Finite element stress analysis method and system for blade disc based on blade simplification

Abstract

The invention discloses a blade disc finite element stress analysis method and system based on blade simplification. According to the blade disc finite element stress analysis method based on blade simplification, when a concentrated mass unit is used for simplifying a blade, a part of a wheel flange including a wheel flange at a radial plate is extracted from a whole wheel flange to serve as a coupling wheel flange; then, a coupling relation is established between the concentrated mass unit and the coupling rim, the rims at the two ends away from the spoke plate are removed, centrifugal loads are prevented from being absorbed by deformation of the rims at the two ends, more centrifugal loads can be transmitted to the spoke plate and the wheel center through the rims at the spoke plate, it is guaranteed that stress at the spoke plate and the wheel center is close to the actual situation, and the service life of the hub is prolonged. The error of a wheel center stress calculation result and a cylindrical section radial stress calculation result is reduced, and the accuracy of finite element stress calculation analysis is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of finite element analysis, and in particular, to a method and system for finite element stress analysis of a bladed disk based on blade simplification, an electronic device, and a computer-readable storage medium. Background Art

[0002] In the finite element stress analysis of a turbine engine bladed disk, in order to improve the calculation efficiency, a cyclic symmetry model or a two-dimensional simplified model is usually used to simplify the blades. Among them, when a two-dimensional simplified model is used for the finite element stress analysis of a turbine engine bladed disk, the engine blades are often replaced by plane stress elements with thickness or lumped mass elements. For example, if the bladed disk contains features such as bolt holes or end teeth, the number of blades distributed circumferentially is often inconsistent with the number of features such as bolt holes or end teeth, or when finite element stress analysis needs to be performed on multi-stage bladed disks, the number of blades in each stage of the multi-stage bladed disks is inconsistent, and lumped mass elements are often used to simulate the blades on the bladed disk. When the engine blades are replaced by plane stress elements with thickness, in order to simulate the centroid position of the blades, it is necessary to set the thickness of the plane stress elements in different regions, which is rather troublesome to operate; while when using lumped mass elements to simulate the turbine engine blades, as Figure 1 and Figure 2 shown, a coupling relationship is usually established between the lumped mass elements and the entire rim where the blades are located, and the centrifugal force of the blades will be evenly applied to the entire rim, which does not conform to the actual situation, resulting in large errors in the calculation results of the hub stress and the radial stress of the cylindrical section, especially when the distance between the hub and the rim is relatively close, the error is even larger, thus resulting in poor accuracy of the finite element stress analysis of the bladed disk. Summary of the Invention

[0003] The present invention provides a method and system for finite element stress analysis of a bladed disk based on blade simplification, an electronic device, and a computer-readable storage medium, which can reduce the errors in the calculation results of the hub stress and the radial stress of the cylindrical section, and improve the accuracy of the finite element stress calculation and analysis.

[0004] According to one aspect of the present invention, a method for finite element stress analysis of a bladed disk based on blade simplification is provided, including the following steps:

[0005] Establish a bladed disk model and calculate the centroid coordinates of a single blade and the mass of the entire circle of blades;

[0006] Extract a part of the rim from the entire rim as a coupling rim, where the coupling rim includes the rim at the web;

[0007] Extract a local disk from the bladed disk model and input the local disk into a finite element calculation model;

[0008] Add lumped mass elements to the finite element calculation model and establish a coupling relationship with the coupling rim. After setting the centroid coordinates and mass of the lumped mass elements based on the centroid coordinates of a single blade and the mass of the entire circle of blades, carry out finite element stress calculation and analysis.

[0009] Further, the process of extracting a part of the rim as the coupling rim from the entire rim includes the following:

[0010] Establish reference planes perpendicular to the axis of the blade disk at the front end of the rim, the rear end of the rim, the root of the front fillet of the web, and the root of the rear fillet of the web respectively.

[0011] Establish a first cutting reference plane between the reference planes at the front end of the rim and the root of the front fillet of the web, and establish a second cutting reference plane between the reference planes at the rear end of the rim and the root of the rear fillet of the web. Among them, both the first cutting reference plane and the second cutting reference plane are perpendicular to the axis of the blade disk.

[0012] Use the first cutting reference plane and the second cutting reference plane to divide the entire rim into three parts, and take the middle part of the rim between the first cutting reference plane and the second cutting reference plane as the coupling rim.

