Three-dimensional stress calculation method for engine blades and disks based on transient time history

Abstract

The present application provides a three-dimensional stress calculation method for engine blades and disks based on transient time history. The method includes the steps of model input, analysis step setting, load calculation, temperature field processing, generation of an APDL command stream file, and three-dimensional transient stress calculation. The purpose of the present application is to establish a three-dimensional stress calculation method for aeroengine blades / disks based on transient time history. By processing the temperature field and rotational speed data of each transient point of the disk / blade under the entire working cycle of the aeroengine, rapid load application and three-dimensional temperature field interpolation are performed in the ANSYS finite element software, improving work efficiency and reducing low-level quality problems; the three-dimensional transient stress of the blade / disk under the working cycle is obtained through rapid iterative calculation, and the stress analysis result is more accurate, thus effectively improving the reliability of the design of aeroengine blades / disks.

Description

Technical Field

[0001] This application relates to the technical field of aero-engines, and particularly to a three-dimensional stress calculation method for engine blades and disks based on transient time history. Background Art

[0002] The core idea of the three-dimensional stress calculation for engine blades / disks based on transient time history is that when an aero-engine transitions from one stable state to another, the change in the loads borne by components is a transient process. Different types of loads have inconsistent response times and change rates, and there will be relatively large transient loads during the conversion process. Therefore, it is necessary to accurately calculate the three-dimensional stress of the entire transient time history of the engine blades / disks during operation to obtain more accurate strength analysis results.

[0003] Most of the static strength designs of key components of existing aero-engines are based on steady-state design points, and the steady-state maximum stress is used as the input parameter for low-cycle fatigue life analysis and evaluation. However, during the actual operation of an engine, it has to go through multiple state transitions, and the loads on components will also change accordingly. This method cannot accurately consider different working state transitions such as cruising and acceleration during the service process of an aero-engine, cannot accurately calculate the transient stress during the engine state transition process, is very inaccurate for the static strength of blades / disks, thus increasing the usage risk of aero-engine blades / disks and reducing the reliability of aero-engine usage. Summary of the Invention

[0004] One aspect of this application provides a three-dimensional stress calculation method for engine blades and disks based on transient time history, which is used to solve the technical problems in the prior art that the transient stress during the engine state transition process cannot be accurately calculated, the static strength evaluation of blades / disks is inaccurate, thereby increasing the usage risk of aero-engine blades / disks and reducing the reliability of aero-engine usage.

[0005] The technical solution adopted by the present invention is as follows:

[0006] A three-dimensional stress calculation method for engine blades and disks based on transient time history includes the steps of:

[0007] Model input: Mesh the blade / disk model in ANSYS finite element software, and record the number of meshes as N1 for temperature field interpolation, serving as the analysis model for the entire calculation process;

[0008] Analysis step setting: Set transient time points between each state and state transition included in one working cycle of the engine, and apply loads and temperature fields at each transient time point by setting analysis steps. Record the number of analysis steps as n;

[0009] Load calculation: Calculate the rotational speed and centrifugal force corresponding to the set analysis step based on the flight state data, denoted as r* and p* respectively, which are used as the load inputs for each transient time point, where * is the corresponding analysis step number. The flight state data includes the temperature and rotational speed corresponding to each state of the engine in one working cycle.

[0010] Temperature field processing: Calculate the transient temperature field at each transient time point, and process the temperature field to obtain a file in a format readable by ANSYS finite element, which is used as the temperature field input for each transient time point. Extract the coordinate data and temperature data from the temperature field for temperature field interpolation.

[0011] APDL command stream file generation: Write a program through MATLAB to automatically read the constraint conditions and loads of each analysis step, and generate an APDL command stream file readable by ANSYS that contains the load information of each analysis step.

[0012] Three-dimensional transient stress calculation: Call the APDL command stream file, and gradually and quickly calculate the three-dimensional transient stress of the blade / disk at each analysis step in ANSYS finite element software, and output the three-dimensional transient stress results under each time history of the working cycle task spectrum.

[0013] Further, in the analysis step setting process, the time accuracy between two transient time points is small enough to capture load mutations, while taking into account the calculation efficiency. Dense points are arranged near the state mutation, and the point arrangement after the state is stable is relatively sparser than that near the state mutation.

