution; Generate pressure surface geometry points and suction surface geometry points including local geometry deviations based on the parametric expression of the mid-camber geometry and the parametric expression of the thickness distribution curve; Generate leading edge curve and trailing edge curve of blade profile; A compressor blade profile including local geometric deviations is generated based on pressure surface geometric points, suction surface geometric points, blade leading edge curve and trailing edge curve including local geometric deviations.

2. The method for rapidly generating a compressor blade profile including local geometric deviations according to claim 1, characterized in that: Acquiring the geometric data of the suction surface and the pressure surface includes: dividing the original blade profile into four sections: a leading edge curve, a trailing edge curve, a suction surface curve and a pressure surface curve, and interpolating them using a B-spline interpolation algorithm to obtain relatively dense geometric data of the suction surface and the pressure surface.

3. The method for rapidly generating a compressor blade profile including local geometric deviations according to claim 1, characterized in that: Determining the mid-arc point and thickness distribution according to the geometric data of the suction surface and the pressure surface includes: for each suction surface point, finding the pressure surface point closest to the point, the midpoint of the line connecting the two points is the point on the mid-arc line, and 1 / 2 of the length of the line is the blade thickness at the mid-arc point, repeating the above steps for all geometric points on the suction surface to obtain the complete distribution of the mid-arc point, connecting all the mid-arc points to obtain the mid-arc curve, and at the same time obtaining the blade thickness distribution, using the coordinate point (xm) composed of the mid-arc point coordinate and the blade thickness h m ,y h ) represents the blade thickness distribution.

4. The method for rapidly generating a compressor blade profile including local geometric deviations according to claim 1, characterized in that: The parameter expression of the thickness distribution curve obtained according to the thickness distribution includes: the entire thickness distribution area is divided into multiple segments, and the coordinates of the control points on each thickness distribution segment are (x 1 m ,y 1 h ); In the first section, the number of control points is 4. According to the thickness distribution curve, the coordinates of the 4 control points are (x 1 m1 ,y 1 h1 )、(x 1 m2 ,y 1 h2 )、(x 1 m3 ,y 1 h3 ) and (x 1 m4 ,y 1 h4 ), where the first point is the starting point of the mid-arc and the thickness at that point, and the fourth point is H i+1 The starting point of the segment thickness distribution, (x 1 m2 ,y 1 h2 ) and (x 1 m3 ,y 1 h3 ) is optimized with the minimum fitting error as the goal, and the analytical solution of the polynomial coefficients of the parameterized expression of the first segment thickness distribution curve is obtained by using the above constraints; The constraints required for the thickness distribution of the second to last segment are: Determine the starting and ending points of the thickness distribution curve of the corresponding segment: (x j m1 ,y j h1 ) and (x j m3 ,y j h3 ), and then the end point of the previous thickness distribution curve, that is, (x j m1 ,y j h1 ) is calculated and recorded as After obtaining the above three constraints, the intermediate control point (x j m2 ,y j h ), using the above constraints, the analytical solutions of the polynomial coefficients of the parameterized expression of the thickness distribution curves of other segments are obtained.

5. The method for rapidly generating a compressor blade profile including local geometric deviations according to claim 1, characterized in that: Based on the parametric expression of the mid-camber geometry and the parametric expression of the thickness distribution curve, the pressure surface geometry points and the suction surface geometry points containing local geometric deviations are generated: Based on any coordinate x between the leading edge point and the trailing edge point of the blade m , get the coordinates of the middle arc (x m ,y m ) and the blade thickness y at that point h ; The point on the center arc (x m ,y m ), solve to get the slope value y of the mid-arc at that point k , determine the direction of the line connecting the corresponding suction surface point and the pressure surface point according to the slope value, and in the middle arc coordinate (x m ,y m ) based on the superimposed thickness y h , obtain the geometric points of the pressure and suction surfaces of the reference blade; For the inlet geometric angle deviation, the blade profile is regenerated by modifying the parameters of the arc fitting polynomial in the first segment; For the profile deviation, the thickness at different mid-arc points of the original blade profile is directly enlarged in proportion, and other parameters are kept unchanged to generate a compressor blade profile containing the profile deviation.

6. The method for rapidly generating a compressor blade profile including local geometric deviations according to claim 1, characterized in that: Generating the leading edge curve and the trailing edge curve of the blade includes: generating four control points of the leading and trailing edge parts through the original blade geometry data and the distance and angle relationship, and then generating the leading and trailing edge curve expression through the cubic Bezier curve; The trailing edge curve expression is obtained by the same method.

7. A compressor blade profile including local geometric deviation, characterized in that: The method is adopted to quickly generate a compressor blade profile including local geometric deviations as described in any one of claims 1 to 6.

8. A system for rapidly generating compressor blade profiles including local geometric deviations, characterized in that: It includes a calculation module, a parameterized expression module, a geometric point acquisition module, a curve generation module and a blade generation module; The calculation module is used to determine the mid-arc point and thickness distribution according to the geometric data of the suction surface and the pressure surface; The parametric expression module is used to determine the parametric expression of the mid-arc geometry according to the arc points, and obtain the parametric expression of the thickness distribution curve according to the thickness distribution; The geometric point acquisition module generates pressure surface geometric points and suction surface geometric points including local geometric deviations based on the parametric expression of the mid-arc geometry and the parametric expression of the thickness distribution curve; The curve generation module is used to generate the leading edge curve and the trailing edge curve of the blade; The blade generation module generates a compressor blade profile containing local geometric deviations based on pressure surface geometric points, suction surface geometric points, blade leading edge curves and trailing edge curves containing local geometric deviations.

9. A computer device, characterized in that: The invention comprises a processor and a memory, wherein the memory is used to store a computer executable program, and the processor reads the computer executable program from the memory and executes it. When the processor executes the computer executable program, the method for quickly generating a compressor blade profile containing a local geometric deviation as described in any one of claims 1 to 7 can be implemented.

10. A computer-readable storage medium, characterized in that: A computer program is stored in a computer-readable storage medium, and when the computer program is executed by a processor, the method for rapidly generating a compressor blade profile containing local geometric deviations as described in any one of claims 1 to 7 can be implemented.

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