[0013] Further, the first cutting reference plane is located exactly in the middle between the front end of the rim and the root of the front fillet of the web, and the second cutting reference plane is located exactly in the middle between the rear end of the rim and the root of the rear fillet of the web.

[0014] Further, the process of calculating the centroid coordinates of a single blade and the mass of the entire circle of blades includes the following:

[0015] Divide the blade disk into a blade part and a disk part along the rim, select a single blade and measure its volume and centroid coordinates, and then calculate the mass of the entire circle of blades according to the volume, density, and the number of blades.

[0016] Further, for a two-dimensional blade disk model, first cut the disk with a plane passing through the axis of the blade disk, then delete the detailed features on the cutting surface, and take the cutting surface as a local disk two-dimensional sheet.

[0017] For a three-dimensional blade disk model, first determine the corresponding target cyclic symmetric structural features on the disk, then determine the reference plane based on the axis of the target cyclic symmetric structural features and the axis of the blade disk, and then establish two cutting planes passing through the axis of the blade disk and forming an angle of 180° / n with the reference plane on both sides of the reference plane. Cut the disk with the two cutting planes to obtain a disk cyclic symmetric segment including the target cyclic symmetric structural features, where n represents the number of cyclic symmetric structures on the disk.

[0018] Further, for the two-dimensional blade disk model, the mass of the lumped mass unit is the mass of the blades in one full circle, and the centroid coordinates of the lumped mass unit are the centroid coordinates of a single selected blade;

[0019] For the three-dimensional blade disk model, the mass of the lumped mass unit is the mass of the blades in one full circle divided by n. The radial coordinate and the axial coordinate of the centroid of the lumped mass unit are the radial coordinate and the axial coordinate of the centroid of a single selected blade, and the circumferential coordinate of the centroid of the lumped mass unit is located on this reference plane and on the side from the center of the disk to the rim in the circumferential symmetry section of the disk.

[0020] In addition, the present invention also provides a blade disk finite element stress analysis system based on blade simplification, including:

[0021] A blade disk model construction module, configured to establish a blade disk model and calculate the centroid coordinates of a single blade and the mass of the blades in one full circle;

[0022] A coupling rim extraction module, configured to extract a part of the rim from the entire rim as a coupling rim, wherein the coupling rim includes the rim at the web;

[0023] A local disk extraction module, configured to extract a local disk from the blade disk model and input the local disk into a finite element calculation model;

[0024] A finite element analysis module, configured to add lumped mass units in the finite element calculation model, establish a coupling relationship with the coupling rim, and, after setting the centroid coordinates and the mass of the lumped mass units based on the centroid coordinates of a single blade and the mass of the blades in one full circle, perform finite element stress calculation and analysis.

[0025] Further, the coupling rim extraction module includes:

[0026] A reference plane construction unit, configured to respectively establish reference planes perpendicular to the axis of the blade disk at the front end of the rim, the rear end of the rim, the root of the front fillet of the web, and the root of the rear fillet of the web;

[0027] A cutting reference plane construction unit, configured to establish a first cutting reference plane between the reference planes at the front end of the rim and the root of the front fillet of the web, and establish a second cutting reference plane between the reference planes at the rear end of the rim and the root of the rear fillet of the web, wherein both the first cutting reference plane and the second cutting reference plane are perpendicular to the axis of the blade disk;

[0028] A coupling rim extraction unit, configured to divide the entire rim into three parts by using the first cutting reference plane and the second cutting reference plane, and use the middle part of the rim between the first cutting reference plane and the second cutting reference plane as the coupling rim.

[0029] In addition, the present invention further provides an electronic device, including a processor and a memory. A computer program is stored in the memory, and the processor is configured to execute the steps of the method as described above by calling the computer program stored in the memory.

[0030] In addition, the present invention further provides a computer-readable storage medium for storing a computer program for performing finite element stress analysis of a bladed disk based on blade simplification. When the computer program runs on a computer, it executes the steps of the method as described above.

[0031] The present invention has the following beneficial effects:

[0032] In the finite element stress analysis method of a bladed disk based on blade simplification of the present invention, when simplifying the blade using a lumped mass element, a partial rim including the rim at the web is extracted from the entire rim as a coupled rim, and then a coupling relationship is established between the lumped mass element and the coupled rim, eliminating the two ends of the rim far from the web position, preventing the centrifugal load from being absorbed by the deformation of the two ends of the rim, so that the vast majority of the centrifugal load can be transmitted to the web and the wheel center through the rim at the web, ensuring that the stresses at the web and the wheel center are close to the actual situation, reducing the errors in the calculation results of the wheel center stress and the radial stress of the cylindrical section, and improving the accuracy of the finite element stress calculation and analysis.