[0014] Further, when processing the temperature field, use the cse operation in CFX-post to batch export the temperature field as a T*.csv file. The data format of the temperature field is "X, Y, Z, T", where X, Y, and Z are coordinate data and T is temperature data. Read the T*.csv file respectively, extract the coordinate data into the LOC*.txt file, and extract the temperature data into the TEMP*.txt file for temperature field interpolation.

[0015] Further, when generating an APDL command stream file readable by ANSYS that contains the load information of each analysis step, first give an APDL command stream file template, including the number of meshes, material properties, constraint conditions, loads, calculations, and output information. When reading the data in different analysis steps, modify the command stream file, including reading the rotational speed r* and centrifugal force p*, reading the coordinate data file LOC*.txt and temperature data file TEMP*.txt, and performing temperature field interpolation in association with the number of meshes N1. Finally, generate a command stream file CAL*.txt that contains the load information of each analysis step.

[0016] Further, when calculating the three-dimensional transient stress of the blade / disk at each analysis step, the dynamic response equation of the transient analysis adopts the direct integration method, and the integration scheme is the Newmark time integration. This direct integration method solves a set of simultaneous static equations at each transient time point:

[0017]

[0018] where α m , α f are time integration parameters. Through the above processing, the three-dimensional transient stress of the blade / disk at each transient time point is calculated batchwise in ANSYS finite element, and the three-dimensional stress changes under different time histories in the entire typical mission spectrum are obtained, and the three-dimensional transient stress between each state transition is obtained.

[0019] On the other hand, this application also provides a three-dimensional stress calculation device for engine blades and disks based on the transient time history, including:

[0020] A model input module for model input: meshing the blade / disk model in ANSYS finite element software, and the number of meshes divided is denoted as N1, which is used for temperature field interpolation and serves as the analysis model for the entire calculation process;

[0021] An analysis step setting module for analysis step setting: setting transient time points between each state and state transition included in one working cycle of the engine, and applying load and temperature field at each transient time point. The number of analysis steps is denoted as n;

[0022] A load calculation module for load calculation: calculating the rotational speed and centrifugal force corresponding to the set analysis step according to the flight state data, and denoting them as r* and p* respectively as the load input at each transient time point, where * is the corresponding analysis step number. The flight state data includes the temperature and rotational speed corresponding to each state in one working cycle of the engine;

[0023] A temperature field processing module for temperature field processing: calculating the transient temperature field at each transient time point, and processing the temperature field to obtain a file in a format readable by ANSYS finite element as the temperature field input at each transient time point, and extracting the coordinate data and temperature data in the temperature field for temperature field interpolation;

[0024] A file generation module for generating an APDL command stream file: automatically reading the constraint conditions and loads of each analysis step through a MATLAB program to generate an APDL command stream file containing the load information of each analysis step that can be read by ANSYS;

[0025] A three-dimensional transient stress calculation module is used for three-dimensional transient stress calculation: by calling the APDL command flow file, the three-dimensional transient stress of the blade / disk at each analysis step is gradually and rapidly calculated in the ANSYS finite element software, and the three-dimensional transient stress results under each time history of the entire cyclic mission spectrum are output.

[0026] On the other hand, this application also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and operable on the processor. When the processor executes the program, the steps of the three-dimensional stress calculation method for engine blades and disks based on the transient time history are implemented.

[0027] On the other hand, this application also provides a storage medium. The storage medium includes a stored program. When the program runs, it controls the device where the storage medium is located to execute the steps of the three-dimensional stress calculation method for engine blades and disks based on the transient time history.

[0028] Compared with the prior art, this application has the following beneficial effects:

[0029] This application provides a three-dimensional stress calculation method, device, electronic device, and storage medium for engine blades and disks based on the transient time history. The three-dimensional stress calculation method for engine blades and disks based on the transient time history includes the steps of: model input, analysis step setting, load calculation, temperature field processing, APDL command flow file generation, and three-dimensional transient stress calculation. The purpose of the present invention is to establish a three-dimensional stress calculation method for aeroengine blades / disks based on the transient time history. By processing the temperature field and rotational speed data of each transient point of the disk / blade under the entire working cycle of the aeroengine, rapid multi-analysis step load application and three-dimensional temperature field interpolation are performed in the ANSYS finite element software, improving work efficiency and reducing low-level quality problems; through rapid iterative calculation, the three-dimensional transient stress of the blade / disk under the working cycle is obtained, and the stress analysis result is more accurate, thereby effectively improving the reliability of the design of aeroengine blades / disks.

