Multidisciplinary simulation coupling method, device and computer equipment for aero-engine

Abstract

The application relates to a multidisciplinary simulation coupling method, device and computer equipment of an aero-engine. The method comprises the following steps: acquiring simulation running models of each discipline of the aero-engine and associated mechanism information therebetween, and identifying coupling information of each coupling type between the disciplines; based on the coupling information of each coupling type between the disciplines, constructing each level coupling mechanism model of the aero-engine through a hierarchical coupling modeling strategy, thereby performing running association processing on the simulation running models of each discipline to obtain a simulation coupling model of the aero-engine; collecting simulation working condition information and simulation condition information of the aero-engine, and simulating the running process of the aero-engine through the simulation coupling model to obtain simulation running results of the aero-engine; and based on the simulation running results of the aero-engine, identifying simulation running information of each discipline of the aero-engine. The method can improve the accuracy and efficiency of accounting for actual course learning hours of users.

Description

Technical Field

[0001] This application relates to the field of aero-engine simulation coupling technology, and in particular to a multidisciplinary simulation coupling method, device and computer equipment for aero-engines. Background Technology

[0002] The actual operation of aero-engines involves the close coupling of multiple disciplines such as aerodynamics, thermodynamics, mechanics, hydraulics, and electronics. However, due to difficulties in integrating specialized tools and the large workload of model interface adaptation, the actual performance simulation of aero-engines struggles to effectively reflect the coupling relationships between various components and systems. This hinders the effective verification and evaluation of the compatibility and mutual influence between systems and components, forcing engine development to rely on trial and error, constantly modifying and adjusting designs and system performance, resulting in high costs and long development cycles. Therefore, improving the coupling accuracy of aero-engines is a current research focus.

[0003] Traditional aero-engine simulation modeling methods employ single-discipline simulation modeling, performing simulation tests from each discipline to obtain simulation test results for the engine. However, the coupling performance of the above-mentioned simulation optimization methods is poor, especially in simulating and reproducing the operation of real engines under special operating conditions, which can lead to significant simulation deviations and consequently poor accuracy in aero-engine simulation operations. Summary of the Invention

[0004] Therefore, it is necessary to provide a multidisciplinary simulation coupling method, device, computer equipment, computer-readable storage medium, and computer program product for aero-engines to address the aforementioned technical problems.

[0005] Firstly, this application provides a multidisciplinary simulation coupling method for aero-engines, including:

[0006] The simulation operation models of various disciplines of aero-engines and the correlation mechanism information between these disciplines are obtained, and based on the correlation mechanism information between these disciplines, the coupling information of each coupling type between these disciplines is identified;

[0007] Based on the coupling information of each coupling type among the disciplines, a hierarchical coupling modeling strategy is used to construct the coupling mechanism models of the aero-engine at each level. Based on the coupling mechanism models of the aero-engine at each level, the simulation operation models of each discipline are processed for operation association to obtain the simulation coupling model of the aero-engine.

[0008] The simulation operating condition information and simulation condition information of the aero-engine are collected, and based on the simulation operating condition information and simulation condition information, the operation process of the aero-engine is simulated through the simulation coupling model to obtain the simulation operation results of the aero-engine.

[0009] Based on the simulation results of the aero-engine, the simulation operation information of various disciplines of the aero-engine is identified.

[0010] Optionally, the step of identifying coupling information of various coupling types between the disciplines based on the association mechanism information between the disciplines includes:

[0011] Based on the correlation mechanism information between the disciplines, identify the coupling-related information between the disciplines, and based on the coupling-related information between the disciplines, query the coupling type and coupling logic information corresponding to each coupling-related information in the coupling database.

[0012] The coupling logic information corresponding to each coupling-related information is used as the coupling information of the coupling type corresponding to each coupling-related information.

[0013] Optionally, based on the coupling information of each coupling type between the various disciplines, the construction of the coupling mechanism model of each level of the aero-engine through a hierarchical coupling modeling strategy includes:

[0014] Based on the coupling information of each coupling type, in the hierarchical coupling modeling database, the modeling level corresponding to each coupling type and the parameter transformation strategy corresponding to each coupling type are queried. Based on the parameter transformation strategy corresponding to each coupling type, the coupling information of each coupling type is parameterized to obtain the coupling parameters of each coupling type.

[0015] According to the order of modeling levels, each first coupling type corresponding to the first modeling level is selected, and the association modeling process is performed based on the coupling parameters of each first coupling type to obtain each first coupling model corresponding to the first modeling level.

[0016] According to the order of modeling levels, the second modeling levels after the first modeling level are selected, and based on the coupling parameters of each first coupling type corresponding to the second modeling level and each coupling model corresponding to the first modeling level, each second coupling model corresponding to the second modeling level is constructed.

[0017] According to the order of modeling levels, the third modeling level after the second modeling level is selected, and the third modeling level replaces the second modeling level. Then, the process of constructing the second coupling model corresponding to each second modeling level is carried out based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling model corresponding to the first modeling level, until the coupling model corresponding to all modeling levels is obtained.

[0018] Each coupling model corresponding to each modeling level is used as the coupling mechanism model of each level of the aero-engine.

[0019] Optionally, based on the coupling mechanism model of the aero-engine at each level, the simulation operation model of each discipline is subjected to operation correlation processing to obtain the simulation coupling model of the aero-engine, including:

[0020] Based on each discipline corresponding to each coupled model, data interaction logic between the simulation operation models of each discipline is generated, and based on each coupled model and the data interaction logic between the simulation operation models of each discipline, a coupled simulation function model between the simulation operation models of each discipline is constructed.

[0021] The simulation operation models of each discipline and the coupled simulation function models between each simulation operation model are subjected to model association processing to obtain the simulation coupling model of the aero-engine.

[0022] Optionally, the step of simulating the operation process of the aero-engine through the simulation coupling model based on the simulation operating condition information and the simulation condition information to obtain the simulation operation results of the aero-engine includes:

[0023] Based on the simulation operating condition information and the simulation condition information, the environmental input data and the operating condition input data of the aero-engine are identified.

[0024] The environmental input data and the operating condition input data are input into the simulation coupling model to simulate the operation process of the aero-engine and obtain the simulation operation results of the aero-engine.

