Blade dynamic airfoil point distribution reconstruction method, device, equipment, medium and product

Abstract

The invention discloses a blade dynamic airfoil profile point distribution reconstruction method and device, equipment, a medium and a product, and relates to the technical field of helicopter aerodynamics, and the method comprises the steps: obtaining the curvature of each original airfoil profile point on a blade according to the coordinate of each original airfoil profile point on the blade; the original airfoil profile point is an airfoil profile point before reconstruction; obtaining the curvature of each reconstructed airfoil profile point on the blade according to the curvature of each original airfoil profile point on the blade; obtaining the serial number of each reconstructed airfoil profile point according to the curvature of each reconstructed airfoil profile point and the total number of the original airfoil profile points; the serial number of each original airfoil profile point and the serial number of each reconstructed airfoil profile point are used as interpolation independent variables, the coordinates of each original airfoil profile point are used as interpolation dependent variables, interpolation processing is carried out to obtain the coordinates of each reconstructed airfoil profile point, the reconstructed airfoil profile points are drawn according to the coordinates of each reconstructed airfoil profile point, and blade airfoil profile point distribution reconstruction is completed. According to the method, the number of airfoil profile points can be reduced, and the airfoil profile can be accurately described.

Description

Technical Field

[0001] The present application relates to the technical field of helicopter aerodynamics, and in particular to a method, device, equipment, medium and product for reconstructing the distribution of dynamic airfoil points of a blade. Background Art

[0002] When using computational fluid dynamics (CFD) methods to conduct numerical simulation research, the grid is the basis of all calculation work, and the distribution of airfoil points is the basis for constructing the grid, which is directly related to the quality and quantity of the grid. Figure 4 The process of creating the blade surface mesh is demonstrated. First, a large number of data points are needed to fit the airfoil contour, thus forming any section of the blade. Then, the blade shape is simulated through operations such as stretching and twisting. However, accurate shape modeling will significantly increase the number of blade surface mesh points, which is a burden for subsequent CFD calculations. Therefore, a blade airfoil point distribution reconstruction method is needed that can reduce the number of airfoil points and accurately describe the airfoil contour. Summary of the invention

[0003] The purpose of the present application is to provide a method, device, equipment, medium and product for reconstructing the distribution of dynamic airfoil points of a blade, which can reduce the number of airfoil points and accurately describe the airfoil profile.

[0004] To achieve the above objectives, this application provides the following solutions:

[0005] In a first aspect, the present application provides a method for reconstructing the distribution of dynamic airfoil points of a blade, comprising:

[0006] Obtaining the curvature of each original airfoil point on the blade according to the coordinates of each original airfoil point on the blade; the original airfoil point is the airfoil point before reconstruction;

[0007] The curvature of each reconstructed airfoil point on the blade is obtained according to the curvature of each original airfoil point on the blade;

[0008] Obtaining the serial number of each reconstructed airfoil point according to the curvature of each reconstructed airfoil point and the total number of original airfoil points;

[0009] The serial numbers of the original airfoil points and the serial numbers of the reconstructed airfoil points are used as interpolation independent variables, and the coordinates of the original airfoil points are used as interpolation dependent variables. Interpolation processing is performed to obtain the coordinates of each reconstructed airfoil point. The reconstructed airfoil points are drawn according to the coordinates of each reconstructed airfoil point to complete the reconstruction of the airfoil point distribution of the blade.

[0010] Optionally, obtaining the curvature of each reconstructed airfoil point on the blade according to the curvature of each original airfoil point on the blade specifically includes:

[0011] Reconstructing the curvature of each original airfoil point on the blade to obtain an updated curvature of each original airfoil point on the blade;

[0012] The serial number of each original airfoil point and the reconstructed serial number of each reconstructed airfoil point are used as interpolation independent variables, and the updated curvature of each original airfoil point is used as the interpolation dependent variable. Interpolation processing is performed to obtain the curvature of each reconstructed airfoil point; the reconstruction serial number of each reconstructed airfoil point is obtained according to the preset serial number of each reconstructed airfoil point, the preset total number of reconstructed airfoil points and the total number of original airfoil points.

