Aero-engine blade model reconstruction method

Abstract

The application discloses an aero-engine blade model reconstruction method and relates to the field of aero-engines. The method comprises the following steps: constructing a theoretical blade two-dimensional model according to parameters of each discrete point of the blade in design parameters; judging an out-of-tolerance type of an actual blade formed after machining; and adjusting the constructed theoretical blade two-dimensional model according to the out-of-tolerance type to obtain a two-dimensional model of the actual blade. The method can conveniently construct a model of the actual blade, so that various parameters of the actual blade can be analyzed in the subsequent process, and the performance of the actual blade can be judged.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and more specifically to a method for reconstructing aero-engine blade models. Background Technology

[0002] Aero-engine blades are the basic units that make up compressors and turbines. The flow channels formed by adjacent blades determine the performance of the engine. Therefore, blades play a decisive role in the performance of compressors and turbines. However, aero-engine blades are characterized by complex blade profiles, large blade torsion and curvature, thin blades, and high geometric precision requirements. During the manufacturing and prototyping process, due to the influence of the manufacturing process, the blades may exhibit manufacturing deviations after processing.

[0003] The inventors have discovered that the prior art has at least the following problems: it is difficult to determine whether the performance of the blade still meets the requirements after the processing deviation occurs. Summary of the Invention

[0004] One objective of this invention is to propose a method for reconstructing an aero-engine blade model, which enables the construction of a model of the actual aero-engine blade after actual machining.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] This invention provides a method for reconstructing an aero-engine blade model, characterized by comprising the following steps:

[0007] A two-dimensional model of the theoretical blade is constructed based on the parameters of each discrete point of the blade in the design parameters.

[0008] Determine the type of deviation in the actual blades formed after processing;

[0009] Adjust the constructed theoretical two-dimensional blade model according to the type of deviation to obtain the actual two-dimensional blade model.

[0010] In an optional embodiment, the type of deviation is selected from one of the following: profile deviation, blade leading edge deviation, position deviation, and torsion angle deviation.

[0011] In an optional embodiment, if the deviation type is profile deviation, the constructed theoretical blade two-dimensional model is adjusted according to the following steps:

[0012] Calculate the normal direction of each discrete point in the two-dimensional model of the theoretical blade;

[0013] Calculate the profile change of the actual blade relative to the theoretical blade at each discrete point in the two-dimensional model of the theoretical blade;

[0014] The profile variation is superimposed on the normal direction of each discrete point in the theoretical blade two-dimensional model to obtain the actual blade two-dimensional model.

[0015] In an optional embodiment, if the calculated contour change at each discrete point of the theoretical blade is the same, then the same contour change is superimposed on the normal direction of each discrete point of the theoretical blade two-dimensional model to obtain the two-dimensional model of the actual blade.

[0016] In an optional embodiment, if the calculated profile change at each discrete point of the theoretical blade is different, the profile change at each discrete point is superimposed on the normal direction of the discrete point to obtain a two-dimensional model of the actual blade.

[0017] In an optional embodiment, the profile variation y at each discrete point of the theoretical blade is calculated using the following formula:

[0018] Among them, A i K represents the profile amplitude. i α is the number of cycles of profile variation; i X is the phase angle of the profile change; X is the coordinate value along the arc length direction of the airfoil.

[0019] In an optional embodiment, α i Greater than or equal to -1 and less than 1.

[0020] In an optional embodiment, K i The value can be an integer.

[0021] In an optional embodiment, A i The value can be an integer.

[0022] In an optional embodiment, if the out-of-tolerance type is leading edge shape out-of-tolerance, the constructed two-dimensional model is adjusted according to the following steps:

[0023] Calculate the installation angle rectangular coordinate system of the theoretical blade two-dimensional model, and transform the coordinates of the theoretical blade two-dimensional model in the original rectangular coordinate system to the installation angle rectangular coordinate system, where the coordinates of the theoretical blade leading edge point are (0, 0) and the coordinates of the theoretical blade trailing edge point are (BT, 0), where BT is the chord length;

[0024] Based on the measured coordinates of discrete points on the actual leaf at the leading edge, local area of ​​the leaf basin, and local area of ​​the leaf underside, the positions of the discrete points on the theoretical leaf at the leading edge, local area of ​​the leaf basin, and local area of ​​the leaf underside are moved.