[0025] Optionally, the step of identifying the simulation operation information of various disciplines of the aero-engine based on the simulation operation results of the aero-engine includes:

[0026] The simulation results of the aero-engine are broken down into sub-simulation results of each discipline, and the simulation data distribution information of each operational function of each discipline is identified based on the sub-simulation results of each discipline.

[0027] Based on the distribution information of simulation operation data of each function in each discipline, and through the functional evaluation strategy of each discipline, the abnormal operation information and functional risk information of each function in each discipline are identified, and the abnormal operation information and functional risk information of each function in each discipline are used as the simulation operation information of each discipline.

[0028] Secondly, this application also provides a multidisciplinary simulation coupling device for aero-engines, comprising:

[0029] The acquisition module is used to acquire the simulation operation models of various disciplines of aero-engines, as well as the correlation mechanism information between the disciplines, and based on the correlation mechanism information between the disciplines, to identify the coupling information of each coupling type between the disciplines.

[0030] The coupling module is used to construct the coupling mechanism models of the aero-engine at all levels based on the coupling information of each coupling type between the disciplines, through a hierarchical coupling modeling strategy, and to perform operational correlation processing on the simulation operation models of each discipline based on the coupling mechanism models of the aero-engine at all levels, so as to obtain the simulation coupling model of the aero-engine.

[0031] The simulation module is used to collect the simulation operating condition information and simulation condition information of the aero-engine, and based on the simulation operating condition information and simulation condition information, simulate the operation process of the aero-engine through the simulation coupling model to obtain the simulation operation results of the aero-engine.

[0032] The identification module is used to identify the simulation operation information of various disciplines of the aero-engine based on the simulation operation results of the aero-engine.

[0033] Optionally, the acquisition module is specifically used for:

[0034] Based on the correlation mechanism information between the disciplines, identify the coupling-related information between the disciplines, and based on the coupling-related information between the disciplines, query the coupling type and coupling logic information corresponding to each coupling-related information in the coupling database.

[0035] The coupling logic information corresponding to each coupling-related information is used as the coupling information of the coupling type corresponding to each coupling-related information.

[0036] Optionally, the coupling module is specifically used for:

[0037] Based on the coupling information of each coupling type, in the hierarchical coupling modeling database, the modeling level corresponding to each coupling type and the parameter transformation strategy corresponding to each coupling type are queried. Based on the parameter transformation strategy corresponding to each coupling type, the coupling information of each coupling type is parameterized to obtain the coupling parameters of each coupling type.

[0038] According to the order of modeling levels, each first coupling type corresponding to the first modeling level is selected, and the association modeling process is performed based on the coupling parameters of each first coupling type to obtain each first coupling model corresponding to the first modeling level.

[0039] According to the order of modeling levels, the second modeling levels after the first modeling level are selected, and based on the coupling parameters of each first coupling type corresponding to the second modeling level and each coupling model corresponding to the first modeling level, each second coupling model corresponding to the second modeling level is constructed.

[0040] According to the order of modeling levels, the third modeling level after the second modeling level is selected, and the third modeling level replaces the second modeling level. Then, the process of constructing the second coupling model corresponding to each second modeling level is carried out based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling model corresponding to the first modeling level, until the coupling model corresponding to all modeling levels is obtained.

[0041] Each coupling model corresponding to each modeling level is used as the coupling mechanism model of each level of the aero-engine.

[0042] Optionally, the coupling module is specifically used for:

[0043] Based on each discipline corresponding to each coupled model, data interaction logic between the simulation operation models of each discipline is generated, and based on each coupled model and the data interaction logic between the simulation operation models of each discipline, a coupled simulation function model between the simulation operation models of each discipline is constructed.

[0044] The simulation operation models of each discipline and the coupled simulation function models between each simulation operation model are subjected to model association processing to obtain the simulation coupling model of the aero-engine.

[0045] Optionally, the simulation module is specifically used for:

[0046] Based on the simulation operating condition information and the simulation condition information, the environmental input data and the operating condition input data of the aero-engine are identified.

[0047] The environmental input data and the operating condition input data are input into the simulation coupling model to simulate the operation process of the aero-engine and obtain the simulation operation results of the aero-engine.

[0048] Optionally, the identification module is specifically used for:

[0049] The simulation results of the aero-engine are broken down into sub-simulation results of each discipline, and the simulation data distribution information of each operational function of each discipline is identified based on the sub-simulation results of each discipline.

[0050] Based on the distribution information of simulation operation data of each function in each discipline, and through the functional evaluation strategy of each discipline, the abnormal operation information and functional risk information of each function in each discipline are identified, and the abnormal operation information and functional risk information of each function in each discipline are used as the simulation operation information of each discipline.

[0051] Thirdly, this application provides a computer device. The computer device includes a memory and a processor, the memory storing a computer program, and the processor executing the computer program to implement the steps of the method described in any one of the first aspects.

[0052] Fourthly, this application provides a computer-readable storage medium having a computer program stored thereon that, when executed by a processor, implements the steps of the method described in any one of the first aspects.

[0053] Fifthly, this application provides a computer program product. The computer program product includes a computer program that, when executed by a processor, implements the steps of the method described in any one of the first aspects.

[0054] The aforementioned multidisciplinary simulation coupling method, apparatus, and computer equipment for aero-engines acquire simulation operation models of each discipline of the aero-engine and the correlation mechanism information between these disciplines. Based on this correlation mechanism information, they identify coupling information of various coupling types between the disciplines. Using a hierarchical coupling modeling strategy, they construct coupling mechanism models of each level of the aero-engine. Based on these coupling mechanism models, they perform operational correlation processing on the simulation operation models of each discipline to obtain a simulation coupling model for the aero-engine. They collect simulation operating condition information and simulation condition information of the aero-engine, and based on this information, they simulate the operation process of the aero-engine using the simulation coupling model to obtain the simulation operation results. Finally, based on the simulation operation results, they identify the simulation operation information of each discipline of the aero-engine. This approach establishes a simulation coupling model between various disciplines, thereby coupling and associating the various simulation operation models of aero-engines to form a dynamic simulation model that couples and interacts multiple subsystems, including overall engine performance, control, fuel, lubricating oil, air, mechanical transmission, starting, ignition, and power extraction. Compared to traditional steady-state performance models, this approach can effectively simulate transient processes and overall engine matching conditions, significantly increasing the number and dimensionality of system operating parameters. This provides strong support for the evaluation and analysis of design schemes and performance parameters, enabling timely identification of risks and vulnerabilities between subsystems during the design process. It reduces the time and cost incurred by discovering or exposing problems during physical system integration, improving R&D efficiency and success rate. Furthermore, this method avoids the problem of large simulation deviations in single-system simulations when simulating and reproducing the operation of real engines under special operating conditions, thus improving the accuracy of aero-engine simulation operations. Attached Figure Description