[0013] Optionally, reconstructing the curvature of each original airfoil point on the blade to obtain an updated curvature of each original airfoil point on the blade specifically includes:

[0014] Reconstruct the curvature of each original airfoil point on the blade based on a set threshold;

[0015] The reconstructed curvature of each original airfoil point on the blade is smoothed to obtain the smoothed curvature of each original airfoil point on the blade;

[0016] The updated curvature of each original airfoil point on the blade is calculated based on the smoothed curvature of each original airfoil point on the blade.

[0017] Optionally, the calculating the updated curvature of each original airfoil point on the blade based on the smoothed curvature of each original airfoil point on the blade specifically includes:

[0018] According to the formula Calculate the updated curvature of the i-th original airfoil point, where represents the updated curvature of the i-th original airfoil point, represents the smooth curvature of the i-th original airfoil point, imax represents the total number of original airfoil points, and σ represents the density coefficient.

[0019] Optionally, according to the formula Calculate the reconstruction sequence number of the reconstructed airfoil point, where: represents the reconstruction number of the reconstructed airfoil point with the preset number j, imax represents the total number of original airfoil points, and jmax represents the preset total number of reconstructed airfoil points.

[0020] Optionally, obtaining the sequence number of each reconstructed airfoil point according to the curvature of each reconstructed airfoil point and the total number of original airfoil points specifically includes:

[0021] According to the formula Calculate the transformation coefficient of the reconstructed airfoil point with the preset sequence number j, where A j represents the transformation coefficient of the reconstructed airfoil point with the preset sequence number j, represents the curvature of the reconstructed airfoil point with preset sequence number j, represents the curvature of the reconstructed airfoil point with a preset sequence number of j+1;

[0022] According to the formula Calculate the sequence interval of the reconstructed airfoil point with the preset sequence number j, where B j represents the sequence number interval of the reconstructed airfoil points with the preset sequence number j, imax represents the total number of original airfoil points, and jmax represents the preset total number of reconstructed airfoil points;

[0023] According to the formula Calculate the sequence number of the reconstructed airfoil point whose preset sequence number is j+1, where: represents the sequence number of the reconstructed airfoil point whose preset sequence number is 1, Indicates the number of the reconstructed airfoil point whose preset number is j+1.

[0024] In a second aspect, the present application provides a device for reconstructing the distribution of dynamic airfoil points of a blade, comprising:

[0025] Obtaining the curvature of each original airfoil point on the blade according to the coordinates of each original airfoil point on the blade; the original airfoil point is the airfoil point before reconstruction;

[0026] An acquisition module, used to obtain the curvature of each original airfoil point on the blade according to the coordinates of each original airfoil point on the blade; the original airfoil point is the airfoil point before reconstruction;

[0027] A reconstructed airfoil point curvature determination module is used to obtain the curvature of each reconstructed airfoil point on the blade according to the curvature of each original airfoil point on the blade;

[0028] A reconstructed airfoil point sequence number calculation module is used to obtain the sequence number of each reconstructed airfoil point according to the curvature of each reconstructed airfoil point and the total number of original airfoil points;

[0029] The airfoil point distribution reconstruction module is used to use the serial numbers of each original airfoil point and the serial numbers of each reconstructed airfoil point as interpolation independent variables, and the coordinates of each original airfoil point as interpolation dependent variables, perform interpolation processing to obtain the coordinates of each reconstructed airfoil point, draw the reconstructed airfoil point according to the coordinates of each reconstructed airfoil point, and complete the reconstruction of the airfoil point distribution of the blade.

[0030] In a third aspect, the present application provides a computer device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement any of the above-described methods for reconstructing the dynamic airfoil point distribution of a blade.

[0031] In a fourth aspect, the present application provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements any of the above-described methods for reconstructing the dynamic airfoil point distribution of a blade.

[0032] In a fifth aspect, the present application provides a computer program product, including a computer program, which, when executed by a processor, implements any of the above-mentioned methods for reconstructing the dynamic airfoil point distribution of a blade.

