Aero-engine cross-dimension calculation method, device and equipment and readable storage medium

Abstract

The invention relates to an aero-engine cross-dimension calculation method and device, equipment and a readable storage medium. The method comprises the following steps: acquiring a throttle lever position of the aero-engine and a model type of each engine component in the aero-engine; according to the position of the throttle lever and the model type, calculation processing of corresponding dimensions is conducted on all the engine components in sequence, and input parameters of all the component models are obtained; wherein physical field representation dimensions adopted by different dimension models of the engine component are different; and determining performance parameters of the aero-engine based on the position of the throttle lever and the input parameters of the component models. By adopting the method, the performance parameter calculation precision can be improved.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and particularly to a cross-dimensional calculation method, device, equipment, and readable storage medium for an aeroengine. Background Art

[0002] Currently, the mainstream in the overall performance calculation software for aeroengines are GasTurb from Germany and PROOSIS from the European Union. Both of these design software adopt zero-dimensional design methods, establish mathematical models relying on thermodynamic formulas, and perform calculations in combination with some empirical data to obtain the performance parameters of aeroengines.

[0003] However, the component characteristics of the zero-dimensional calculation method adopt a universal characteristic diagram, resulting in low accuracy of the calculated performance parameters. Summary of the Invention

[0004] Based on this, it is necessary to provide a cross-dimensional calculation method, device, equipment, and readable storage medium for an aeroengine that can improve the calculation accuracy of performance parameters in response to the above technical problems.

[0005] In a first aspect, this application provides a cross-dimensional calculation method for an aeroengine, including:

[0006] Obtain the throttle lever position of the aeroengine and the component model types of each engine component in the aeroengine;

[0007] According to the throttle lever position and the component model types, perform corresponding-dimensional calculation processing on each engine component in sequence to obtain the input parameters of each component model; wherein, the physical field characterization dimensions adopted by different-dimensional models of engine components are different;

[0008] Determine the performance parameters of the aeroengine based on the throttle lever position and the input parameters of each component model.

[0009] In one of the embodiments, the above component model types include the dimension and function of the model. The above-mentioned iterative calculation under the common working constraint conditions of each engine component using the corresponding-dimensional calculation model according to the throttle lever position and the component model types to obtain the input parameters of each component model includes:

[0010] Determine the vector to be solved in the common working equation set of the calculation model according to the throttle lever position;

[0011] Determine the calculation order of multiple engine components according to the function of the model;

[0012] According to the calculation order and the dimensions of the model, the target dimension calculation models corresponding to each engine component are determined in sequence, and the input parameters of each component model are determined by using the target dimension calculation models corresponding to each engine component; wherein, the target dimension calculation model is a zero-dimensional calculation model or a multi-dimensional calculation model.

[0013] In one embodiment, the above determining the input parameters of each component model by using the target dimension calculation models corresponding to each engine component includes:

[0014] When the target dimension calculation model corresponding to the engine component is a zero-dimensional calculation model, the input parameters of the component model are determined according to the input parameters and output parameters of the zero-dimensional calculation model;

[0015] When the target dimension calculation model corresponding to the engine component is a multi-dimensional calculation model, the multi-dimensional calculation model is called, and the input parameters of the component model are determined based on the input parameters and output parameters of the multi-dimensional calculation model.

[0016] In one embodiment, the above calling the multi-dimensional calculation model includes:

[0017] Obtain a zero-dimensional - multi-dimensional interaction instruction set;

[0018] Call the multi-dimensional calculation model based on the zero-dimensional - multi-dimensional interaction instruction set;

[0019] The method further includes:

[0020] Write the input parameters of the component model determined based on the multi-dimensional calculation model into the zero-dimensional - multi-dimensional interaction instruction set.

[0021] In one embodiment, the above determining the performance parameters of the aeroengine based on the throttle lever position and the input parameters of each component model includes:

[0022] Determine the parameter convergence situation according to the input parameters of multiple component models;

[0023] When the input parameters of multiple component models converge, determine the performance parameters of the aeroengine based on the throttle lever position.