[0025] Based on the positions of discrete points in the leading edge, local area of ​​the leaf basin, and local area of ​​the leaf back after displacement, the model is reshaped to obtain a two-dimensional model of the actual blade in the rectangular coordinate system of the installation angle.

[0026] By employing inverse coordinate transformation, the model obtained from the reconstruction of the actual blade installation angle in the rectangular coordinate system is transformed back to the original rectangular coordinate system to obtain a two-dimensional model of the actual blade.

[0027] In optional embodiments, Bézier curves, spline curves, or polynomial curves are used to reshape the leading edge, local area of ​​the leaf basin, and local area of ​​the leaf back after displacement.

[0028] In an optional embodiment, the curve where the leading edge point is located after reconfiguration is first-order continuous and / or the curve at the junction of the leaf basin curve, leaf back curve and the unreconfigured leaf body is second-order continuous.

[0029] In an optional embodiment, if the deviation type is torsion angle deviation, the constructed two-dimensional model is adjusted using the following steps:

[0030] Calculate the centroid coordinates of each section of the two-dimensional model of the theoretical blade;

[0031] Based on the measured centroid coordinates of each section of the actual blade, calculate the torsional angle of the centroid of each section of the theoretical blade relative to the centroid coordinates of each section of the actual blade.

[0032] Based on the torsion angle of each section, the two-dimensional model of the theoretical blade is subjected to torsion based on the center of gravity to obtain the corrected two-dimensional model of the actual blade.

[0033] In an optional embodiment, if the error type is positional error, the constructed two-dimensional model is adjusted using the following steps:

[0034] Calculate the centroid coordinates of each section of the two-dimensional model of the theoretical blade;

[0035] Measure the centroid coordinates of each section of the actual blade;

[0036] Calculate the positional variation of the centroid coordinates of each section of the theoretical blade relative to the actual blade centroid coordinates;

[0037] Based on the positional variation values ​​of the centroid coordinates of each section of the theoretical blade, the two-dimensional model of the theoretical blade is transformed by translational changes based on the centroid to obtain the two-dimensional model of the actual blade.

[0038] Based on the above technical solution, the embodiments of the present invention can produce at least the following technical effects:

[0039] The above technical solution can generate a two-dimensional model of the actually processed blade based on the original two-dimensional model of the blade and the actual processed blade data obtained from the testing. Based on this two-dimensional model of the actual processed blade, the impact on the actual blade performance can be evaluated, thus providing theoretical support for the acceptance of blades with out-of-tolerance performance. Attached Figure Description

[0040] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this application, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings:

[0041] Figure 1 A schematic diagram of the parameters of an aero-engine blade provided in an embodiment of the present invention;

[0042] Figure 2a The aero-engine blades provided in this embodiment of the invention use curves with adjusted uniform profile.

[0043] Figure 2b for Figure 2a A magnified view of part A;

[0044] Figure 2c for Figure 2a A magnified view of part B;

[0045] Figure 3a The aero-engine blades provided in this embodiment of the invention use a curve adjusted by a single profile non-uniform variation;

[0046] Figure 3b for Figure 3a A magnified view of part A;

[0047] Figure 3c for Figure 3a A magnified view of part B;

[0048] Figure 3d The waveform diagram of the amplitude variation of the non-uniform profile is used to generate the non-uniform profile air shape.

[0049] Figure 4a The aero-engine blades provided in this embodiment of the invention employ a curve adjusted by composite profile non-uniform variation.

[0050] Figure 4b for Figure 4a A magnified view of part A;

[0051] Figure 4c for Figure 4a A magnified view of part B;

[0052] Figure 4d The waveform diagram of the amplitude variation of the composite profile non-uniform variation profile is used to generate the composite non-uniform profile airfoil.