[0033] According to the specific embodiments provided in this application, this application discloses the following technical effects:

[0034] The present application provides a method, device, equipment, medium and product for reconstructing the distribution of dynamic airfoil points of a blade. The method comprises the following steps: obtaining the serial number of each reconstructed airfoil point according to the curvature of each reconstructed airfoil point and the total number of original airfoil points; using the serial number of each original airfoil point and the serial number of each reconstructed airfoil point as interpolation independent variables, and using the coordinates of each original airfoil point as interpolation dependent variables, performing interpolation processing to obtain the coordinates of each reconstructed airfoil point. The point density can be adaptively adjusted according to the curvature of the airfoil profile, thereby solving the problem of increasing the number of grid points on the blade surface and achieving the technical effect of reducing the number of airfoil points and accurately describing the airfoil profile. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0036] Figure 1 This is an application environment diagram of a method for reconstructing the distribution of dynamic airfoil points of a blade in one embodiment of the present application;

[0037] Figure 2 A flowchart of a method for reconstructing the distribution of dynamic airfoil points of a blade provided in one embodiment of the present application;

[0038] Figure 3 A specific flow chart of a method for reconstructing the distribution of dynamic airfoil points of a blade provided in one embodiment of the present application;

[0039] Figure 4 Schematic diagram for blade surface mesh generation;

[0040] Figure 5 It is a comparison diagram of the original airfoil points and the reconstructed airfoil points;

[0041] Figure 6 It is the distribution diagram of the original airfoil points;

[0042] Figure 7 Update the curvature distribution diagram for the original airfoil points;

[0043] Figure 8 A schematic diagram of the structure of a computer device provided in one embodiment of the present application. DETAILED DESCRIPTION

[0044] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0045] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the present application is further described in detail below with reference to the accompanying drawings and specific implementation methods.

[0046] The method for reconstructing the dynamic airfoil point distribution of a blade provided in the embodiment of the present application can be applied to Figure 1 In the application environment shown, the terminal 102 communicates with the server 104 through a network. The data storage system can store data that the server 104 needs to process. The data storage system can be set up separately, integrated on the server 104, or placed on the cloud or other servers. The terminal 102 may send the coordinates of each original airfoil point on the blade to the server 104. After receiving the coordinates of each original airfoil point on the blade, the server 104 obtains the curvature of each original airfoil point on the blade according to the coordinates of each original airfoil point on the blade; the original airfoil point is the airfoil point before reconstruction; the curvature of each reconstructed airfoil point on the blade is obtained according to the curvature of each original airfoil point on the blade; the serial number of each reconstructed airfoil point is obtained according to the curvature of each reconstructed airfoil point and the total number of original airfoil points; the serial number of each original airfoil point and the serial number of each reconstructed airfoil point are used as interpolation independent variables, and the coordinates of each original airfoil point are used as interpolation dependent variables, and the coordinates of each original airfoil point are interpolated to obtain the coordinates of each reconstructed airfoil point, and the reconstructed airfoil point is drawn according to the coordinates of each reconstructed airfoil point, so as to complete the reconstruction of the airfoil point distribution of the blade. The server 104 may feed back the obtained coordinates of each reconstructed airfoil point to the terminal 102. In addition, in some embodiments, the method for reconstructing the dynamic airfoil point distribution of the blade can also be implemented independently by the server 104 or the terminal 102. For example, the terminal 102 can directly perform blade airfoil point distribution reconstruction processing on the coordinates of each original airfoil point on the blade, or the server 104 can obtain the coordinates of each original airfoil point on the blade from the data storage system and perform blade airfoil point distribution reconstruction processing on the coordinates of each original airfoil point on the blade.

[0047] The terminal 102 may be, but is not limited to, various desktop computers, laptop computers, smart phones, tablet computers, IoT devices, and portable wearable devices. The IoT devices may be smart speakers, smart TVs, smart air conditioners, smart vehicle-mounted devices, etc. The portable wearable devices may be smart watches, smart bracelets, head-mounted devices, etc. The server 104 may be implemented as an independent server or a server cluster consisting of multiple servers, or may be a cloud server.

[0048] In an exemplary embodiment, Figure 2 and Figure 3 As shown, a method for reconstructing the distribution of dynamic airfoil points of a blade is provided. The method is executed by a computer device, and can be executed by a computer device such as a terminal or a server alone, or can be executed by a terminal and a server together. In the embodiment of the present application, the method is applied to Figure 1 The server 104 in the example is used for explanation, and the steps include the following steps 201 to 204.

[0049] in:

[0050] Step 201: obtaining the curvature of each original airfoil point on the blade according to the coordinates of each original airfoil point on the blade; the original airfoil point is the airfoil point before reconstruction.

[0051] Step 202: Obtain the curvature of each reconstructed airfoil point on the blade according to the curvature of each original airfoil point on the blade.