[0030] In addition to the purposes, features, and advantages described above, the present invention has other purposes, features, and advantages. Hereinafter, the present invention will be described in further detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The accompanying 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:

[0032] Figure 1 is a schematic flow chart of the three-dimensional stress calculation method for engine blades and disks based on the transient time history of the preferred embodiment of this application.

[0033] Figure 2 It is a schematic diagram of a three-dimensional stress calculation device module for engine blades and disks based on transient time history in another preferred embodiment of the present application.

[0034] Figure 3 It is a schematic block diagram of an electronic device entity in a preferred embodiment of the present application.

[0035] Figure 4 It is an internal structure diagram of a computer device in a preferred embodiment of the present application. Detailed implementation manners

[0036] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments may be combined with each other. The present invention will be described in detail below with reference to the drawings and in combination with the embodiments.

[0037] Refer to Figure 1 , a preferred embodiment of the present invention provides a three-dimensional stress calculation method for engine blades and disks based on transient time history, including the steps:

[0038] S1. Model input: In this embodiment, the three-dimensional transient stress under one working cycle of the engine is calculated, which includes several calculation states. The blade / disk calculation models and materials used in each state are the same. It is necessary to mesh the blade / disk model in the ANSYS finite element software. The number of meshes is denoted as N1, which is used for temperature field interpolation and serves as the analysis model for the entire calculation process.

[0039] S2. Analysis step setting: Since the engine includes several flight states under one working cycle, and transient time points need to be set between each state and state transition. Therefore, in this step, transient time points are set between each state and state transition included in a typical mission cycle spectrum of the engine. Analysis steps are set to apply loads and temperature fields at each transient time point. The number of analysis steps is denoted as n.

[0040] S3. Load calculation: Since the engine has different speeds and centrifugal forces corresponding to different states under one working cycle, in this step, the speeds and centrifugal forces corresponding to the set analysis steps are calculated according to the flight state data, and are denoted as r* and p* respectively as the load inputs at each transient time point, where * is the corresponding analysis step number. The flight state data includes the temperature and speed corresponding to each state of the engine under one working cycle.

[0041] S4. Temperature field processing: Since the engine has different temperature fields in different states under a typical mission cycle spectrum, and different transient time points in each state also have different temperature fields, this step needs to calculate the transient temperature fields at each transient time point, process the temperature fields to obtain files in a format readable by ANSYS finite element, use them as the temperature field inputs for each transient time point, and extract the coordinate data and temperature data in the temperature fields for temperature field interpolation.

[0042] S5. Generation of APDL command stream file: Since there are many flight states under the entire typical mission spectrum of the engine, and there are also many analysis steps set, and the steps of inputting the loads and temperature fields for each analysis step are numerous, therefore, in this step, a program is written in MATLAB to automatically read the constraint conditions and loads for each analysis step and generate an APDL command stream file readable by ANSYS and containing the load information for each analysis step.

[0043] S6. Three-dimensional transient stress calculation: Write a bat file to call the APDL command stream file generated in step S5, and gradually and quickly calculate the three-dimensional transient stresses of the blade / disk at each analysis step in the ANSYS finite element software, and output the three-dimensional transient stress results at each time history of the working cycle.

[0044] This embodiment provides a method for calculating the three-dimensional stresses of engine blades and disks based on transient time history, including the steps of: model input, analysis step setting, load calculation, temperature field processing, generation of APDL command stream file, and three-dimensional transient stress calculation. The purpose of this embodiment is to establish a method for calculating the three-dimensional stresses of aeroengine blades / disks based on transient time history. By processing the temperature fields and speed data at each transient point of the disks / blades during the entire working cycle of the aeroengine, rapid load application and three-dimensional temperature field interpolation are performed in the ANSYS finite element software, improving work efficiency and reducing low-level quality problems; the three-dimensional transient stresses of the blades / disks during the working cycle are obtained through rapid iterative calculation, and the stress analysis results are more accurate, thus effectively improving the reliability of the design of aeroengine blades / disks.