[0055] To more clearly illustrate the technical solutions in the embodiments or related technologies of this application, the accompanying drawings used in the description of the embodiments or related technologies will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0056] Figure 1 This is a flowchart illustrating a multidisciplinary simulation coupling method for an aero-engine in one embodiment.

[0057] Figure 2 This is a flowchart illustrating a multidisciplinary simulation coupling example for an aero-engine in one embodiment;

[0058] Figure 3 This is a structural block diagram of a multidisciplinary simulation coupling device for an aero-engine in one embodiment.

[0059] Figure 4 This is an internal structural diagram of a computer device in one embodiment. Detailed Implementation

[0060] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0061] The multidisciplinary simulation coupling method for aero-engines provided in this application embodiment can be applied to the application environment of multidisciplinary simulation coupling for aero-engines. This method can be applied to terminals, servers, or systems including both terminals and servers, and is implemented through interaction between the terminals and servers. The terminals can be, but are not limited to, various personal computers, laptops, mid-range computers, etc. The terminals establish simulation coupling models between different disciplines, thereby coupling and associating various simulation operation models of the aero-engine to form a dynamic simulation model with coupled interaction of multiple subsystems such as overall engine performance, control, fuel, lubricating oil, air, mechanical transmission, starting, ignition, and power extraction. Compared with traditional steady-state performance models, this method can effectively simulate system transient processes and overall engine matching conditions, significantly increasing the number and dimensionality of system operating parameters. This provides strong support for the evaluation and analysis of design schemes and performance parameters, timely identifying risks and vulnerabilities between subsystems during the design process, reducing the time and cost incurred by discovering or exposing problems during physical system integration, and improving R&D efficiency and success rate. Furthermore, this approach avoids the problem of large simulation deviations in single-system simulations when simulating and reproducing the operation of real engines under special operating conditions, thereby improving the accuracy of aero-engine simulation.

[0062] In one exemplary embodiment, such as Figure 1 As shown, a multidisciplinary simulation coupling method for aero-engines is provided. Taking the application of this method to a terminal as an example, the method includes the following steps S101 to S104. Wherein:

[0063] Step S101: Obtain the simulation operation model of each discipline of the aero-engine and the correlation mechanism information between each discipline, and based on the correlation mechanism information between each discipline, identify the coupling information of each coupling type between the disciplines.

[0064] In this embodiment, the terminal encompasses disciplines including, but not limited to, overall engine performance, various engine structural systems, air system OD characteristics, engine control, sensors, ignition system, fuel regulation system, starter, generator, transmission system, complex systems, lubrication system, air system, platform interaction interface, intake and exhaust conditions, and characteristic operating conditions. Each discipline corresponds to a simulation operation model, which includes, but is not limited to, steady-state models of various subsystems, overall engine performance models, air system OD characteristic models, control models, sensor models, ignition system models, fuel regulation system models, starter models, generator models, conventional system models, and load system models. The correlation mechanism information between disciplines involves mechanistic information that includes or partially includes the aerodynamic, thermodynamic, control, electronic, electrical, mechanical, hydraulic, and heat transfer subsystem mechanisms involved in the operation of the entire aero-engine. Then, based on the correlation mechanism information between disciplines, the terminal identifies the coupling information of various coupling types between disciplines. This coupling type includes, but is not limited to, steady-state parameter coupling, aerodynamic and thermodynamic performance parameter coupling, electrical control signal coupling, mechanical and hydraulic parameter coupling, heat transfer parameter coupling, and environmental condition coupling. The specific identification process will be explained in detail later.

[0065] Step S102: Based on the coupling information of various coupling types between disciplines, a hierarchical coupling modeling strategy is used to construct coupling mechanism models of aero-engines at all levels. Based on the coupling mechanism models of aero-engines at all levels, the simulation operation models of each discipline are processed for operation correlation to obtain the simulation coupling model of aero-engines.

[0066] In this embodiment, the terminal constructs various coupling mechanism models of the aero-engine based on coupling information of different coupling types between disciplines, using a hierarchical coupling modeling strategy. Based on these models, it performs operational correlation processing on the simulation operation models of each discipline to obtain the aero-engine simulation coupling model. Each coupling mechanism model corresponds to a coupling model at a different modeling level, as shown in Table 1, which contains model information such as coupling parameters, design system, and functions for different modeling levels. The specific modeling process will be explained in detail later.

[0067] Table 1: Model Information of Coupled Models at Different Modeling Levels

[0068]

[0069] Step S103: Collect simulation operating condition information and simulation condition information of the aero-engine, and based on the simulation operating condition information and simulation condition information, simulate the operation process of the aero-engine through a simulation coupling model to obtain the simulation operation results of the aero-engine.

[0070] In this embodiment, the terminal collects simulation operating condition information and simulation condition information of the aero-engine. Based on this information, it simulates the aero-engine's operation process using a simulation coupling model to obtain the simulation results. The simulation operating condition information characterizes the engine's operating conditions corresponding to various disciplines within the aero-engine. The simulation condition information includes environmental information, operating conditions, operating states, and other influencing factors related to the aero-engine's operating conditions. The terminal's simulation of the aero-engine's operation process yields simulation results that include the operational information of the simulation models from various disciplines.

[0071] Step S104: Based on the simulation results of the aero-engine, identify the simulation operation information of various disciplines of the aero-engine.

[0072] In this embodiment, the terminal identifies the simulation operation information of various disciplines of the aero-engine based on the simulation operation results. This simulation operation information includes operational anomaly information for each operational function of each discipline, as well as functional risk information for each operational function of each discipline. The specific identification process will be described in detail later.