[0052] Step 203: obtaining the sequence number of each reconstructed airfoil point according to the curvature of each reconstructed airfoil point and the total number of original airfoil points.

[0053] Step 204: Using the serial numbers of each original airfoil point and the serial numbers of each reconstructed airfoil point as interpolation independent variables, and using the coordinates of each original airfoil point as interpolation dependent variables, interpolation processing is performed to obtain the coordinates of each reconstructed airfoil point, and the reconstructed airfoil points are drawn according to the coordinates of each reconstructed airfoil point to complete the reconstruction of the blade airfoil point distribution. Figure 5 The distribution of the original airfoil points and the reconstructed airfoil points is shown, where Figure 5 Part (a) shows the distribution of the original airfoil points when the total number of original airfoil points is 131. Figure 5 Part (b) shows the distribution of reconstructed airfoil points obtained by processing the original airfoil points with 131 reconstructed points using the blade dynamic airfoil point distribution reconstruction method of the present application, which is equal to the number of original points. It can be seen that even with the same number of points, the airfoil points reconstructed by the present application are more concentrated in the area with large curvature, such as the enlarged view of the airfoil head, which is conducive to a more detailed description of the part with large curvature of the airfoil. Figure 5Part (c) shows the distribution of reconstructed airfoil points obtained by processing the original airfoil points with 65 reconstructed points using the dynamic airfoil point distribution reconstruction method of the present application, which is about half the number of original points. It can be seen that the reconstruction method of the present application can still characterize the airfoil profile while reducing the number of points. Figure 5 It can be seen that the reconstructed airfoil points are adaptively encrypted at locations with large curvature and adaptively sparse at areas with small curvature. Even if the number of reconstructed airfoil points is only half of the number of original airfoil points, it still has excellent airfoil shape fitting capabilities.

[0054] By implementing the above steps 201 to 204, the present application can adaptively adjust the point density according to the curvature of the airfoil profile, and can still accurately describe the airfoil profile when reducing the number of airfoil points.

[0055] In another exemplary embodiment of the present application, before step 201 , the process further includes: reading in original airfoil point coordinates.

[0056] The storage form of the original airfoil points is shown in Table 1, where i max Represents the total number of original airfoil points, interpolation independent variable The original airfoil point number is equal to that in equation (1). The superscript (ori) of the parameter indicates that the parameter is the original airfoil point. The x and y coordinates of the original airfoil point are known quantities. The distribution of each point is as follows: Figure 6 shown.

[0057]

[0058] Table 1 Coordinates of original airfoil points

[0059]

[0060] In another exemplary embodiment of the present application, the above step 201 is replaced by the following steps:

[0061] Step 2011: Calculate the curvature of the original point.

[0062] The coordinates of the current point as the i-th original airfoil point are , combining the previous point (the i-1th original airfoil point) and the next point (the i+1th original airfoil point) to form a triangle, with each side having a length of l a (edge ​​formed by the next point and the current point), l b (the edge formed by the next point and the previous point) and l c (The edge formed by the previous point and the current point), the calculation formula is as follows (2). Using the cosine theorem, we can get l b The corresponding angle is θ as shown in formula (3), and then the curvature of the i-th original airfoil point can be obtained by formula (4): However, the curvature obtained at this time only includes the original airfoil points i=2, 3, ..., imax-1. The curvature of the first original airfoil point i=1 and the last original airfoil point i=imax requires the use of boundary conditions.

[0063]

[0064]

[0065]

[0066] Step 2012: Set boundary conditions.

[0067] The curvature of the first original airfoil point and the last original airfoil point is set equal to the curvature of the adjacent original airfoil point, so the relationship of formula (5) must be satisfied. So far, the curvature of each original airfoil point is obtained.

[0068]

[0069] That is, the curvature of each original airfoil point on the blade is calculated according to equations (2) to (5).

[0070] In another exemplary embodiment of the present application, step 202 is replaced by the following steps:

[0071] Step 2021: reconstruct the curvature of each original airfoil point on the blade to obtain an updated curvature of each original airfoil point on the blade.