[0024] In one embodiment, the above method further includes:

[0025] When the input parameters of multiple component models do not converge, update the initial guess values of the input parameters of the component model until the input parameters of multiple component models converge;

[0026] Determine the performance parameters of the aeroengine based on the updated input parameters of the component model.

[0027] In a second aspect, the present application further provides an aeroengine cross-dimension calculation device, including:

[0028] An acquisition module, configured to acquire the throttle lever position of an aeroengine and the component model types of each engine component in the aeroengine;

[0029] A calculation module, configured to perform calculation processing on each engine component in corresponding dimensions according to the throttle lever position and the component model type to obtain the input parameters of each component model; wherein, different dimensional models of engine components adopt different physical field characterization dimensions;

[0030] A determination module, configured to determine the performance parameters of the aeroengine based on the input parameters of each component model that satisfy the co-working constraints of the engine.

[0031] In a third aspect, the present application further provides a computer device, including a memory and a processor, the memory stores a computer program, and when the processor executes the computer program, the following steps are implemented:

[0032] Acquire the throttle lever position of the aeroengine and the model types of each engine component in the aeroengine;

[0033] According to the throttle lever position and the model type, perform calculation processing on each engine component in corresponding dimensions to obtain the input parameters of each component model; wherein, different dimensional models of engine components adopt different physical field characterization dimensions;

[0034] Determine the performance parameters of the aeroengine based on the throttle lever position and the input parameters of each component model.

[0035] In a fourth aspect, the present application further provides a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the following steps are implemented:

[0036] Acquire the throttle lever position of the aeroengine and the model types of each engine component in the aeroengine;

[0037] According to the throttle lever position and the model type, perform calculation processing on each engine component in corresponding dimensions to obtain the input parameters of each component model; wherein, different dimensional models of engine components adopt different physical field characterization dimensions;

[0038] Determine the performance parameters of the aeroengine based on the throttle lever position and the input parameters of each component model.

[0039] In a fifth aspect, the present application further provides a computer program product, including a computer program, and when the computer program is executed by a processor, the following steps are implemented:

[0040] Acquire the throttle lever position of the aeroengine and the model types of each engine component in the aeroengine;

[0041] According to the throttle lever position and the model type, the calculation processing of each engine component is sequentially performed in the corresponding dimension to obtain the input parameters of each component model; wherein, the physical field representation dimensions adopted by different dimension models of the engine components are different;

[0042] Determine the performance parameters of the aero-engine based on the throttle lever position and the input parameters of each component model.

[0043] The above-mentioned cross-dimensional calculation method, device, equipment, and readable storage medium for aero-engines first obtain the throttle lever position of the aero-engine and the model types of each engine component in the aero-engine; then, according to the throttle lever position and the model type, the calculation processing of each engine component is sequentially performed in the corresponding dimension to obtain the input parameters of each component model; wherein, the physical field representation dimensions adopted by different dimension models of the engine components are different; finally, determine the performance parameters of the aero-engine based on the throttle lever position and the input parameters of each component model; the traditional technology usually only uses a zero-dimensional calculation model, and this zero-dimensional calculation model cannot fully reflect the diversity and details of complex aero-engines. However, the present application adopts different physical field representation dimensions for engine components of different dimensions, which can penetrate into the internal structure and flow process of each component and consider more spatial variables and time changes. Therefore, compared with the traditional zero-dimensional calculation model, the multi-dimensional calculation method of the present application can provide a higher-precision performance evaluation and greatly improve the accuracy of calculating the performance parameters of aero-engines. Description of the Drawings

[0044] In order to more clearly illustrate the technical solutions in the embodiments of the present application or related technologies, the following will briefly introduce the drawings required for use in the description of the embodiments of the present application or related technologies. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other related drawings can be obtained based on these drawings without creative efforts.