[0073] Based on the above scheme, by establishing simulation coupling models between various disciplines, the various simulation operation models of aero-engines are coupled and correlated, forming a dynamic simulation model with coupled interaction of multiple subsystems such as overall engine performance, control, fuel, lubricating oil, air, mechanical transmission, starting, ignition, and power extraction. Compared with traditional steady-state performance models, this model can effectively simulate system transient processes and overall engine matching conditions, significantly increasing the number and dimensionality of system operating parameters. This provides strong support for the evaluation and analysis of design schemes and performance parameters, promptly identifying risks and vulnerabilities between subsystems during the design process, reducing the time and cost incurred by discovering or exposing problems during physical system integration, and improving R&D efficiency and success rate. Furthermore, this approach avoids the problem of large simulation deviations in single-system simulations when simulating and reproducing the operation of real engines under special operating conditions, thereby improving the accuracy of aero-engine simulation operations.

[0074] Optionally, based on the correlation mechanism information between disciplines, the coupling information of each coupling type between disciplines is identified, including: based on the correlation mechanism information between disciplines, identifying each coupling-related information between disciplines, and based on each coupling-related information between disciplines, querying the coupling type corresponding to each coupling-related information and the coupling logic information corresponding to each coupling-related information in the coupling database; and using the coupling logic information corresponding to each coupling-related information as the coupling information of the coupling type corresponding to each coupling-related information.

[0075] In this embodiment, the terminal identifies coupling-related information between disciplines based on the association mechanism information between disciplines, and queries the coupling database for the coupling type and coupling logic information corresponding to each coupling-related information. The coupling logic information refers to the logical mechanism information related to the coupling logic between two disciplines.

[0076] Finally, the terminal uses the coupling logic information corresponding to each coupling-related information as the coupling information of the coupling type corresponding to each coupling-related information.

[0077] Based on the above scheme, by breaking down the information on the connection mechanism between various disciplines into coupling-related information of various coupling types, the comprehensiveness and accuracy of identifying the coupling relationship between various disciplines are improved.

[0078] Optionally, based on coupling information of various coupling types between disciplines, a hierarchical coupling modeling strategy is used to construct coupling mechanism models of aero-engines at various levels. This includes: based on the coupling information of each coupling type, querying the modeling level corresponding to each coupling type and the parameter transformation strategy corresponding to each coupling type in the hierarchical coupling modeling database; and parameterizing the coupling information of each coupling type according to the parameter transformation strategy to obtain the coupling parameters of each coupling type; selecting the first coupling types corresponding to the first modeling level according to the order of modeling levels, and performing correlation modeling based on the coupling parameters of each first coupling type to obtain the first coupling models corresponding to the first modeling level; and then, according to the modeling level... The process proceeds in the following order: First, the second modeling level is selected after the first modeling level. Based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling models corresponding to the first modeling level, each second coupling model corresponding to the second modeling level is constructed. Then, following the order of modeling levels, the third modeling level is selected after the second modeling level, and the third modeling level replaces the second modeling level. The process then returns to the previous steps of constructing each second coupling model based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling models corresponding to the first modeling level, until all coupling models corresponding to all modeling levels are obtained. Each coupling model corresponding to each modeling level is used as the coupling mechanism model for each level of the aero-engine.

[0079] In this embodiment, based on the coupling information of each coupling type, the terminal queries the hierarchical coupling modeling database for the modeling level corresponding to each coupling type and the parameter transformation strategy corresponding to each coupling type. Then, based on the parameter transformation strategy, the terminal parameterizes the coupling information of each coupling type to obtain the coupling parameters for each coupling type. Next, the terminal filters the first coupling types corresponding to the first modeling level according to the order of modeling levels and performs correlation modeling based on the coupling parameters of each first coupling type to obtain the first coupling models corresponding to the first modeling level. Finally, the terminal filters the second modeling levels following the first modeling level according to the order of modeling levels and constructs the second coupling models corresponding to each second modeling level based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling models corresponding to the first modeling level.

[0080] The terminal, following the modeling level order, filters for the third modeling level following the second modeling level, replaces the second modeling level with the third modeling level, and returns to execute the steps of constructing the second coupling models corresponding to each second modeling level based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling models corresponding to the first modeling level, until all coupling models corresponding to all modeling levels are obtained. Finally, the terminal uses the coupling models corresponding to each modeling level as the coupling mechanism models for each level of the aero-engine. Specifically, the terminal performs modeling according to different modeling levels, and after completing the modeling for each modeling level, it constructs the coupling models for the next modeling level based on the coupling models constructed at that modeling level, combined with the coupling parameters of the next modeling level, and so on, until the coupling models for the last modeling level are obtained.

[0081] For example, the enhanced model of the entire aero-engine system is distinguished according to the type of coupling signal between the models of each subsystem:

[0082] Among them, the L0 level model is the steady-state parameter model of the aero-engine, which is composed of the steady-state models of each subsystem and is used to calculate the matching of the performance parameters of the engine at each steady-state point.

[0083] The L1 level model is an overall aero-thermodynamic performance model for aero-engines. It mainly calculates the dynamic changes of key performance parameters of aero-engines with input quantities. It needs to realize the simulation calculation of variables such as rotor speed, parameters of various sections (temperature, pressure, flow rate, etc.), and thrust. It can realize the simulation capabilities of engine start-up, acceleration and deceleration, steady state, and shutdown processes.

[0084] The L2 model is based on the L1 model and adds electronic control signal coupling simulation function. It is used to calculate the response of the closed-loop system composed of the overall model, control model, sensor model and other components under external commands. It needs to include engine control plan, control logic, control algorithm and other contents, and support sensor performance characteristics and fault simulation capabilities.

[0085] The L3 model is based on the L2 model and adds coupled simulation functions for mechanical and hydraulic parameters. It is used to calculate the system response results when considering the component-level mechanism model of the mechanical and hydraulic system. It requires the establishment of component-level mechanism models of systems such as fuel regulation, transmission, starter, generator, and load, and can support mechanical and hydraulic performance characteristics and fault simulation capabilities.