[0072] Step 2022: Using the serial number of each original airfoil point and the reconstructed serial number of each reconstructed airfoil point as interpolation independent variables, and using the updated curvature of each original airfoil point as the interpolation dependent variable, interpolation processing is performed to obtain the curvature of each reconstructed airfoil point; the reconstruction serial number of each reconstructed airfoil point is obtained based on the preset serial number of each reconstructed airfoil point, the preset total number of reconstructed airfoil points and the total number of original airfoil points.

[0073] In another exemplary embodiment of the present application, step 2021 is replaced by the following steps:

[0074] The curvature of each original airfoil point on the blade is reconstructed based on the set threshold.

[0075] The reconstructed curvature of each original airfoil point on the blade is smoothed to obtain the smoothed curvature of each original airfoil point on the blade.

[0076] The updated curvature of each original airfoil point on the blade is calculated based on the smoothed curvature of each original airfoil point on the blade.

[0077] In another exemplary embodiment of the present application, the curvature of each original airfoil point on the blade is reconstructed based on a set threshold, specifically by adding a curvature limiter.

[0078] Due to the influence of numerical errors, the curvature of the airfoil points in the local area may be too large or too small, which will cause the distribution of the reconstructed airfoil points to be over-concentrated or over-sparse. Therefore, it is necessary to limit the curvature of the calculated original airfoil points, as shown in formula (6).

[0079]

[0080] If the curvature of a point is less than 0.3, the curvature of the point is taken as 0.3; if the curvature of a point is greater than 30, the curvature of the point is taken as 30; if the curvature is between 0.3 and 30, no modification is made. The thresholds of 0.3 and 30 here are given based on experience, and other values ​​can also be used.

[0081] In another exemplary embodiment of the present application, the reconstructed curvature of each original airfoil point on the blade is smoothed to obtain the smoothed curvature of each original airfoil point on the blade, that is, the curvature of the original point is smoothed, and the specific method is as shown in formula (7):

[0082]

[0083] The average curvature of nearby points is used as the smoothed curvature, where: Represents the smoothed curvature of the i-th original airfoil point. For the internal original airfoil points (i=3,4,…,imax-2), a 5-point smoothing strategy is used; for the original airfoil points at the boundary (i=2 and i=imax-1), a 3-point smoothing strategy is used; for the first and last points, the curvature of the adjacent points is referenced. So far, the curvature of each original airfoil point after smoothing is obtained.

[0084] In another exemplary embodiment of the present application, the updated curvature of each original airfoil point on the blade is calculated based on the smooth curvature of each original airfoil point on the blade, that is, the curvature of the updated original point is specifically calculated using formula (8).

[0085]

[0086] in, represents the updated curvature of the i-th original airfoil point, represents the smooth curvature of the i-th original airfoil point, imax represents the total number of original airfoil points, and σ represents the density coefficient, which is used to control the sparseness of the reconstructed airfoil points. It is a value between 0 and 1. When σ increases and approaches 1, the airfoil points will be concentrated in the area with large curvature; conversely, when σ decreases and approaches 0, the airfoil points will gradually be evenly distributed. Figure 7The updated curvature distribution of the original airfoil points obtained after processing using the method of the present application is shown.

[0087] In another exemplary embodiment of the present application, before using the serial number of each original airfoil point and the reconstructed serial number of each reconstructed airfoil point as interpolation independent variables and the updated curvature of each original airfoil point as the interpolation dependent variable, and performing interpolation processing to obtain the curvature of each reconstructed airfoil point, it also includes: scaling the serial number of the reconstructed point, that is, determining the reconstruction serial number of the reconstructed airfoil point.

[0088] The number of original airfoil points is known to be imax, and its serial number is as shown in formula (1), ranging from 1 to imax. The number of reconstructed airfoil points is set to jmax, and its serial number range is 1 to jmax. The serial number of the reconstructed airfoil point is scaled to the interval of 1 to imax, and the reconstructed serial number of the reconstructed airfoil point is calculated according to formula (9):

[0089]

[0090] The superscript (rec) represents the reconstruction number of the reconstructed airfoil point. represents the reconstruction number of the reconstructed airfoil point with the preset number j, imax represents the total number of original airfoil points, and jmax represents the preset total number of reconstructed airfoil points.