[0045] Figure 1 It is the internal structure diagram of a computer device in an embodiment;

[0046] Figure 2 It is the flow diagram of the cross-dimensional calculation method of aero-engines in an embodiment;

[0047] Figure 3 It is the flow diagram of the cross-dimensional calculation method of aero-engines in another embodiment;

[0048] Figure 4 It is the flow diagram of the cross-dimensional calculation method of aero-engines in another embodiment;

[0049] Figure 5 It is the flow diagram of the cross-dimensional calculation method of aero-engines in another embodiment;

[0050] Figure 6 is a schematic flow chart of an aero-engine cross-dimensional calculation method in another embodiment;

[0051] Figure 7 is a structural block diagram of an aero-engine cross-dimensional calculation device in one embodiment. Detailed implementation manners

[0052] In order to make the objectives, technical solutions and advantages of the present application clearer and more understandable, the present application will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0053] In an exemplary embodiment, a computer device is provided. The computer device may be a server, and its internal structure diagram may be as Figure 1 shown. The computer device includes a processor, a memory, an input / output interface (Input / Output, abbreviated as I / O), and a communication interface. Among them, the processor, the memory, and the input / output interface are connected through a system bus, and the communication interface is connected to the system bus through the input / output interface. 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, a computer program, and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store data in the process of aero-engine cross-dimensional calculation. The input / output interface of the computer device is used to exchange information between the processor and external devices. The communication interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, it implements an aero-engine cross-dimensional calculation method.

[0054] Those skilled in the art can understand that Figure 1 the structure shown in

[0055] In an exemplary embodiment, as Figure 2 shown, an aero-engine cross-dimensional calculation method is provided. Taking the method applied to the computer device in Figure 1 as an example, it includes the following steps 201 to step 203. Among them:

[0056] Step 201: Obtain the throttle lever position of the aeroengine and the component model types of each engine component in the aeroengine.

[0057] Among them, the throttle lever position refers to information about the basic data and operating status of the aeroengine, which may include engine model, operating environment, fuel type, etc.

[0058] In the embodiment of the present application, first, the computer device needs to collect the throttle lever position. Among them, the throttle lever position may include the vector to be solved in the common working equations. The elements of the vector to be solved in the common working equations may include:

[0059] (1) The relative proportion values of the auxiliary lines of the fan, compressor, and turbine: It can characterize the flow path of the air flow in the engine and the pressure change and flow velocity change in each component.

[0060] (2) The outlet pressure value of the nozzle: It can characterize the gas pressure at the exhaust port of the jet engine.

[0061] (3) The rotational speed values of the high-speed and low-speed shafts: It can determine the rotational speed matching and power transmission efficiency of each component of the engine.

[0062] After the computer device obtains the vector to be solved in the common working equations of the engine, it then needs to collect information on each engine component that makes up the aeroengine. The components of the aeroengine include an air intake, a fan, a compressor, a combustion chamber, a turbine, a nozzle, etc. Each component has a unique structure and working principle, so different information needs to be obtained according to the different characteristics of the components:

[0063] (1) Two-dimensional calculation: For example, for the fan component, two-dimensional calculation is usually adopted, focusing on the changes of the air flow on the plane, and analyzing the aerodynamic performance and pressure distribution of the fan blades.

[0064] (2) Three-dimensional calculation: For example, for the turbine component, the working state of the turbine is affected by a complex flow field. Usually, three-dimensional calculation is required to analyze the changes of the air flow in three-dimensional space and calculate the temperature, pressure, and velocity field distributions inside the turbine.

[0065] (3) Zero-dimensional calculation: For some simple components, such as the air intake, a zero-dimensional calculation model can be adopted, that is, analyze it through a simplified thermodynamics and fluid mechanics model, focusing on the overall state of the fluid rather than local details.

[0066] Step 202: According to the throttle lever position and the component model type, perform corresponding-dimensional calculation processing on each engine component in sequence to obtain the input parameters of each component model; among them, the physical field characterization dimensions adopted by different-dimensional models of the engine components are different.

[0067] Among them, the aerodynamic performance parameters refer to the performance data of engine components under specific working conditions, such as pressure ratio, isentropic efficiency, total pressure loss coefficient, etc.