[0053] Figure 5a The curve after adjusting the local profile variation of the aero-engine blade provided in the embodiment of the present invention;

[0054] Figure 5bfor Figure 5a A magnified view of part A;

[0055] Figure 5c for Figure 5a A magnified view of part B;

[0056] Figure 6a The curve showing the adjusted profile variation of the leading edge of an aero-engine blade tip, as provided in an embodiment of the present invention.

[0057] Figure 6b for Figure 6a A magnified view of part A;

[0058] Figure 7a The curve showing the adjusted profile variation of the blunt tip leading edge of an aero-engine blade, as provided in an embodiment of the present invention.

[0059] Figure 7b for Figure 7a A magnified view of part A;

[0060] Figure 8a The curve showing the adjusted profile of the leading edge of the suction surface of an aero-engine blade according to an embodiment of the present invention;

[0061] Figure 8b for Figure 8a A magnified view of part A;

[0062] Figure 9a The curve showing the adjusted profile of the leading edge of the pressure surface deflection of an aero-engine blade, provided in an embodiment of the present invention.

[0063] Figure 9b for Figure 9a A magnified view of part A;

[0064] Figure 10a The curve showing the adjusted torsional angle of an aero-engine blade provided in an embodiment of the present invention;

[0065] Figure 10b for Figure 10a A magnified view of part A;

[0066] Figure 10c for Figure 10a A magnified view of part B; Detailed Implementation

[0067] The following is combined Figures 1 to 10c The technical solution provided by this invention will be described in more detail below.

[0068] Explanation of nouns and terms used in this embodiment.

[0069] Axial compressor: A multi-stage compression device in which the airflow direction is consistent with or nearly consistent with the direction of the rotation axis of the impeller. It consists of a series of stators and rotors arranged alternately and is commonly used in aero engines or gas turbines.

[0070] Blades: The airflow passage of a compressor / turbine, a crucial component that enables the conversion of airflow function and changes the direction of airflow.

[0071] Leaf shape: The basic unit that makes up a leaf. A leaf is formed by stacking leaf shapes along the stacking line.

[0072] Out-of-tolerance: Aero-engine blades have complex profiles and large blade twist and curvature. During the blade manufacturing and prototyping process, due to the influence of the manufacturing process, the actual geometric parameters of the blade after processing may deviate from the theoretical values. This phenomenon is called out-of-tolerance. Types of out-of-tolerance include profile out-of-tolerance, blade leading edge out-of-tolerance, positional out-of-tolerance, and torsion angle out-of-tolerance.

[0073] Blade profile reconstruction: The blade profile of blades with machining defects is re-fitted and reconstructed, enabling designers to perform numerical simulation analysis and evaluation of blade profile defects.

[0074] Installation angle: This angle βy represents the degree of tilt of the blade when it is installed in the blade cascade, such as... Figure 1 As shown, it is the angle between the chord line of the blade shape and the frontal line of the blade. The chord line is the straight line b connecting the leading edge point and the trailing edge point of the blade shape, and the frontal line is the straight line connecting the leading edge point and the trailing edge point of all blade shapes respectively.

[0075] This invention provides a method for reconstructing an aero-engine blade model, comprising the following steps:

[0076] Step 1: Construct a theoretical two-dimensional model of the blade based on the parameters of each discrete point in the design parameters. Existing modeling methods can be used to construct the theoretical blade model. The blade two-dimensional model is a two-dimensional model in rectangular coordinates.

[0077] Step 2: Determine the type of deviation in the blades formed after processing.

[0078] In step two above, the type of deviation is selected from one of the following: profile deviation, blade leading edge deviation, position deviation, and torsion angle deviation.

[0079] Among them, profile deviation refers to the deviation between the blade profile after processing and the theoretical profile.

[0080] Blade leading edge deviation refers to the deviation between the shape of the blade leading edge after processing and the theoretical shape.

[0081] Position deviation refers to the deviation between the position of the blade after processing and the theoretical position.

[0082] Torsion angle deviation refers to the deviation between the torsion angle of the blade after processing and the theoretical torsion angle.