[0091] In another exemplary embodiment of the present application, the sequence number of each original airfoil point and the reconstructed sequence number of each reconstructed airfoil point are used as interpolation independent variables, and the updated curvature of each original airfoil point is used as the interpolation dependent variable, and interpolation processing is performed to obtain the curvature of each reconstructed airfoil point, that is, to calculate the curvature of the reconstructed point, which specifically includes:

[0092] by and the reconstruction number of the reconstructed airfoil point As the interpolation independent variable, the updated curvature of the original airfoil point As the interpolation dependent variable, using cubic spline interpolation (other interpolation methods are also possible) to obtain the curvature of the reconstructed airfoil point with the preset sequence number j as

[0093]

[0094] In another exemplary embodiment of the present application, step 203 is replaced by the following steps:

[0095] Step 2031: Calculate the sequence number interval of the reconstruction points.

[0096] The inverse of the reconstructed airfoil point curvature is used as the transformation coefficient as shown in formula (10), where the transformation coefficient A j The characteristic of is that it is smaller in the area with large curvature and larger in the area with small curvature. j Scaling can obtain the sequence interval B of the reconstructed airfoil pointsj As shown in formula (11).

[0097]

[0098]

[0099] Among them, A j represents the transformation coefficient of the reconstructed airfoil point with the preset sequence number j, represents the curvature of the reconstructed airfoil point with preset sequence number j, represents the curvature of the reconstructed airfoil point with the preset sequence number j+1, B j represents the serial number interval of the reconstructed airfoil points with the preset serial number j, imax represents the total number of original airfoil points, and jmax represents the preset total number of reconstructed airfoil points.

[0100] Step 2032: Update the sequence number of the reconstruction point.

[0101] The starting number of the reconstructed airfoil point is 1 as shown in formula (12). The interval of the reconstructed airfoil point numbers obtained in the previous step is B. j , and the sequence number of the reconstructed airfoil point can be obtained by accumulating As shown in formula (13).

[0102]

[0103]

[0104] in, Indicates the number of the reconstructed airfoil point whose preset number is j+1.

[0105] In another exemplary embodiment of the present application, the above step 204, i.e. updating the coordinates of the reconstructed points and outputting them, is replaced by the following steps:

[0106] The sequence number of the reconstructed airfoil point and As interpolation independent variables, the coordinates of the original airfoil points are and As the interpolation dependent variable, use cubic spline interpolation (other interpolation methods are also possible) to obtain the coordinates of the reconstructed airfoil points and Finally, the coordinates of the reconstructed airfoil points are output one by one and , the reconstructed airfoil points are drawn according to the coordinates of each reconstructed airfoil point to complete the reconstruction of the airfoil point distribution of the blade. So far, all the steps of the adaptive curvature distribution of the airfoil points have been completed.

[0107] The traditional method of reconstructing the distribution of blade airfoil points uses arc length as the interpolation independent variable, which has obvious limitations, because the total arc length after reconstruction is inconsistent with the total arc length of the original airfoil points, which will cause error accumulation and lead to errors in the reconstruction results. This application uses the airfoil point sequence number as the interpolation independent variable, and keeps the interpolation independent variable in the same range by scaling the sequence number, which effectively solves the problem of the traditional reconstruction method.

[0108] Compared with the traditional reconstruction method, the present application has fewer calculation steps, lower calculation amount and higher calculation efficiency. It can not only achieve the purpose of adaptive distribution of airfoil points with curvature, but also use multiple interpolation methods at the same time, effectively improving the simulation accuracy of the airfoil profile.

[0109] The application of this invention can significantly reduce the number of airfoil points. max While maintaining the contour characteristics of the airfoil curve, the number of points required to construct the blade surface mesh is also greatly reduced (a total of j max ·k max grid points, where k max Indicates the number of blade span profiles. Figure 4 ), which significantly improves the modeling efficiency of the blade shape.

[0110] Based on the same inventive concept, the embodiment of the present application also provides a blade dynamic airfoil point distribution reconstruction device for implementing the blade dynamic airfoil point distribution reconstruction method involved above. The implementation scheme for solving the problem provided by the device is similar to the implementation scheme recorded in the above method, so the specific limitations in one or more blade dynamic airfoil point distribution reconstruction device embodiments provided below can refer to the limitations of the blade dynamic airfoil point distribution reconstruction method above, and will not be repeated here.

[0111] In an exemplary embodiment, a device for reconstructing the distribution of dynamic airfoil points of a blade is provided, comprising:

[0112] The acquisition module is used to obtain the curvature of each original airfoil point on the blade according to the coordinates of each original airfoil point on the blade; the original airfoil point is the airfoil point before reconstruction.