[0068] In the embodiments of the present application, the computer device performs corresponding-dimensional calculation processing on each engine component in sequence according to the throttle lever position and the model type, and obtains the input parameters of each component model.

[0069] In some embodiments, the computer device can select the corresponding physical field characterization dimension and calculation model according to the characteristics of each engine component. The selection of the physical field characterization dimension of each engine component can be based on its physical properties and the complexity of the working state. For example:

[0070] (1) The fan component usually performs two-dimensional aerodynamic calculations, focusing on analyzing the distribution of air flow on the fan blade surface and calculating the changes in air flow pressure and velocity.

[0071] (2) Compressor: The compressor usually involves three-dimensional calculations because the distribution and changes of air flow on the compressor blades are relatively complex and multi-dimensional air flow needs to be considered.

[0072] (3) Turbine: Due to the influence of various factors, the turbine part usually uses a three-dimensional calculation model to accurately describe the air flow, temperature and blade force conditions.

[0073] (4) Combustion chamber and nozzle: The combustion chamber and nozzle usually use a zero-dimensional or simplified one-dimensional calculation model, focusing on the changes in temperature and pressure, as well as the efficiency of the combustion process.

[0074] After obtaining the information of all components and selecting the appropriate calculation model, the computer device starts to calculate each component to obtain the aerodynamic performance parameters of each component.

[0075] For example, for the fan component, the computer device can calculate the air flow distribution, pressure change, air flow velocity, etc. on the fan blade through a two-dimensional aerodynamic model.

[0076] For the turbine component, the computer device performs three-dimensional flow field calculations and calculates the stress, thermal stress, etc. of the blades according to the rotation speed and temperature of the turbine blades.

[0077] For the combustion chamber and nozzle, the computer device analyzes the combustion process, pressure distribution and heat exchange process through a zero-dimensional model to determine the working efficiency of the combustion chamber and the air flow velocity of the nozzle.

[0078] Step 203, determine the performance parameters of the aeroengine based on the throttle lever position and the input parameters of each component model.

[0079] In the embodiments of the present application, the computer device determines the performance parameters of the aeroengine based on the throttle lever position and the input parameters of each component model.

[0080] In some embodiments, after the aerodynamic performance parameters of each component are calculated, the computer device integrates these aerodynamic performance parameters to evaluate the overall performance of the aeroengine. For example, the thrust and fuel consumption rate of the aeroengine can be evaluated.

[0081] Among them, the computer device calculates the thrust output by combining the aerodynamic performance parameters of the turbine and the nozzle. Based on the engine thrust and fuel consumption data, the fuel consumption efficiency of the aeroengine is calculated. By synthesizing the performance of each component, the thermal efficiency, mechanical efficiency, etc. of the engine are evaluated by comparing the working states of each engine component.

[0082] In some embodiments, according to the calculated performance parameters, the computer device gives feedback to evaluate the operating condition of the engine. If the performance parameters do not meet the standards, the computer device will identify the engine components that affect the performance and recommend corresponding optimization measures. These optimization measures can include adjusting the cooling effect of the turbine, improving the efficiency of the compressor, and improving the design of the nozzle, etc.

[0083] In the above cross-dimensional calculation method of the aeroengine, first, the throttle lever position of the aeroengine and the model types of each engine component in the aeroengine are obtained; then, according to the throttle lever position and the model types, corresponding-dimensional calculation processing is sequentially performed on each engine component to obtain the input parameters of each component model; among them, different-dimensional models of engine components adopt different physical field characterization dimensions; finally, based on the throttle lever position and the input parameters of each component model, the performance parameters of the aeroengine are determined; traditional technologies usually only adopt zero-dimensional calculation models, and this zero-dimensional calculation model cannot fully reflect the diversity and details of complex aeroengines. However, the present application adopts different physical field characterization dimensions for engine components of different dimensions, which can penetrate into the internal structure and flow process of each component and consider more spatial variables and time changes. Therefore, compared with the traditional zero-dimensional calculation model, the multi-dimensional calculation method of the present application can provide higher-precision performance evaluation and greatly improve the accuracy of calculating the performance parameters of the aeroengine.