[0086] The L4 model is based on the L3 model and adds coupled simulation function of heat transfer parameters. It is used to calculate the heat transfer and temperature rise between different systems of the aero-engine as the engine operates. It requires the establishment of component-level mechanism models of the lubricating oil system, air system and related systems (such as thermal simulation model of fuel control system, fuel lubricating oil heat transfer model, etc.) and can support heat transfer performance characteristics and fault simulation capabilities.

[0087] The L5 model is based on the L4 model and adds the function of coupled simulation of external condition parameters. It is used to calculate the response of each system model of the aero-engine after coupling with the aircraft or test bench model. It needs to realize the coupling of mechanical, electrical, control, gas, liquid and thermal signals between the aero-engine model and the aircraft or test bench model, and support the dynamic evolution simulation capability of environmental conditions.

[0088] Based on the above scheme, by adopting a hierarchical and progressive modeling approach, the coupled models constructed at different modeling levels not only include the coupled models of each modeling level, but also the coupling logic related to other disciplines, thus ensuring the comprehensiveness and practicality of the constructed coupled models.

[0089] Optionally, based on the coupling mechanism model of each level of the aero-engine, the simulation operation models of each discipline are processed for operation association to obtain the simulation coupling model of the aero-engine. This includes: generating data interaction logic between the simulation operation models of each discipline based on each discipline corresponding to each coupling model, and constructing a coupled simulation function model between the simulation operation models of each discipline based on each coupling model and the data interaction logic between the simulation operation models of each discipline; and performing model association processing on the simulation operation models of each discipline and the coupled simulation function model between the simulation operation models to obtain the simulation coupling model of the aero-engine.

[0090] In this embodiment, the terminal generates data interaction logic between simulation operation models of each discipline based on each coupled model, and constructs a coupled simulation function model between simulation operation models of each discipline based on each coupled model and the data interaction logic between simulation operation models of each discipline. The data interaction logic consists of the data interaction information between the two disciplines during actual operation, and the interaction coupling logic corresponding to the operation interaction information.

[0091] Then, the terminal performs model association processing on the simulation operation models of each discipline and the coupled simulation function models between each simulation operation model to obtain the simulation coupling model of the aero-engine.

[0092] Based on the above scheme, after identifying the data interaction logic of the simulation operation models of each discipline, a coupled simulation function model between the simulation operation models of each discipline is constructed, thereby improving the simulation coupling effect between multiple simulation operation models.

[0093] Optionally, based on simulation operating condition information and simulation condition information, the operation process of the aero-engine is simulated through a simulation coupling model to obtain the simulation operation results of the aero-engine. This includes: identifying the environmental input data and operating condition input data of the aero-engine based on the simulation operating condition information and simulation condition information; inputting the environmental input data and operating condition input data into the simulation coupling model to simulate the operation process of the aero-engine and obtain the simulation operation results of the aero-engine.

[0094] In this embodiment, the terminal identifies the environmental input data and operating condition input data of the aero-engine based on simulation operating condition information and simulation condition information. The simulation operating condition information includes simulation requirement data for various disciplines corresponding to the operating conditions to be simulated by the aero-engine. The terminal then breaks down and normalizes the simulation requirement data for each discipline to obtain the simulation requirement data. The simulation condition information includes the environmental conditions of different aero-engines and the operating conditions of the aero-engine itself. Finally, the terminal extracts the data corresponding to each environmental condition and operating condition to obtain the simulation operation results of the aero-engine.

[0095] Next, the terminal inputs environmental and operational condition data into the simulation coupling model to simulate the operation of the aero-engine and obtain the simulation results. During the actual simulation, the simulation coupling model interacts with the engine according to the following relationships: Before calculation, the overall engine performance model needs to read the latest data from the fuel conditioning system model (control inputs), the air system model (bleed air volume and cooling / heat transfer data), the starter's status and inputs, the power consumption values ​​of the transmission system model and the power generation system model, and environmental conditions. After the model parameters are calculated, it needs to update the required measurement variables of the sensor system model, the temperature and pressure parameters of the air system interface, the load force and speed of each bearing in the lubricating oil system, and the transmission system speed. The sensor system calculates the model output based on the status parameters input from the overall engine performance model and updates it to the control system. The control system model needs to read the measurement results from the sensor system, receive the latest control commands from the aircraft system / ground test system, and update the control signals of the fuel conditioning system, starter, power generation system, and other parts based on the latest model calculation results. The fuel control system model needs to read the latest values ​​of the transmission system's speed signal, the control system's control signal, and the lubricating oil system's heat exchange temperature rise. Based on the model's mechanism, it calculates the latest operating results and updates the control variables provided to the overall engine performance model. The lubricating oil system model needs to read the latest results of the engine's bearing load and speed, fuel-lubricating oil heat exchange results, and bearing cavity air pressure and flow rate. Based on the model's mechanism, it calculates the latest operating results and updates the lubricating oil temperature, flow rate, and other parameters of the fuel-lubricating oil heat exchanger. The air system model needs to read the pressure and temperature values ​​at the required locations from the overall engine performance model and update the bleed air flow rate and cooling / heat transfer parameters at each location based on the model's calculation results.

[0096] Based on the above scheme, by decomposing the simulation operating condition information and simulation condition information, the environmental input data and operating condition input data of the aero-engine are obtained. Then, the operation process of the aero-engine is simulated through the simulation coupling model, thereby improving the simulation efficiency and accuracy of the aero-engine.

[0097] Optionally, based on the simulation results of aero-engines, the simulation operation information of various disciplines of aero-engines is identified, including: breaking down the simulation results of aero-engines into sub-simulation results of each discipline, and based on the sub-simulation results of each discipline, identifying the simulation operation data distribution information of each operation function of each discipline; based on the simulation operation data distribution information of each operation function of each discipline, identifying the operation anomaly information and the functional risk information of each operation function of each discipline through the functional evaluation strategy of each discipline, and using the operation anomaly information and the functional risk information of each operation function of each discipline as the simulation operation information of each discipline.