[0113] The reconstructed airfoil point curvature determination module is used to obtain the curvature of each reconstructed airfoil point on the blade according to the curvature of each original airfoil point on the blade.

[0114] The reconstructed airfoil point sequence number calculation module is used to obtain the sequence number of each reconstructed airfoil point according to the curvature of each reconstructed airfoil point and the total number of original airfoil points.

[0115] The airfoil point distribution reconstruction module is used to use the serial numbers of each original airfoil point and the serial numbers of each reconstructed airfoil point as interpolation independent variables, and the coordinates of each original airfoil point as interpolation dependent variables, perform interpolation processing to obtain the coordinates of each reconstructed airfoil point, draw the reconstructed airfoil point according to the coordinates of each reconstructed airfoil point, and complete the reconstruction of the airfoil point distribution of the blade.

[0116] In an exemplary embodiment, a computer device is provided. The computer device may be a server or a terminal. The internal structure diagram thereof may be as follows: Figure 8 As shown. The computer device includes a processor, a memory, an input / output interface (Input / Output, referred to as I / O) and a communication interface. The processor, the memory and the input / output interface are connected through a system bus, and the communication interface is connected to the system bus through the input / output interface. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store original airfoil point coordinates. The input / output interface of the computer device is used to exchange information between the processor and an external device. The communication interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a method for reconstructing the distribution of dynamic airfoil points of a blade is implemented.

[0117] Those skilled in the art will understand that Figure 8 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components. In an exemplary embodiment, a computer device is provided, including a memory and a processor, wherein a computer program is stored in the memory, and the processor implements the steps in the above-mentioned method embodiments when executing the computer program.

[0118] In an exemplary embodiment, a computer-readable storage medium is provided, storing a computer program, and when the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0119] In an exemplary embodiment, a computer program product is provided, including a computer program, and when the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0120] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, stored data, displayed data, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties, and the collection, use and processing of relevant data must comply with relevant regulations.

[0121] Those of ordinary skill in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to the memory, database or other medium used in the embodiments provided in the present application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetic random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM may be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM).

[0122] The database involved in each embodiment provided in this application may include at least one of a relational database and a non-relational database. The non-relational database may include a distributed database based on blockchain, etc., but is not limited thereto. The processor involved in each embodiment provided in this application may be a general-purpose processor, a central processing unit, a graphics processor, a digital signal processor, a programmable logic device, a data processing logic device based on quantum computing, etc., but is not limited thereto.

[0123] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0124] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and core ideas of this application. At the same time, for those skilled in the art, according to the ideas of this application, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting this application.

Claims

1. A method for reconstructing the distribution of dynamic airfoil points of a blade, It is characterized in that The method for reconstructing the distribution of dynamic airfoil points of a blade comprises: Obtaining the curvature of each original airfoil point on the blade according to the coordinates of each original airfoil point on the blade; the original airfoil point is the airfoil point before reconstruction; The curvature of each reconstructed airfoil point on the blade is obtained according to the curvature of each original airfoil point on the blade; Obtaining the serial number of each reconstructed airfoil point according to the curvature of each reconstructed airfoil point and the total number of original airfoil points; The serial numbers of the original airfoil points and the serial numbers of the reconstructed airfoil points are used as interpolation independent variables, and the coordinates of the original airfoil points are used as interpolation dependent variables. Interpolation processing is performed to obtain the coordinates of each reconstructed airfoil point. The reconstructed airfoil points are drawn according to the coordinates of each reconstructed airfoil point to complete the reconstruction of the airfoil point distribution of the blade.

2. The method for reconstructing the distribution of dynamic airfoil points of a blade according to claim 1, It is characterized in that The step of obtaining the curvature of each reconstructed airfoil point on the blade according to the curvature of each original airfoil point on the blade specifically includes: Reconstructing the curvature of each original airfoil point on the blade to obtain an updated curvature of each original airfoil point on the blade; The serial number of each original airfoil point and the reconstructed serial number of each reconstructed airfoil point are used as interpolation independent variables, and the updated curvature of each original airfoil point is used as the interpolation dependent variable. Interpolation processing is performed to obtain the curvature of each reconstructed airfoil point; the reconstruction serial number of each reconstructed airfoil point is obtained according to the preset serial number of each reconstructed airfoil point, the preset total number of reconstructed airfoil points and the total number of original airfoil points.