[0033] In addition, the finite element stress analysis system of a bladed disk based on blade simplification of the present invention also has the above advantages.

[0034] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The present invention will be further described in detail below with reference to the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0036] Figure 1 is a schematic structural diagram of a turbine engine bladed disk;

[0037] Figure 2 is a schematic diagram of establishing a coupling relationship between a lumped mass element and the entire rim where the blade is located in the prior art;

[0038] Figure 3 is a schematic flowchart of the finite element stress analysis method of a bladed disk based on blade simplification according to a preferred embodiment of the present application;

[0039] Figure 4 is Figure 3 a sub-flowchart of step S2 in

[0040] Figure 5 It is a schematic diagram of the principle of extracting the coupling rim from the entire rim in the preferred embodiment of the present application;

[0041] Figure 6 It is a schematic diagram of establishing a coupling relationship between the lumped mass unit and the coupling rim in the preferred embodiment of the present application;

[0042] Figure 7 It is a schematic diagram of the module structure of the bladed disk finite element stress analysis system based on blade simplification in another embodiment of the present application. Specific embodiments

[0043] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the drawings and in conjunction with the embodiments.

[0044] Referring to Figure 3 , the preferred embodiment of the present application provides a bladed disk finite element stress analysis method based on blade simplification, including the following contents:

[0045] Step S1: Establish a bladed disk model and calculate the centroid coordinates of a single blade and the mass of the entire circle of blades;

[0046] Step S2: Extract a part of the rim from the entire rim as the coupling rim, where the coupling rim includes the rim at the web;

[0047] Step S3: Extract a local disk from the bladed disk model and input the local disk into the finite element calculation model;

[0048] Step S4: Add a lumped mass unit in the finite element calculation model and establish a coupling relationship with the coupling rim, and after setting the centroid coordinates and mass of the lumped mass unit based on the centroid coordinates of a single blade and the mass of the entire circle of blades, carry out finite element stress calculation and analysis.

[0049] It can be understood that in the method for finite element stress analysis of a bladed disk based on blade simplification in this embodiment, a bladed disk model is first established and the centroid coordinates of a single blade and the mass of the entire circle of blades are calculated, so as to facilitate the subsequent determination of the centroid coordinates and mass of the lumped mass unit. Then, a part of the rim is extracted from the entire rim as the coupled rim, and the coupled rim includes the rim at the web. The local disk is extracted from the bladed disk model and input into the finite element calculation model. Then, the coupling relationship between the lumped mass unit and the coupled rim is established in the finite element calculation model, and the finite element stress calculation and analysis can be carried out. In the prior art, since the coupling relationship is established between the lumped mass unit and the entire rim where the blade is located, the centrifugal force of the blade will be evenly applied to the entire rim. However, the actual situation is that the centrifugal load of the blade is mainly borne by the rim near the web. When the prior art conducts finite element analysis, it will cause the load borne by the rim near the web to be too small and the load borne by the rim far from the web to be too large. A part of the centrifugal load borne by the rim far from the web will be balanced by its own deformation, and the remaining centrifugal load will be transmitted to the web and the wheel center through the rim near the web, resulting in a too small total load transmitted to the web and the wheel center, and thus the stress at the web and the wheel center will also be too small, and the error between the calculated result of the wheel center stress and the calculated result of the radial stress of the cylindrical section is large. Therefore, when the present invention simplifies the blade by using the lumped mass unit, a part of the rim including the rim at the web is extracted from the entire rim as the coupled rim, and then the coupling relationship between the lumped mass unit and the coupled rim is established, and the two end rims far from the web are removed, preventing the centrifugal load from being absorbed by the deformation of the two end rims, so that most of the centrifugal load can be transmitted to the web and the wheel center through the rim at the web, ensuring that the stress at the web and the wheel center is closer to the actual situation, reducing the error between the calculated result of the wheel center stress and the calculated result of the radial stress of the cylindrical section, and improving the accuracy of the finite element stress calculation and analysis.