[0083] Step 3: Adjust the constructed theoretical blade two-dimensional model according to the type of deviation to obtain the actual blade two-dimensional model.

[0084] If the error type is an error in a part of the blade, then only the theoretical blade two-dimensional model of that part is corrected; if the error type is an error in the entire blade, then the entire theoretical blade two-dimensional model is corrected.

[0085] Specifically, in step three above, it is necessary to adjust the constructed two-dimensional model according to the different types of out-of-tolerance situations.

[0086] Scenario 1: If the out-of-tolerance type is profile out-of-tolerance, adjust the constructed 2D model according to the following steps:

[0087] First, the normal direction of each discrete point in the two-dimensional model of the theoretical blade is calculated.

[0088] Secondly, the profile change of the actual blade relative to the theoretical blade at each discrete point in the two-dimensional model of the theoretical blade is calculated. This can be achieved by using sensors to measure the parameter values ​​of the actual blade at each discrete point, and then calculating the difference based on the parameter values ​​of the theoretical blade at those discrete points. This difference represents the profile change at a given discrete point.

[0089] Finally, the profile variation is superimposed on the normal direction of each discrete point in the theoretical blade's two-dimensional model to obtain the actual blade's two-dimensional model. In this step, if the profile variation at each discrete point of the theoretical blade is the same, then the same profile variation is directly superimposed on the normal direction of each discrete point. The uniformity of the blade profile variation can be determined by measuring the waveform of the actual blade. If it is uniform, then only the profile variation at certain discrete points needs to be calculated. If the profile variation at each discrete point of the theoretical blade is different, then the corresponding profile variation is superimposed on the normal direction of each discrete point.

[0090] Specifically, if the profile change at each discrete point of the theoretical blade is not uniform, the profile change at each discrete point can be calculated using the following formula (I).

[0091]

[0092] Among them, A i K represents the profile amplitude. i α is the number of cycles of profile variation. i X is the phase angle of the profile change; X is the coordinate value along the arc length direction of the airfoil.

[0093] Profile amplitude refers to the peak value of the waveform obtained by comparing the theoretical blade parameters with the measured actual blade parameters.

[0094] The number of profile variation cycles refers to the number of peaks and troughs in the waveform obtained by comparing the theoretical blade parameters with the measured actual blade parameters. A pair of peaks and troughs includes one or more peaks and one or more troughs in a certain area.

[0095] The profile change phase angle is a constant, and its value can be the same as the number of profile change cycles.

[0096] In the above formula (I), α i Greater than or equal to -1 and less than 1. A i Both Ki can be selected values.

[0097] The following introduces several specific methods for reconstructing leaf profile deviation.

[0098] 1. Leaf profile adjustment:

[0099] The steps for constructing the profile adjustment leaf geometry are as follows:

[0100] 1) Convert the input geometry into a contour surface geometry leaf shape;

[0101] 2) Construct a two-dimensional airfoil by selecting axial and circumferential coordinates based on the contour surface airfoil;

[0102] 3) Determine the normal direction of each discrete point of the two-dimensional airfoil;

[0103] 4) Calculate the profile variation at each discrete point position of the two-dimensional airfoil;

[0104] 5) Based on the variation of profile at each discrete point of the two-dimensional leaf shape superimposed along the normal direction;

[0105] 6) Output contour geometry of the blade with variable profile.

[0106] As mentioned above, leaf profile adjustment is divided into two cases: local adjustment and full adjustment; full adjustment is further divided into uniform profile adjustment and non-uniform profile adjustment, which are described below.

[0107] 1.1 Adjustment of uniform contour

[0108] The profile of each discrete point of the two-dimensional airfoil changes uniformly across all cross-sections, achieving the desired effect (see [link]). Figure 2a , Figure 2b and Figure 2c . Figure 2a In the diagram, the dashed line represents the original leaf shape, and the solid line represents the leaf shape after contour uniformity adjustment. In other graphics, the dashed line also represents the original leaf shape, and the solid line represents the adjusted leaf shape.