[0045] In a preferred embodiment of the present application, in the analysis step setting step, the time accuracy between two transient time points is small enough to capture load mutations. At the same time, to balance the calculation efficiency, points are densely distributed near state mutations, and the points are relatively sparser after the state is stable than near state mutations, reducing the calculation amount and improving the calculation effect.

[0046] In a preferred embodiment of the present application, when processing the temperature field, the cse operation in CFX-post is used to batch export the temperature field as a T*.csv file. The data format of the temperature field is "X, Y, Z, T", where X, Y, and Z are coordinate data and T is temperature data. The T*.csv file is read separately, and the coordinate data is extracted into a LOC*.txt file, and the temperature data is extracted into a TEMP*.txt file for temperature field interpolation.

[0047] In a preferred embodiment of the present application, when generating an APDL command stream file that can be read by ANSYS and contains load information for each analysis step, first a template of the APDL command stream file is given, including information such as the number of meshes, material properties, constraint conditions, loads, calculations, and outputs. When reading data in different analysis steps, the command stream file will be modified, including reading the rotational speed r* and centrifugal force p*, reading the coordinate data file LOC*.txt and the temperature data file TEMP*.txt, and performing temperature field interpolation in association with the number of meshes N1. Finally, a command stream file CAL*.txt containing load information for each analysis step is generated.

[0048] In a preferred embodiment of the present application, when calculating the three-dimensional transient stress of the blade / disk at each analysis step, the transient analysis dynamic response equation uses the direct integration method, and the integration scheme is the Newmark time integration. This direct integration method solves a set of simultaneous static equations at each transient time point:

[0049]

[0050] where α m , α f are time integration parameters. Through the above processing, the three-dimensional transient stress of the blade / disk at each transient time point is batch calculated in ANSYS finite element, and the three-dimensional stress changes under different time histories in the entire typical mission spectrum are obtained, and the three-dimensional transient stress between each state transition is obtained.

[0051] As Figure 2 shown, another embodiment of the present application further provides a three-dimensional stress calculation device for engine blades and disks based on a transient time history, including:

[0052] A model input module for model input: meshing the blade / disk model in ANSYS finite element software, and the number of meshes divided is denoted as N1, which is used for temperature field interpolation and serves as the analysis model for the entire calculation process;

[0053] Analysis step setting module, for analysis step setting: Set transient time points between various states and state transitions included in one working cycle of the engine, set the analysis step applied loads and temperature fields at each transient time point, and record the number of analysis steps as n;

[0054] Load calculation module, for load calculation: Calculate the rotational speed and centrifugal force corresponding to the set analysis steps according to the flight state data, and record them as r* and p* respectively as the load inputs at each transient time point, where * is the corresponding analysis step number, and the flight state data includes the temperature and rotational speed corresponding to each state in one working cycle of the engine;

[0055] Temperature field processing module, for temperature field processing: Calculate the transient temperature field at each transient time point, and process the temperature field to obtain a file in a format readable by ANSYS finite element as the temperature field input at each transient time point, and extract the coordinate data and temperature data in the temperature field for temperature field interpolation;

[0056] File generation module, for generating APDL command stream files: Write a program through MATLAB to automatically read the constraint conditions and loads of each analysis step, and generate an APDL command stream file readable by ANSYS containing the load information of each analysis step;

[0057] Three-dimensional transient stress calculation module, for three-dimensional transient stress calculation: Call the APDL command stream file, and gradually and quickly calculate the three-dimensional transient stress of the blade / disk at each analysis step in ANSYS finite element software, and output the three-dimensional transient stress results under each time history of the working cycle.

[0058] As Figure 3 shown, another preferred embodiment of the present application provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, it implements the steps of the three-dimensional stress calculation method for engine blades and disks based on transient time history.

[0059] Another preferred embodiment of the present application provides a storage medium, where the storage medium includes a stored program. When the program runs, it controls the device where the storage medium is located to execute the steps of the three-dimensional stress calculation method for engine blades and disks based on transient time history.