[0050] It can be understood that in the step S1, a bladed disk model is first constructed according to the structural characteristics of the bladed disk. For example, for a bladed disk with an axisymmetric structure, a two-dimensional bladed disk model is constructed, and for a bladed disk with a cyclic symmetric structure, a three-dimensional bladed disk model is constructed. Then, the bladed disk is segmented. Specifically, the bladed disk is segmented into a blade part and a disk part along the rim. Then, any single blade is selected and its volume and centroid coordinates are measured. The centroid coordinates include the radial coordinate and the axial coordinate. Then, the mass of the entire circle of blades is calculated according to the volume of a single blade, the density of the blade, and the number of blades. The calculation formula is m 总 = nρV, where m 总 represents the mass of the entire circle of blades, n represents the number of blades, ρ represents the density of the blade, and V represents the volume of a single blade.

[0051] It can be understood that in the step S2, considering that the centrifugal load of the blade is mainly borne by the rim near the web, in order to improve the accuracy of the finite element stress analysis, a part of the rim is extracted from the entire rim as the coupled rim, and then a concentrated mass unit is coupled with the coupled rim. Among them, as Figure 4 shown, the process of extracting a part of the rim from the entire rim as the coupled rim includes the following contents:

[0052] Step S21: Establish reference planes perpendicular to the axis of the blade disk at the front end of the rim, the rear end of the rim, the root of the front fillet of the web, and the root of the rear fillet of the web respectively;

[0053] Step S22: Establish a first cutting reference plane between the reference planes at the front end of the rim and the root of the front fillet of the web, and establish a second cutting reference plane between the reference planes at the rear end of the rim and the root of the rear fillet of the web. Among them, both the first cutting reference plane and the second cutting reference plane are perpendicular to the axis of the blade disk;

[0054] Step S23: Use the first cutting reference plane and the second cutting reference plane to divide the entire rim into three parts, and take the middle part of the rim between the first cutting reference plane and the second cutting reference plane as the coupled rim.

[0055] Specifically, as Figure 5 shown, first establish reference planes perpendicular to the axis of the blade disk at the front end of the rim, the rear end of the rim, the root of the front fillet of the web, and the root of the rear fillet of the web respectively. Then, establish a first cutting reference plane A between the reference planes at the front end of the rim and the root of the front fillet of the web, and establish a second cutting reference plane B between the reference planes at the rear end of the rim and the root of the rear fillet of the web. Among them, both the first cutting reference plane and the second cutting reference plane are perpendicular to the axis of the blade disk. Then, use the first cutting reference plane A and the second cutting reference plane B to divide the entire rim into three parts: front, middle, and rear, and take the middle part of the rim between the first cutting reference plane and the second cutting reference plane as the coupled rim.

[0056] It can be understood that the coupled rim extracted by the present invention includes the complete web rim, excluding the front rim and the rear rim far from the web, preventing the centrifugal load from being absorbed by the deformation of the two end rims, so that the vast majority of the centrifugal load can be transmitted to the web and the wheel center through the rim at the web, ensuring that the stress at the web and the wheel center is closer to the actual situation, which is beneficial to improving the accuracy of the finite element stress calculation and analysis.

[0057] Preferably, the first cutting reference plane A is located exactly in the middle between the front end of the rim and the root of the front fillet of the web, and the second cutting reference plane B is located exactly in the middle between the rear end of the rim and the root of the rear fillet of the web. It can be understood that determining the two cutting reference planes at the exact middle between the front end of the rim and the root of the front fillet of the web and between the rear end of the rim and the root of the rear fillet of the web is convenient for quickly and accurately setting the positions of the cutting reference planes. On the other hand, more centrifugal loads are transmitted from the rim at the web to the web and the wheel center through the rim, making the stresses at the web and the wheel center basically consistent with the actual situation, and further improving the accuracy of the finite element stress calculation and analysis.

[0058] It can be understood that after extracting the coupled rim in the step S2, in the step S3, it is necessary to extract a local wheel disc from the blade disc model and input it into the finite element calculation model for finite element stress calculation and analysis. Among them, for the two-dimensional blade disc model with an axisymmetric structure, the process of extracting the local wheel disc from the blade disc model is specifically as follows:

[0059] First, cut the wheel disc with a plane passing through the axis of the blade disc (i.e., the meridian plane), cut off half of the blade disc, and then delete the detailed features on the cutting surface, such as ventilation holes, etc. Take the cutting surface as a two-dimensional sheet body of the local wheel disc and input it into the finite element calculation model.