3. The method for reconstructing the distribution of dynamic airfoil points of a blade according to claim 2, It is characterized in that The reconstructing the curvature of each original airfoil point on the blade to obtain the updated curvature of each original airfoil point on the blade specifically includes: Reconstruct the curvature of each original airfoil point on the blade based on a set threshold; The reconstructed curvature of each original airfoil point on the blade is smoothed to obtain the smoothed curvature of each original airfoil point on the blade; The updated curvature of each original airfoil point on the blade is calculated based on the smoothed curvature of each original airfoil point on the blade.

4. The method for reconstructing the distribution of dynamic airfoil points of a blade according to claim 3, It is characterized in that The step of calculating the updated curvature of each original airfoil point on the blade based on the smoothed curvature of each original airfoil point on the blade specifically includes: According to the formula Calculate the updated curvature of the i-th original airfoil point, where Cur i (ori)′ represents the updated curvature of the i-th original airfoil point, Cur i (smo) represents the smooth curvature of the i-th original airfoil point, imax represents the total number of original airfoil points, and σ represents the density coefficient.

5. The method for reconstructing the distribution of dynamic airfoil points of a blade according to claim 2, It is characterized in that According to the formula Calculate the reconstruction sequence number of the reconstructed airfoil point, where represents the reconstruction number of the reconstructed airfoil point with the preset number j, imax represents the total number of original airfoil points, and jmax represents the preset total number of reconstructed airfoil points.

6. The method for reconstructing the distribution of dynamic airfoil points of a blade according to claim 1, It is characterized in that The obtaining of the sequence number of each reconstructed airfoil point according to the curvature of each reconstructed airfoil point and the total number of original airfoil points specifically includes: According to the formula Calculate the transformation coefficient of the reconstructed airfoil point with the preset sequence number j, where A j represents the transformation coefficient of the reconstructed airfoil point with the preset sequence number j, represents the curvature of the reconstructed airfoil point with preset sequence number j, represents the curvature of the reconstructed airfoil point with a preset sequence number of j+1; According to the formula Calculate the sequence interval of the reconstructed airfoil point with the preset sequence number j, where B j represents the sequence number interval of the reconstructed airfoil points with the preset sequence number j, imax represents the total number of original airfoil points, and jmax represents the preset total number of reconstructed airfoil points; According to the formula Calculate the sequence number of the reconstructed airfoil point whose preset sequence number is j+1, where: represents the sequence number of the reconstructed airfoil point whose preset sequence number is 1, Indicates the number of the reconstructed airfoil point whose preset number is j+1.

7. A device for reconstructing the distribution of dynamic airfoil points of a blade, It is characterized in that The blade dynamic airfoil point distribution reconstruction device comprises: An acquisition module, used to obtain the curvature of each original airfoil point on the blade according to the coordinates of each original airfoil point on the blade; the original airfoil point is the airfoil point before reconstruction; A reconstructed airfoil point curvature determination module is used to obtain the curvature of each reconstructed airfoil point on the blade according to the curvature of each original airfoil point on the blade; A reconstructed airfoil point sequence number calculation module is used to obtain the sequence number of each reconstructed airfoil point according to the curvature of each reconstructed airfoil point and the total number of original airfoil points; The airfoil point distribution reconstruction module is used to use the serial numbers of each original airfoil point and the serial numbers of each reconstructed airfoil point as interpolation independent variables, and the coordinates of each original airfoil point as interpolation dependent variables, perform interpolation processing to obtain the coordinates of each reconstructed airfoil point, draw the reconstructed airfoil point according to the coordinates of each reconstructed airfoil point, and complete the reconstruction of the airfoil point distribution of the blade.

8. A computer device, include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for reconstructing the dynamic airfoil point distribution of a blade according to any one of claims 1 to 6.

9. A computer-readable storage medium having a computer program stored thereon, It is characterized in that When the computer program is executed by a processor, the method for reconstructing the distribution of dynamic airfoil points of a blade according to any one of claims 1 to 6 is implemented.

10. A computer program product comprising a computer program, It is characterized in that When the computer program is executed by a processor, the method for reconstructing the distribution of dynamic airfoil points of a blade according to any one of claims 1 to 6 is implemented.

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