[0060] As Figure 4 shown, a preferred embodiment of the present application further provides a computer device, which may be a terminal or a living body detection server, and its internal structure diagram may be as Figure 4As shown in the figure. The computer device includes a processor, a memory, and a network interface connected via a system bus. Among them, 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 and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage medium. The network interface of the computer device is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, it realizes the steps of the method for calculating the three-dimensional stress of engine blades and disks based on the transient time history in the above embodiments.

[0061] Those skilled in the art can understand that Figure 4 the structure shown in the figure is only a block diagram of some structures 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 some components, or have different component arrangements.

[0062] It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. And although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in a different order than here.

[0063] If the functions described in the method of this embodiment are implemented in the form of software function units and sold or used as an independent product, they can be stored in one or more computer-readable storage media. Based on such an understanding, the part of the present application embodiment that contributes to the prior art or part of this technical solution can be embodied in the form of a software product. The software product is stored in a storage medium and includes several instructions for causing a computing device (which may be a personal computer, a server, a mobile computing device, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present application. And the aforementioned storage media include: USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks, or optical discs and other various media that can store program codes.

[0064] 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 memory, CD-ROM, optical memory, etc.) that contain computer-usable program code. The solutions in the embodiments of the present application can be implemented in various computer languages. For example, object-oriented programming languages such as Java and interpreted scripting languages such as JavaScript, etc.

[0065] The present application is described with reference to the flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to the 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 means for implementing the functions specified in Figure 1 one or more of the flows Figure 1 or blocks or a combination of blocks.

[0066] 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, so that the instructions stored in the computer-readable memory generate a manufactured article including instruction means, and the instruction means implements the functions specified in Figure 1 one or more of the flows Figure 1 or blocks or a combination of blocks.

[0067] These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to generate a computer-implemented process, and thus the instructions executed on the computer or other programmable device provide steps for implementing the functions specified in Figure 1 one or more of the flows Figure 1 or blocks or a combination of blocks.

[0068] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A three-dimensional stress calculation method for engine blades and disks based on transient time history, characterized in that Including the steps: Model input: Mesh the blade / disk model in ANSYS finite element software. The number of meshes is denoted as N1, which is used for temperature field interpolation and serves as the analysis model for the entire calculation process. Analysis step setting: Set transient time points between various states and state transitions included in one working cycle of the engine. Apply loads and temperature fields for the analysis steps at each transient time point. The number of analysis steps is denoted as n. Load calculation: Calculate the rotational speed and centrifugal force corresponding to the set analysis steps according to the flight state data, denoted as r* and p* respectively, which are used as load inputs for each transient time point, where * is the corresponding analysis step number. The flight state data includes the temperature and rotational speed corresponding to each state in one working cycle of the engine. Temperature field processing: Calculate the transient temperature field at each transient time point and process the temperature field to obtain a file in a format readable by ANSYS finite element, which is used as the temperature field input for each transient time point. Extract the coordinate data and temperature data from the temperature field for temperature field interpolation. APDL command stream file generation: Write a program in MATLAB to automatically read the constraint conditions and loads for each analysis step and generate an APDL command stream file readable by ANSYS that contains the load information for each analysis step. When generating the APDL command stream file readable by ANSYS that contains the load information for each analysis step, first give an APDL command stream file template, including the number of meshes, material properties, constraint conditions, loads, calculations, and output information. When reading the data in different analysis steps, modify the command stream file, including reading the rotational speed r* and centrifugal force p*, reading the coordinate data file LOC*.txt and temperature data file TEMP*.txt, and performing temperature field interpolation in association with the number of meshes N1. Finally, generate the command stream file CAL*.txt that contains the load information for each analysis step. Three-dimensional transient stress calculation: Call the APDL command stream file and gradually and rapidly calculate the three-dimensional transient stress of the blade / disk at each analysis step in ANSYS finite element software, and output the three-dimensional transient stress results for each time history in the working cycle. When calculating the three-dimensional transient stress of the blade / disk at each analysis step, the transient analysis dynamic response equation uses the direct integration method, and the integration scheme is the Newmark time integration. This direct integration method solves a set of simultaneous static equations at each transient time point: where α m , α f is the time integration parameter. Through the above processing, the three-dimensional transient stresses of the blade / disk at each transient time point are calculated batch by batch in ANSYS finite element, the three-dimensional stress changes under different time histories in the entire typical mission spectrum are obtained, and the three-dimensional transient stresses between each state transition are obtained.