[0060] For the three-dimensional blade disc model with a cyclic symmetric structure, the process of extracting the local wheel disc from the blade disc model is specifically as follows:

[0061] First, determine the corresponding target cyclic symmetric structure features on the wheel disc, then determine the reference plane based on the axis of the target cyclic symmetric structure features and the axis of the blade disc, and then establish two cutting planes on both sides of the reference plane that pass through the axis of the blade disc and form an angle of 180° / n with the reference plane. Use the two cutting planes to cut the wheel disc to obtain a cyclic symmetric segment of the wheel disc including the target cyclic symmetric structure features, where n represents the number of cyclic symmetric structures on the wheel disc.

[0062] It can be understood that the three-dimensional blade disc has cyclic symmetric structure features, such as uniformly distributed bolt holes, end teeth, air flow holes, etc. on the wheel disc. To ensure the accuracy of the stress calculation and analysis, it is not possible to extract a two-dimensional wheel disc sheet body for finite element calculation and analysis, but it is necessary to extract a local three-dimensional wheel disc structure for finite element calculation and analysis. Next, taking the bolt hole as an example of the cyclic symmetric structure feature, the process of extracting the local wheel disc structure of the three-dimensional blade disc model will be exemplarily described.

[0063] Assume that there are n bolt holes evenly distributed on the web of the wheel disc. First, select a target bolt hole. Then, establish a reference plane passing through the axis of the target bolt hole and the axis of the blade disc. Next, establish two cutting planes on the left and right sides of this reference plane, which pass through the axis of the blade disc and form an angle of 180° / n with this reference plane. Use the two cutting planes to cut the wheel disc, so as to obtain a wheel disc cyclic symmetric segment including the target bolt hole. Among them, the entire wheel disc can be divided into n wheel disc cyclic symmetric segments.

[0064] It can be understood that in step S4, after establishing a finite element calculation model in the finite element analysis software, add lumped mass elements in the finite element calculation model, and establish the coupling relationship between the lumped mass elements and the coupled rim, specifically as Figure 6 shown. After setting the centroid coordinates and mass of the lumped mass elements based on the centroid coordinates of a single blade and the mass of the whole circle of blades, carry out finite element stress calculation analysis to obtain the calculation results of displacement and stress. Among them, the specific stress calculation process belongs to the prior art and will not be elaborated here. For example, after assigning material properties, setting boundary conditions, applying loads such as rotational speed and temperature in the finite element calculation model, perform solution settings, submit calculation analysis, and perform post-processing after calculation to obtain the calculation results of displacement and stress.

[0065] Among them, for the two-dimensional blade disc model, the mass of the lumped mass element is the mass m of the whole circle of blades 总 , and the centroid coordinates of the lumped mass element are the centroid coordinates of the selected single blade, that is, the centroid coordinates of the lumped mass element are the radial coordinate and axial coordinate of the centroid of the single blade measured in step S1. For the three-dimensional blade disc model, the mass of the lumped mass element is the mass m of the whole circle of blades 总 / n. The radial coordinate and axial coordinate of the centroid of the lumped mass element are the radial coordinate and axial coordinate of the centroid of the selected single blade. The circumferential coordinate of the centroid of the lumped mass element is on this reference plane (that is, the reference plane determined based on the axis of the target cyclic symmetric structural feature and the axis of the blade disc) and on the side where the center of the wheel disc of the wheel disc cyclic symmetric segment points to the rim.

[0066] It can be understood that in order to verify the effectiveness and accuracy of the finite element stress analysis method for the blade disc of the present invention, the present invention also conducts finite element comparative calculation analysis with the prior art. The results show that the present invention can reduce the errors of the calculation results of the stress at the center of the wheel disc and the radial stress of the cylindrical section. The specific comparison results are shown in Table 1.

[0067] Table 1. Finite element comparative calculation analysis results of the prior art and the present invention

[0068]

[0069] As can be seen from Table 1, the calculation errors of the prior art regarding the equivalent stress of the wheel center and the average stress of the cylindrical section both exceed 15%, while the calculation errors of the present invention regarding the equivalent stress of the wheel center and the average stress of the cylindrical section are both within 1%. The present invention greatly reduces the calculation errors of the equivalent stress of the wheel center and the average stress of the cylindrical section, and greatly improves the accuracy of the finite element stress calculation and analysis.