[0109] 1.2 Adjustment of Non-uniform Contour

[0110] The profile deviation of each discrete point in the two-dimensional air profile at each cross section varies non-uniformly. The method for realizing the profile deviation variation curve is as follows:

[0111] 1) The discrete points are connected by a line from the leading edge along the suction surface to the trailing edge, and then from the trailing edge along the pressure surface to the leading edge;

[0112] 2) Construct a contour variation curve along the direction of 1), with the horizontal axis representing the dimensionless distribution of arc length and the vertical axis representing the amount of contour variation;

[0113] 3) The formula for the contour variation curve is shown in formula (1) below.

[0114]

[0115] Among them: A i This refers to: profile amplitude;

[0116] K i This refers to the number of cycles of profile variation.

[0117] α i This refers to the phase angle of the profile change;

[0118] X refers to the coordinate value along the arc length of the leaf shape.

[0119] Based on the above method for generating profile variation curves, a non-uniform profile variation airfoil geometry can be constructed. The implementation effect of a single non-uniform profile variation is shown in [link to documentation]. Figures 3a to 3c As shown, the effect of achieving non-uniform variation in composite profile is as follows: Figures 4a to 4c As shown. Among them, Figure 3d The waveform diagram of the amplitude variation of the non-uniform profile is used to generate the non-uniform profile airfoil. Figure 4d The waveform diagram of the amplitude variation of the composite profile non-uniform variation profile is used to generate the composite non-uniform profile airfoil.

[0120] 1.3 Local contour adjustment

[0121] Variations in the local profile of the two-dimensional airfoil at each cross-section achieve the effect of local bulges or depressions, as shown in the image. Figures 5a to 5c As shown.

[0122] Scenario 2: If the out-of-tolerance type is leading edge shape out-of-tolerance, adjust the constructed 2D model according to the following steps:

[0123] First, the installation angle rectangular coordinate system of the theoretical blade two-dimensional model is calculated, and the coordinates of the theoretical blade two-dimensional model in the original rectangular coordinate system are transformed to the installation angle rectangular coordinate system. The coordinates of the theoretical blade leading edge point are (0, 0), and the coordinates of the theoretical blade trailing edge point are (BT, 0), where BT is the chord length.

[0124] Secondly, based on the measured coordinates of discrete points on the leading edge, leaf basin, and underside of the actual leaf, the positions of the discrete points on the leading edge, leaf basin, and underside of the theoretical leaf are moved.

[0125] Next, based on the positions of discrete points on the leading edge, local areas of the blade base, and local areas of the blade back after displacement, a new model is created to obtain a two-dimensional model of the actual blade in a Cartesian coordinate system at the installation angle. The configuration refers to connecting discrete points with curves in a specific order. For example, the order could be from the trailing edge along the suction surface to the leading edge, and then from the leading edge along the pressure surface to the trailing edge.

[0126] Specifically, Bézier curves, spline curves, or polynomial curves can be used to reshape the leading edge, leaf base, and leaf back after displacement. Furthermore, the curve where the leading edge point is located after reshaping should be first-order continuous and / or the curves at the junction of the leaf base curve, leaf back curve, and leaf body should be second-order continuous.

[0127] Finally, an inverse coordinate transformation is used to transform the reconstructed model of the actual blade installation angle in the rectangular coordinate system back to the original rectangular coordinate system to obtain a two-dimensional model of the actual blade.

[0128] The following describes a specific embodiment for reconstructing the leading edge shape of a leaf.

[0129] The steps for constructing the leading edge shape adjustment leaf geometry are as follows:

[0130] 1) Convert the input geometry into a contour surface geometry leaf shape;

[0131] 2) Construct a two-dimensional airfoil by selecting axial and circumferential coordinates based on the contour surface airfoil;

[0132] 3) Based on the leading and trailing edge points of the two-dimensional blade, obtain the installation angle, transform the coordinates so that the horizontal coordinate is the chord length direction, the leading edge point is (0, 0) and the trailing edge point is (BT, 0), where BT is the chord length value;

[0133] 4) Based on the two-dimensional leaf shape after coordinate transformation, the leading edge is reshaped, and a Bezier curve is used for each of the pot and back curves: the leading edge point can be translated up, down, left and right to ensure the first-order continuity of the leading edge point and the second-order continuity at the connection between the leaf pot, the back curve and the leaf body.