[0098] In this embodiment, the terminal breaks down the simulation results of the aero-engine into sub-simulation results for each discipline, and identifies the simulation data distribution information of each operational function within each discipline based on the sub-simulation results. Each discipline corresponds to one or more operational functions, and the obtained aero-engine simulation results contain operational data for each operational function throughout the entire simulation phase. By sorting the operational data according to their distribution over time, the simulation data distribution information for each operational function can be obtained.

[0099] Finally, based on the simulation operation data distribution information of each function in each discipline, the terminal identifies the operational anomaly information and functional risk information of each function in each discipline through the functional evaluation strategy of each discipline. The functional evaluation strategy for each discipline includes sub-functional evaluation strategies for each function, and each sub-evaluation strategy includes the normal operation data distribution range and normal operation data distribution trend for each function. Based on the simulation operation data distribution information of each function in each discipline, the terminal filters abnormal data distribution information and abnormal data distribution trends from the access operation data distribution information of each function according to the normal operation data distribution range and normal operation data distribution trend. These abnormal data distribution information and abnormal data distribution trends are then used as the operational anomaly information for each function in each discipline. Next, the terminal selects the distribution range with the largest distribution deviation from the abnormal data distribution information as the functional risk information for each function in each discipline. Finally, the terminal uses the operational anomaly information and functional risk information of each function in each discipline as the simulation operation information for each discipline.

[0100] Based on the above scheme, after simulation, the operational functions of each discipline are broken down and analyzed, which improves the comprehensiveness and accuracy of the simulation operation information of each discipline obtained from the analysis.

[0101] This application also provides an example of multidisciplinary simulation coupling for aero-engines, such as... Figure 2 As shown, the specific processing procedure includes the following steps:

[0102] Step S201: Obtain the simulation operation models of various disciplines of aero-engine, as well as the information on the correlation mechanisms between these disciplines.

[0103] Step S202: Based on the correlation mechanism information between disciplines, identify the coupling-related information between disciplines, and based on the coupling-related information between disciplines, query the coupling type and coupling logic information corresponding to each coupling-related information in the coupling database.

[0104] Step S203: The coupling logic information corresponding to each coupling-related information is used as the coupling information of the coupling type corresponding to each coupling-related information.

[0105] Step S204: Based on the coupling information of each coupling type, query the modeling level corresponding to each coupling type and the parameter transformation strategy corresponding to each coupling type in the hierarchical coupling modeling database, and parameterize the coupling information of each coupling type according to the parameter transformation strategy corresponding to each coupling type to obtain the coupling parameters of each coupling type.

[0106] Step S205: According to the order of modeling levels, filter each first coupling type corresponding to the first modeling level, and perform correlation modeling processing based on the coupling parameters of each first coupling type to obtain each first coupling model corresponding to the first modeling level.

[0107] Step S206: According to the order of modeling levels, filter the second modeling levels after the first modeling level, and construct the second coupling models corresponding to each second modeling level based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling models corresponding to the first modeling level.

[0108] Step S207: According to the order of modeling levels, filter the third modeling level after the second modeling level, replace the second modeling level with the third modeling level, and return to execute the step of constructing the second coupling model corresponding to each second modeling level based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling model corresponding to each first modeling level, until the coupling model corresponding to all modeling levels is obtained.

[0109] Step S208: Use each coupling model corresponding to each modeling level as the coupling mechanism model of each level of the aero-engine.

[0110] Step S209: Based on each discipline corresponding to each coupled model, generate the data interaction logic between the simulation operation models of each discipline, and based on each coupled model and the data interaction logic between the simulation operation models of each discipline, construct the coupled simulation function model between the simulation operation models of each discipline.

[0111] Step S210 involves performing model association processing on the simulation operation models of each discipline and the coupled simulation function models between each simulation operation model to obtain the simulation coupling model of the aero-engine.

[0112] Step S211: Collect simulation operating condition information and simulation condition information of the aero-engine.

[0113] Step S212: Based on the simulation operating condition information and simulation condition information, identify the environmental input data and operating condition input data of the aero-engine.

[0114] Step S213: Input the environmental input data and the operating condition input data into the simulation coupling model to simulate the operation process of the aero-engine and obtain the simulation operation results of the aero-engine.

[0115] Step S214: The simulation results of the aero-engine are broken down into sub-simulation results of each discipline, and the simulation data distribution information of each discipline's operation functions is identified based on the sub-simulation results of each discipline.

[0116] Step S215: Based on the simulation operation data distribution information of each operation function of each discipline, the operation anomaly information and the function risk information of each operation function of each discipline are identified through the function evaluation strategy of each discipline, and the operation anomaly information and the function risk information of each operation function of each discipline are used as the simulation operation information of each discipline.

[0117] It should be understood that although the steps in the flowcharts of the embodiments described above are shown sequentially according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some steps in the flowcharts of the embodiments described above may include multiple steps or multiple stages. These steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these steps or stages is not necessarily sequential, but can be performed alternately or in turn with other steps or at least some of the steps or stages of other steps.

[0118] Based on the same inventive concept, this application also provides a multidisciplinary simulation coupling device for aero-engines to implement the aforementioned multidisciplinary simulation coupling method. The solution provided by this device is similar to the solution described in the above method; therefore, the specific limitations of one or more embodiments of the multidisciplinary simulation coupling device for aero-engines provided below can be found in the limitations of the multidisciplinary simulation coupling method for aero-engines described above, and will not be repeated here.

[0119] In one exemplary embodiment, such as Figure 3 As shown, a multidisciplinary simulation coupling device for an aero-engine is provided, comprising: an acquisition module 310, a coupling module 320, a simulation module 330, and an identification module 340, wherein:

[0120] The acquisition module 310 is used to acquire the simulation operation model of each discipline of the aero-engine, as well as the correlation mechanism information between each discipline, and to identify the coupling information of each coupling type between each discipline based on the correlation mechanism information between each discipline.

[0121] The coupling module 320 is used to construct the coupling mechanism models of the aero-engine at all levels based on the coupling information of each coupling type between the disciplines, through a hierarchical coupling modeling strategy, and to perform operational correlation processing on the simulation operation models of each discipline based on the coupling mechanism models of the aero-engine at all levels, so as to obtain the simulation coupling model of the aero-engine.