[0070] As Figure 7 shown, another embodiment of the present invention further provides a blade disk finite element stress analysis system based on blade simplification, preferably adopting the blade disk finite element stress analysis method as described above, including:

[0071] A blade disk model construction module, configured to establish a blade disk model and calculate the centroid coordinates of a single blade and the mass of the entire circle of blades;

[0072] A coupling rim extraction module, configured to extract a part of the rim from the entire rim as a coupling rim, wherein the coupling rim includes the rim at the web;

[0073] A local disk extraction module, configured to extract a local disk from the blade disk model and input the local disk into the finite element calculation model;

[0074] A finite element analysis module, configured to add lumped mass elements in the finite element calculation model, establish a coupling relationship with the coupling rim, and, after setting the centroid coordinates and mass of the lumped mass elements based on the centroid coordinates of a single blade and the mass of the entire circle of blades, perform finite element stress calculation and analysis.

[0075] It can be understood that for the blade disk finite element stress analysis system based on blade simplification in this embodiment, a blade disk model is first established and the centroid coordinates of a single blade and the mass of the entire circle of blades are calculated to facilitate the subsequent determination of the centroid coordinates and mass of the lumped mass unit. Then, a partial rim is extracted from the entire rim as the coupled rim. The coupled rim includes the rim at the web. The local disk is extracted from the blade disk model and input into the finite element calculation model. Then, the coupling relationship between the lumped mass unit and the coupled rim is established in the finite element calculation model, and the finite element stress calculation and analysis can be carried out. In the prior art, since the coupling relationship is established between the lumped mass unit and the entire rim where the blade is located, the centrifugal force of the blade is evenly applied to the entire rim. However, in actuality, the centrifugal load of the blade is mainly borne by the rim near the web. When the prior art conducts finite element analysis, it will cause the load borne by the rim near the web to be too small and the load borne by the rim far from the web to be too large. A part of the centrifugal load borne by the rim far from the web will be balanced by its own deformation, and the remaining centrifugal load is then transmitted to the web and the wheel center through the rim near the web, resulting in a too small total load transmitted to the web and the wheel center, and thus the stress at the web and the wheel center will also be too small, and there is a large error between the calculated result of the wheel center stress and the calculated result of the radial stress of the cylindrical section. Therefore, when the present invention simplifies the blade using the lumped mass unit, a partial rim including the rim at the web is extracted from the entire rim as the coupled rim, and then the coupling relationship between the lumped mass unit and the coupled rim is established, excluding the two ends of the rim far from the web to prevent the centrifugal load from being absorbed by the deformation of the two ends of the rim, so that the vast majority of the centrifugal load can be transmitted to the web and the wheel center through the rim at the web, ensuring that the stress at the web and the wheel center is closer to the actual situation, reducing the error between the calculated result of the wheel center stress and the calculated result of the radial stress of the cylindrical section, and improving the accuracy of the finite element stress calculation and analysis.

[0076] Among them, the coupled rim extraction module includes:

[0077] A reference plane construction unit for respectively establishing reference planes perpendicular to the axis of the blade disk at the front end of the rim, the rear end of the rim, the root of the front fillet of the web, and the root of the rear fillet of the web;

[0078] A cutting reference plane construction unit for establishing a first cutting reference plane between the reference planes at the front end of the rim and the root of the front fillet of the web, and establishing a second cutting reference plane between the reference planes at the rear end of the rim and the root of the rear fillet of the web, where both the first cutting reference plane and the second cutting reference plane are perpendicular to the axis of the blade disk;

[0079] A coupled rim extraction unit for using the first cutting reference plane and the second cutting reference plane to divide the entire rim into three parts, and taking the middle part of the rim between the first cutting reference plane and the second cutting reference plane as the coupled rim.

[0080] It can be understood that each module and unit in the embodiments of the present system correspond to each step in the above method embodiments. Therefore, the specific working principles of each module and unit will not be elaborated herein. One can refer to each step in the above method embodiments for corresponding reference.

[0081] In addition, another embodiment of the present invention further provides an electronic device, including a processor and a memory. A computer program is stored in the memory. The processor is configured to execute the steps of the method as described above by calling the computer program stored in the memory.