[0134] 5) Based on the reconstructed leading edge shape of the two-dimensional leaf profile, coordinate transformation, and return to the original coordinate system;

[0135] 6) Output the 2D model of the contour surface geometric airfoil after the leading edge is reconfigured.

[0136] The leading edge shape adjustment method uses a Bezier curve for both the suction and pressure surfaces. The curves must ensure second-order continuity at the connection between the right boundary and the blade body; and at the connection point of the leading edge, the two curves must ensure at least first-order continuity.

[0137] By using the above-mentioned modeling method for adjusting the leading edge shape, typical geometric structures commonly encountered in blade processing, such as leading edge deflection (upward or downward), leading edge sharpness, leading edge bluntness, and leading edge necking, can be simulated for numerical simulation analysis, providing support for processing and manufacturing. Figure 6a and Figure 6b This is a schematic diagram illustrating the effect of the pointed leading edge. Figure 7a and Figure 7b This is a schematic diagram illustrating the effect of a blunt leading edge. Figure 8a and Figure 8b This diagram illustrates the effect of tilting the suction surface. Figure 9a and Figure 9b This diagram illustrates the effect of the pressure surface deflecting at the leading edge.

[0138] Furthermore, by adjusting the shape of the leading edge of the blade and coordinating the changes in the cross sections of the blade along the radial direction, geometric modeling of leading edge impact damage can be achieved.

[0139] Scenario 3: If the error type is torsion angle error, then adjust the constructed 2D model using the following steps:

[0140] First, calculate the centroid coordinates of each section of the two-dimensional model of the theoretical blade.

[0141] Secondly, based on the measured coordinates of the centroids of each section of the actual blade, the torsional angle change of the centroid of each section of the theoretical blade relative to the centroid of each section of the actual blade is calculated.

[0142] Finally, based on the torsion angle of each section, the two-dimensional model of the theoretical blade is torsioned based on the center of gravity of the theoretical blade to obtain the corrected two-dimensional model of the actual blade.

[0143] The following describes a specific embodiment for reconstructing the out-of-tolerance airfoil twist angle.

[0144] 1) Convert the input geometry into a contour surface geometry leaf shape.

[0145] 2) Construct a two-dimensional air profile by selecting axial and circumferential coordinates based on the contour surface air profile.

[0146] 3) Calculate the centroid coordinates of each airfoil section.

[0147] 4) Based on the input torsion angle change value, perform torsional changes on each cross-section air profile based on the center of gravity.

[0148] 5) Output contour geometry airfoils with variable twist angle.

[0149] The effect of varying the twist angle of the two-dimensional airfoil at each cross-section is shown in the figure. Figures 10a to 10c .

[0150] Scenario 4: If the error type is positional error, then adjust the constructed 2D model using the following steps:

[0151] First, calculate the centroid coordinates of each section of the two-dimensional model of the theoretical blade.

[0152] Secondly, measure the centroid coordinates of each section of the actual blade.

[0153] Next, calculate the positional variation of the centroid coordinates of each section of the theoretical blade relative to the actual blade centroid coordinates.

[0154] Finally, based on the positional variation values ​​of the centroid coordinates of each section of the theoretical blade, the two-dimensional model of the theoretical blade is transformed by translational changes based on the centroid to obtain the two-dimensional model of the actual blade.

[0155] The following describes a specific embodiment of a method for constructing a blade with out-of-position tolerance.

[0156] 1) Convert the input geometry into a contour surface geometry leaf shape.

[0157] 2) Construct a two-dimensional air profile by selecting axial and circumferential coordinates based on the contour surface air profile.

[0158] 3) Determine the centroid coordinates of each airfoil section.

[0159] 4) Based on the input positional change value, perform translational changes on each cross-section airfoil based on the center of gravity.