[0122] The simulation module 330 is used to collect the simulation operating condition information and simulation condition information of the aero-engine, and based on the simulation operating condition information and simulation condition information, simulate the operation process of the aero-engine through the simulation coupling model to obtain the simulation operation results of the aero-engine.

[0123] The identification module 340 is used to identify the simulation operation information of various disciplines of the aero-engine based on the simulation operation results of the aero-engine.

[0124] Optionally, the acquisition module 310 is specifically used for:

[0125] Based on the correlation mechanism information between the disciplines, identify the coupling-related information between the disciplines, and based on the coupling-related information between the disciplines, query the coupling type and coupling logic information corresponding to each coupling-related information in the coupling database.

[0126] The coupling logic information corresponding to each coupling-related information is used as the coupling information of the coupling type corresponding to each coupling-related information.

[0127] Optionally, the coupling module 320 is specifically used for:

[0128] Based on the coupling information of each coupling type, in the hierarchical coupling modeling database, the modeling level corresponding to each coupling type and the parameter transformation strategy corresponding to each coupling type are queried. Based on the parameter transformation strategy corresponding to each coupling type, the coupling information of each coupling type is parameterized to obtain the coupling parameters of each coupling type.

[0129] According to the order of modeling levels, each first coupling type corresponding to the first modeling level is selected, and the association modeling process is performed based on the coupling parameters of each first coupling type to obtain each first coupling model corresponding to the first modeling level.

[0130] According to the order of modeling levels, the second modeling levels after the first modeling level are selected, and based on the coupling parameters of each first coupling type corresponding to the second modeling level and each coupling model corresponding to the first modeling level, each second coupling model corresponding to the second modeling level is constructed.

[0131] According to the order of modeling levels, the third modeling level after the second modeling level is selected, and the third modeling level replaces the second modeling level. Then, the process of constructing the second coupling model corresponding to each second modeling level is carried out based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling model corresponding to the first modeling level, until the coupling model corresponding to all modeling levels is obtained.

[0132] Each coupling model corresponding to each modeling level is used as the coupling mechanism model of each level of the aero-engine.

[0133] Optionally, the coupling module 320 is specifically used for:

[0134] Based on each discipline corresponding to each coupled model, data interaction logic between the simulation operation models of each discipline is generated, and based on each coupled model and the data interaction logic between the simulation operation models of each discipline, a coupled simulation function model between the simulation operation models of each discipline is constructed.

[0135] The simulation operation models of each discipline and the coupled simulation function models between each simulation operation model are subjected to model association processing to obtain the simulation coupling model of the aero-engine.

[0136] Optionally, the simulation module 330 is specifically used for:

[0137] Based on the simulation operating condition information and the simulation condition information, the environmental input data and the operating condition input data of the aero-engine are identified.

[0138] The environmental input data and the operating condition input data are input into the simulation coupling model to simulate the operation process of the aero-engine and obtain the simulation operation results of the aero-engine.

[0139] Optionally, the identification module 340 is specifically used for:

[0140] The simulation results of the aero-engine are broken down into sub-simulation results of each discipline, and the simulation data distribution information of each operational function of each discipline is identified based on the sub-simulation results of each discipline.

[0141] Based on the distribution information of simulation operation data of each function in each discipline, and through the functional evaluation strategy of each discipline, the abnormal operation information and functional risk information of each function in each discipline are identified, and the abnormal operation information and functional risk information of each function in each discipline are used as the simulation operation information of each discipline.

[0142] The modules in the aforementioned multidisciplinary simulation coupling device for aero-engines can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device, or stored in the memory of a computer device as software, so that the processor can call and execute the corresponding operations of each module.

[0143] In one exemplary embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as follows: Figure 4 As shown, the computer device includes a processor, memory, input / output interface, communication interface, display unit, and input device. The processor, memory, and input / output interface are connected via a system bus, and the communication interface, display unit, and input device are also connected to the system bus via the input / output interface. The processor provides computational and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The input / output interface is used for exchanging information between the processor and external devices. The communication interface is used for wired or wireless communication with external terminals; wireless communication can be achieved through Wi-Fi, mobile cellular networks, NFC (Near Field Communication), or other technologies. When the computer program is executed by the processor, it implements a multidisciplinary simulation coupling method for aero-engines. The display unit is used to form a visually visible image and can be a display screen, projection device, or virtual reality imaging device. The display screen can be an LCD screen or an e-ink screen. The input device of the computer device can be a touch layer covering the display screen, or buttons, trackballs, or touchpads set on the casing of the computer device, or external keyboards, touchpads, or mice, etc.

[0144] Those skilled in the art will understand that Figure 4 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0145] In one exemplary embodiment, a computer device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the steps of a multidisciplinary simulation coupling method for an aero-engine.

[0146] In one embodiment, a computer-readable storage medium is provided having a computer program stored thereon, the computer program being executed by a processor to implement the steps of a multidisciplinary simulation coupling method for an aero-engine.

[0147] In one embodiment, a computer program product is provided, including a computer program that, when executed by a processor, implements the steps of a multidisciplinary simulation coupling method for an aero-engine.

[0148] 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, data stored, data displayed, 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 the relevant data must comply with relevant regulations.

[0149] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium. When executed, the computer program can include the processes of the embodiments described above. Any references to memory, databases, or other media used in the embodiments provided in this 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 can take many forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM). The databases involved in the embodiments provided in this application may include at least one type of relational database and non-relational database. Non-relational databases may include, but are not limited to, blockchain-based distributed databases. The processors involved in the embodiments provided in this application may be general-purpose processors, central processing units, graphics processing units, digital signal processors, programmable logic devices, quantum computing-based data processing logic devices, etc., and are not limited to these.

[0150] The technical features of the above embodiments can be combined in any way. For the sake of brevity, 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.