2. The three-dimensional stress calculation method for engine blades and disks based on transient time history according to claim 1, wherein In the analysis step setting step, the time accuracy between two transient time points is small enough to capture load mutations, while taking into account the calculation efficiency. Dense points are arranged near state mutations, and the points arranged after the state stabilizes are relatively sparser than those near state mutations.

3. The three-dimensional stress calculation method for engine blades and disks based on transient time history according to claim 1, characterized in that When processing the temperature field, use the cse operation in CFX-post to batch export the temperature field as a T*.csv file. The data format of the temperature field is "X, Y, Z, T", where X, Y, and Z are coordinate data and T is temperature data. Read the T*.csv file respectively, extract the coordinate data into the LOC*.txt file, and extract the temperature data into the TEMP*.txt file for temperature field interpolation.

4. A three-dimensional stress calculation device for engine blades and disks based on transient time history, characterized in that, Including: A model input module for model input: Meshing the blade / disk model in ANSYS finite element software, and the number of meshes is denoted as N1, which is used for temperature field interpolation and serves as the analysis model for the entire calculation process; An analysis step setting module for analysis step setting: Setting transient time points between various states and state transitions included in one working cycle of the engine, and applying analysis step loads and temperature fields at each transient time point. The number of analysis steps is denoted as n; A load calculation module for load calculation: Calculating the rotational speed and centrifugal force corresponding to the set analysis steps according to the flight state data, denoted as r* and p* respectively, as the load input at each transient time point, where * is the corresponding analysis step number. The flight state data includes the temperature and rotational speed corresponding to each state in one working cycle of the engine; A temperature field processing module for temperature field processing: Calculating the transient temperature field at each transient time point, and processing the temperature field to obtain a file in a format readable by ANSYS finite element, as the temperature field input at each transient time point. Extracting the coordinate data and temperature data in the temperature field for temperature field interpolation; A file generation module for generating an APDL command stream file: Automatically reading the constraint conditions and loads of each analysis step through a program written in MATLAB to generate an APDL command stream file readable by ANSYS and containing the load information of each analysis step. When generating the APDL command stream file readable by ANSYS and containing the load information of each analysis step, first give an APDL command stream file template, including the number of meshes, material properties, constraint conditions, loads, calculations, and output information. When reading the data in different analysis steps, modify the command stream file, including reading the rotational speed r* and centrifugal force p*, reading the coordinate data file LOC*.txt and the temperature data file TEMP*.txt, and associating with the number of meshes N1 for temperature field interpolation. Finally, generate a command stream file CAL*.txt containing the load information of each analysis step; A three-dimensional transient stress calculation module for three-dimensional transient stress calculation: Invoking the APDL command stream file, and gradually and rapidly calculating the three-dimensional transient stress of the blade / disk at each analysis step in ANSYS finite element software, and outputting the three-dimensional transient stress results at each time history of the working cycle. When calculating the three-dimensional transient stress of the blade / disk at each analysis step, the transient analysis dynamic response equation adopts the direct integration method, and the integration scheme is the Newmark time integration. This direct integration method solves a set of simultaneous static equations at each transient time point: where α m , α f is the time integration parameter. Through the above processing, the three-dimensional transient stresses of the blade / disk at each transient time point are calculated batch by batch in ANSYS finite element, the three-dimensional stress changes under different time histories in the entire typical mission spectrum are obtained, and the three-dimensional transient stresses between each state transition are obtained.

5. An electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that When the processor executes the program, it implements the steps of the method for calculating the three-dimensional stress of the engine blade and disk based on the transient time history according to any one of claims 1 to 3.

6. A storage medium, the storage medium including a stored program which, when the program runs, controls the device where the storage medium is located to execute the steps of the method for calculating three-dimensional stresses of an engine blade and a disk based on a transient time history according to any one of claims 1 to 3.

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