[0082] In addition, another embodiment of the present invention further provides a computer-readable storage medium for storing a computer program for performing finite element stress analysis of a blisk based on blade simplification. The computer program executes the steps of the method as described above when running on a computer.

[0083] The forms of common computer-readable storage media generally include: floppy disks, flexible disks, hard disks, magnetic tapes, any other magnetic media, CD-ROMs, any other optical media, punch cards, paper tapes, any other physical media with a pattern of holes, random access memories (RAMs), programmable read-only memories (PROMs), erasable programmable read-only memories (EPROMs), flash erasable programmable read-only memories (FLASH-EPROMs), any other memory chips or cartridges, or any other media readable by a computer. The instructions can further be transmitted or received by a transmission medium. The term transmission medium can include any tangible or intangible medium that can be used to store, encode, or carry instructions for execution by a machine, and includes digital or analog communication signals or the intangible medium that facilitates the communication of the above instructions. The transmission medium includes coaxial cables, copper wires, and optical fibers, which include the wires of a bus used to transmit a computer data signal.

[0084] Those skilled in the art should understand that the embodiments of the present application can be provided as a method, a system, or a computer program product. Therefore, the present application can take the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware aspects. Moreover, the present application can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk memories, CD-ROMs, optical memories, etc.) containing computer-usable program code. The solutions in the embodiments of the present application can be implemented using various computer languages. For example, object-oriented programming languages such as Java and interpreted scripting languages such as JavaScript.

[0085] This application is described with reference to the flowcharts and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the present application. It should be understood that each flow and / or block in the flowchart and / or block diagram, as well as the combination of flows and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, such that the instructions executed by the processor of the computer or other programmable data processing devices generate a means for implementing the functions specified in one or more of the flows Figure 1 one or more of the flows and / or blocks Figure 1 or a means for implementing the functions specified in one or more of the blocks.

[0086] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, such that the instructions stored in the computer-readable memory generate a manufactured article including an instruction means that implements the functions specified in one or more of the flows Figure 1 one or more of the flows and / or blocks Figure 1 or a means for implementing the functions specified in one or more of the blocks.

[0087] These computer program instructions can also be loaded onto a computer or other programmable data processing device, such that a series of operation steps are executed on the computer or other programmable device to generate a computer-implemented process, so that the instructions executed on the computer or other programmable device provide steps for implementing the functions specified in one or more of the flows Figure 1 one or more of the flows and / or blocks Figure 1 or a means for implementing the functions specified in one or more of the blocks.

[0088] Although the preferred embodiments of the present application have been described, those skilled in the art can make additional changes and modifications once they learn the basic creative concepts. Therefore, the appended claims are intended to be construed as including the preferred embodiments as well as all changes and modifications falling within the scope of the present application.

[0089] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalent technologies, the present application is also intended to include these changes and modifications.

[0090] The above description is only for the preferred embodiments of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.

Claims

1. A finite element stress analysis method for a blade disk based on blade simplification, characterized in that: Includes the following: Establish a blade disk model and calculate the coordinates of the center of mass of a single blade and the mass of the entire blade circle; Extracting a part of the wheel rim from the entire wheel rim as a coupling wheel rim, wherein the coupling wheel rim includes the wheel rim at the spoke plate; Extracting a local wheel disk from the blade disk model and inputting the local wheel disk into the finite element calculation model; A concentrated mass unit is added to the finite element calculation model and a coupling relationship is established with the coupling rim. The centroid coordinates and mass of the concentrated mass unit are set based on the centroid coordinates of a single blade and the mass of the entire blade circle, and then the finite element stress calculation and analysis is carried out.

2. The finite element stress analysis method for blade disk based on blade simplification according to claim 1, characterized in that: The process of extracting a part of the wheel rim from the entire wheel rim as the coupling wheel rim comprises the following steps: Establish reference planes perpendicular to the blade disk axis at the front end of the wheel rim, the rear end of the wheel rim, the front rounded root of the spoke plate, and the rear rounded root of the spoke plate respectively; A first cutting reference plane is established between the reference planes at the front end of the rim and the root of the front chamfer of the spoke, and a second cutting reference plane is established between the reference planes at the rear end of the rim and the root of the rear chamfer of the spoke, wherein both the first cutting reference plane and the second cutting reference plane are perpendicular to the axis of the blade disk; The entire wheel rim is divided into three parts by using the first cutting reference plane and the second cutting reference plane, and the middle part of the wheel rim between the first cutting reference plane and the second cutting reference plane is used as the coupling wheel rim.