[0160] 5) Output the contour geometry of the airfoil with variable position.

[0161] As can be seen, the above technical solution can locally adjust the theoretical blade profile coordinates based on the blade profile machining deviations, reconstructing blade profiles that meet various deviation conditions, and supporting deviation analysis and evaluation. Numerical simulations can be performed for different blade deviation forms to analyze the impact of different deviation types on blade performance, thus providing theoretical support for the acceptance of blades with deviations. Based on the methods presented in this paper, geometric models can be constructed as needed to analyze and evaluate machining problems such as blade scratches, local bulges / dents, etc.

[0162] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only used to facilitate the description of this invention and to simplify the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this invention.

[0163] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. However, these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for reconstructing an aero-engine blade model, characterized in that, Includes the following steps: A two-dimensional model of the theoretical blade is constructed based on the parameters of each discrete point of the blade in the design parameters. Determine the type of deviation in the actual blade formed after processing; the type of deviation is selected from one of the following: blade leading edge deviation, position deviation, and twist angle deviation; Adjust the constructed theoretical two-dimensional model of the blade according to the type of deviation to obtain the two-dimensional model of the actual blade; If the out-of-tolerance type is leading edge shape out-of-tolerance, adjust the constructed two-dimensional model according to the following steps: Calculate the installation angle rectangular coordinate system of the theoretical blade two-dimensional model, and transform the coordinates of the theoretical blade two-dimensional model in the original rectangular coordinate system to the installation angle rectangular coordinate system. The coordinates of the theoretical blade leading edge point are (0, 0), and the coordinates of the theoretical blade trailing edge point are (BT, 0), where BT is the chord length. Based on the measured coordinates of discrete points on the actual leaf at the leading edge, local area of ​​the leaf basin, and local area of ​​the leaf underside, the positions of the discrete points on the theoretical leaf at the leading edge, local area of ​​the leaf basin, and local area of ​​the leaf underside are moved. Based on the positions of discrete points in the leading edge, local area of ​​the leaf basin, and local area of ​​the leaf back after displacement, the model is reshaped to obtain a two-dimensional model of the actual blade in the rectangular coordinate system of the installation angle. By employing inverse coordinate transformation, the model obtained from the reconstruction of the actual blade installation angle in the rectangular coordinate system is transformed back to the original rectangular coordinate system to obtain a two-dimensional model of the actual blade.

2. The method for reconstructing an aero-engine blade model according to claim 1, characterized in that, The leading edge, local areas of the leaf basin, and local areas of the leaf underside after displacement are reshaped using Bézier curves, spline curves, or polynomial curves.

3. The method for reconstructing an aero-engine blade model according to claim 2, characterized in that, The curve at the leading edge point after reconfiguration is first-order continuous and / or the curve at the junction of the leaf basin curve, leaf back curve and the unreconfigured leaf body is second-order continuous.

4. The method for reconstructing an aero-engine blade model according to claim 1, characterized in that, If the error type is torsion angle error, then the following steps should be taken to adjust the constructed two-dimensional model: Calculate the centroid coordinates of each section of the two-dimensional model of the theoretical blade; Based on the measured centroid coordinates of each section of the actual blade, calculate the change in torsional angle of each section of the theoretical blade relative to the centroid of each section of the actual blade. Based on the torsion angle of each section, the two-dimensional model of the theoretical blade is torsionped based on the center of gravity of the theoretical blade to obtain the corrected two-dimensional model of the actual blade.

5. The method for reconstructing an aero-engine blade model according to claim 1, characterized in that, If the error type is location error, then the following steps should be taken to adjust the constructed two-dimensional model: Calculate the centroid coordinates of each section of the two-dimensional model of the theoretical blade; Measure the centroid coordinates of each section of the actual blade; Calculate the positional variation of the centroid coordinates of each section of the theoretical blade relative to the actual blade centroid coordinates; Based on the positional variation values ​​of the centroid coordinates of each section of the theoretical blade, the two-dimensional model of the theoretical blade is transformed by translational changes based on the centroid to obtain the two-dimensional model of the actual blade.

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