[0151] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. A multidisciplinary simulation coupling method for aero-engines, characterized in that, The method includes: The simulation operation models of various disciplines of aero-engines and the correlation mechanism information between these disciplines are obtained, and based on the correlation mechanism information between these disciplines, the coupling information of each coupling type between these disciplines is identified; Based on the coupling information of each coupling type, in the hierarchical coupling modeling database, the modeling level corresponding to each coupling type and the parameter transformation strategy corresponding to each coupling type are queried. Based on the parameter transformation strategy corresponding to each coupling type, the coupling information of each coupling type is parameterized to obtain the coupling parameters of each coupling type. According to the order of modeling levels, each first coupling type corresponding to the first modeling level is selected, and the association modeling process is performed based on the coupling parameters of each first coupling type to obtain each first coupling model corresponding to the first modeling level. According to the order of modeling levels, the second modeling levels after the first modeling level are selected, and based on the coupling parameters of each first coupling type corresponding to the second modeling level and each coupling model corresponding to the first modeling level, each second coupling model corresponding to the second modeling level is constructed. According to the order of modeling levels, the third modeling level after the second modeling level is selected, and the third modeling level replaces the second modeling level. Then, the process of constructing the second coupling model corresponding to each second modeling level is carried out based on the coupling parameters of each first coupling type corresponding to the second modeling level and the coupling model corresponding to the first modeling level, until the coupling model corresponding to all modeling levels is obtained. Each coupling model corresponding to each modeling level is used as the coupling mechanism model of each level of the aero-engine; Based on the coupling mechanism model of the aero-engine at each level, the simulation operation models of each discipline are subjected to operation correlation processing to obtain the simulation coupling model of the aero-engine. The simulation operating condition information and simulation condition information of the aero-engine are collected, and based on the simulation operating condition information and simulation condition information, the operation process of the aero-engine is simulated through the simulation coupling model to obtain the simulation operation results of the aero-engine. Based on the simulation results of the aero-engine, the simulation operation information of various disciplines of the aero-engine is identified.

2. The method according to claim 1, characterized in that, The coupling information, based on the association mechanism information between the disciplines, identifies the coupling information of various coupling types between the disciplines, including: Based on the correlation mechanism information between the disciplines, identify the coupling-related information between the disciplines, and based on the coupling-related information between the disciplines, query the coupling type and coupling logic information corresponding to each coupling-related information in the coupling database. The coupling logic information corresponding to each coupling-related information is used as the coupling information of the coupling type corresponding to each coupling-related information.

3. The method according to claim 1, characterized in that, The aforementioned simulation coupling model based on the various coupling mechanism models of the aero-engine performs operational correlation processing on the simulation operation models of each discipline to obtain the simulation coupling model of the aero-engine, including: Based on each discipline corresponding to each coupled model, data interaction logic between the simulation operation models of each discipline is generated, and based on each coupled model and the data interaction logic between the simulation operation models of each discipline, a coupled simulation function model between the simulation operation models of each discipline is constructed. The simulation operation models of each discipline and the coupled simulation function models between each simulation operation model are subjected to model association processing to obtain the simulation coupling model of the aero-engine.

4. The method according to claim 1, characterized in that, The process of simulating the operation of the aero-engine based on the simulation operating condition information and the simulation condition information, through the simulation coupling model, to obtain the simulation operation results of the aero-engine includes: Based on the simulation operating condition information and the simulation condition information, the environmental input data and the operating condition input data of the aero-engine are identified. The environmental input data and the operating condition input data are input into the simulation coupling model to simulate the operation process of the aero-engine and obtain the simulation operation results of the aero-engine.

5. The method according to claim 4, characterized in that, The method of identifying simulation operation information of various disciplines related to the aero-engine based on the simulation operation results of the aero-engine includes: The simulation results of the aero-engine are broken down into sub-simulation results of each discipline, and the simulation data distribution information of each operational function of each discipline is identified based on the sub-simulation results of each discipline. Based on the distribution information of simulation operation data of each function in each discipline, and through the functional evaluation strategy of each discipline, the abnormal operation information and functional risk information of each function in each discipline are identified, and the abnormal operation information and functional risk information of each function in each discipline are used as the simulation operation information of each discipline.

6. A multidisciplinary simulation coupling device for an aero-engine, characterized in that, The device includes: The acquisition module is used to acquire the simulation operation models of various disciplines of aero-engines, as well as the correlation mechanism information between the disciplines, and based on the correlation mechanism information between the disciplines, to identify the coupling information of each coupling type between the disciplines. The coupling module is used to query the modeling level corresponding to each coupling type and the parameter transformation strategy corresponding to each coupling type in the hierarchical coupling modeling database based on the coupling information of each coupling type, and to parameterize the coupling information of each coupling type based on the parameter transformation strategy corresponding to each coupling type to obtain the coupling parameters of each coupling type; according to the order of modeling levels, it filters each first coupling type corresponding to the first modeling level, and performs correlation modeling processing based on the coupling parameters of each first coupling type to obtain each first coupling model corresponding to the first modeling level; according to the order of modeling levels, it filters the second modeling level after the first modeling level, and based on the coupling parameters of each first coupling type corresponding to the second modeling level and the first modeling level... For each corresponding coupling model, construct each second coupling model corresponding to each second modeling level; according to the order of modeling levels, filter the third modeling level after the second modeling level, and replace the second modeling level with the third modeling level; return to execute the step of constructing each second coupling model corresponding to each second modeling level based on the coupling parameters of each first coupling type corresponding to the second modeling level and each coupling model corresponding to the first modeling level, until all coupling models corresponding to all modeling levels are obtained; each coupling model corresponding to each modeling level is used as the coupling mechanism model of each level of the aero-engine; based on the coupling mechanism model of each level of the aero-engine, perform operation association processing on the simulation operation model of each discipline to obtain the simulation coupling model of the aero-engine; The simulation module is used to collect the simulation operating condition information and simulation condition information of the aero-engine, and based on the simulation operating condition information and simulation condition information, simulate the operation process of the aero-engine through the simulation coupling model to obtain the simulation operation results of the aero-engine. The identification module is used to identify the simulation operation information of various disciplines of the aero-engine based on the simulation operation results of the aero-engine.

7. The apparatus according to claim 6, characterized in that, The acquisition module is specifically used for: Based on the correlation mechanism information between the disciplines, identify the coupling-related information between the disciplines, and based on the coupling-related information between the disciplines, query the coupling type and coupling logic information corresponding to each coupling-related information in the coupling database. The coupling logic information corresponding to each coupling-related information is used as the coupling information of the coupling type corresponding to each coupling-related information.

8. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 5.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 5.

10. A computer program product, comprising a computer program, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 5.

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