3. The finite element stress analysis method for blade disk based on blade simplification according to claim 2, characterized in that: The first cutting reference plane is located in the middle of the front end of the wheel rim and the front rounded root of the spoke plate, and the second cutting reference plane is located in the middle of the rear end of the wheel rim and the rear rounded root of the spoke plate.

4. The finite element stress analysis method for blade disk based on blade simplification according to claim 1, characterized in that: The process of calculating the coordinates of the center of mass of a single blade and the mass of a whole circle of blades includes the following: The blade disk is divided into the blade part and the disk part along the wheel rim. A single blade is selected and its volume and center of mass coordinates are measured. Then, the mass of the entire circle of blades is calculated based on the volume, density and number of blades.

5. The finite element stress analysis method for blade disk based on blade simplification according to claim 4, characterized in that: For the two-dimensional blade disk model, the disk is first cut using a plane passing through the axis of the blade disk, and then the detailed features on the cut surface are deleted, and the cut surface is used as a local two-dimensional disk slice; For the three-dimensional blade disk model, the target cyclically symmetrical structural features on the disk are first determined, and then the reference plane is determined based on the axis of the target cyclically symmetrical structural features and the axis of the blade disk. Then, two cutting planes passing through the axis of the blade disk and forming an angle of 180° / n with the reference plane are established on both sides of the reference plane. The disk is cut using the two cutting planes to obtain a cyclically symmetrical segment of the disk including the target cyclically symmetrical structural features, where n represents the number of cyclically symmetrical structures on the disk.

6. The finite element stress analysis method for blade disk based on blade simplification according to claim 5, characterized in that: For the two-dimensional blade disk model, the mass of the concentrated mass unit is the mass of the entire blade circle, and the centroid coordinates of the concentrated mass unit are the centroid coordinates of the selected single blade; For the three-dimensional blade disk model, the mass of the concentrated mass unit is the mass of the entire circle of blades / n, the radial coordinates and axial coordinates of the center of mass of the concentrated mass unit are the radial coordinates and axial coordinates of the center of mass of a selected single blade, and the circumferential coordinates of the center of mass of the concentrated mass unit are located on the reference plane and on the side of the wheel center pointing to the wheel rim of the cyclically symmetrical section of the wheel disk.

7. A blade disk finite element stress analysis system based on blade simplification, characterized in that: include: The blade disk model building module is used to build the blade disk model and calculate the center of mass coordinates of a single blade and the mass of the entire blade circle; A coupling rim extraction module is used to extract a part of the rim from the entire rim as a coupling rim, wherein the coupling rim includes the rim at the spoke plate; A local disk extraction module is used to extract the local disk from the blade disk model and input the local disk into the finite element calculation model; The finite element analysis module is used to add concentrated mass units to the finite element calculation model and establish a coupling relationship with the coupling rim. After setting the centroid coordinates and mass of the concentrated mass unit based on the centroid coordinates of a single blade and the mass of the entire circle of blades, finite element stress calculation and analysis is carried out.

8. The blade disk finite element stress analysis system based on blade simplification according to claim 7, characterized in that: The coupling wheel rim extraction module comprises: A reference plane construction unit is used to respectively establish reference planes perpendicular to the blade disk axis at the front end of the rim, the rear end of the rim, the front rounded root of the spoke plate, and the rear rounded root of the spoke plate; A cutting reference plane construction unit is used to establish a first cutting reference plane between a reference plane at the front end of the rim and a reference plane at the root of the front chamfer of the spoke, and to establish a second cutting reference plane between a reference plane at the rear end of the rim and a reference plane at the root of the rear chamfer of the spoke, wherein both the first cutting reference plane and the second cutting reference plane are perpendicular to the axis of the blade disk; The coupling wheel rim extraction unit is used to divide the entire wheel rim into three parts by using the first cutting reference plane and the second cutting reference plane, and to use the middle part of the wheel rim between the first cutting reference plane and the second cutting reference plane as the coupling wheel rim.

9. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the method according to any one of claims 1 to 6 by calling the computer program stored in the memory.

10. A computer-readable storage medium for storing a computer program for performing finite element stress analysis of a blade disk based on blade simplification, characterized in that: When the computer program is run on a computer, the steps of the method according to any one of claims 1 to 6 are executed.

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