[0084] In an exemplary embodiment, the model type includes the dimension of the model and the function of the model. On this basis, as Figure 3 shown, the above-mentioned "performing corresponding-dimensional calculation processing on each engine component according to the throttle lever position and the model type to obtain the input parameters of each component model" in the above embodiment includes steps 301 to 303. Among them:

[0085] Step 301, determining the vector to be solved of the common working equation set of the zero-dimensional calculation model according to the throttle lever position.

[0086] Among them, the zero-dimensional calculation model does not consider the local detailed flow or thermodynamic characteristics, but only needs to consider the global parameters, such as pressure, temperature, flow rate, etc.

[0087] In the embodiment of the present application, based on the obtained throttle lever position, the computer device needs to determine the vector to be solved of the common working equations of the zero-dimensional calculation model.

[0088] In some embodiments, according to the working state of the engine and the design requirements of each engine component, the computer device determines the vector to be solved of the common working equations required by the zero-dimensional model. These vectors to be solved of the common working equations include, but are not limited to, the inlet conditions of the air flow (such as pressure, temperature, flow velocity, etc.), the input conditions during the combustion process (such as fuel flow rate, air flow rate, etc.), and the pressure and velocity of the gas at the nozzle outlet, etc.

[0089] Step 302, determine the calculation order of multiple engine components according to the function of the model.

[0090] In the embodiment of the present application, the computer device needs to obtain the functions of the models of each component of the aeroengine. The functions of the models include the physical positions and mutual relationships of each engine component in the engine. For example, the relative positions of components such as the fan, compressor, turbine, combustion chamber, etc. and the flow direction of the air flow, etc.

[0091] Since there is a certain coupling relationship between different components and a certain order usually needs to be followed for calculation, the computer device needs to determine the calculation order of each engine component according to the obtained functions of the models. The calculation order is usually based on the mutual influence and energy transfer between each engine component. For example, the calculation result of the fan will affect the calculation of the compressor, and the calculation result of the compressor will in turn affect the working conditions of the combustion chamber and the turbine. According to these relationships, the calculation order can be gradually advanced from front to back along the air flow path. Exemplarily, the calculation order can be the inlet duct, fan, compressor, combustion chamber, turbine, nozzle.

[0092] Step 303, according to the calculation order and the dimension of the model, sequentially determine the target dimension calculation models corresponding to each engine component, and use the target dimension calculation models corresponding to each engine component to determine the input parameters of each component model; wherein, the target dimension calculation model is a zero-dimensional calculation model or a multi-dimensional calculation model.

[0093] In the embodiment of the present application, according to the calculation order of the components and the dimension of the model, the computer device sequentially determines the target dimension calculation models required for each component. Among them, the selection of the target dimension calculation model is based on the complexity and physical characteristics of the component, and can be divided into two types: the zero-dimensional calculation model and the multi-dimensional calculation model:

[0094] (1) Zero-dimensional calculation model: The zero-dimensional model is usually used for simplified components, such as intake ducts and combustion chambers. For these engine components, the computer device uses the zero-dimensional calculation model to calculate the input parameters of these component models.

[0095] (2) Multi-dimensional calculation model: For complex components such as airflows and heat conduction (such as fans, compressors, turbines, etc.), the computer device selects a multi-dimensional calculation model, usually including two-dimensional or three-dimensional models. The multi-dimensional calculation model takes into account factors such as the flow inside the engine components, temperature distribution, and pressure changes.

[0096] After determining the target-dimensional calculation model, the computer device calculates each engine component one by one to obtain the aerodynamic performance parameters of each component. For example:

[0097] (1) Fan component: For the fan, a two-dimensional calculation model is usually adopted to calculate the distribution of airflows on the fan blades, pressure changes, rotational speed, etc. According to the calculation results, the aerodynamic performance parameters of the fan are obtained.

[0098] (2) Compressor component: For the compressor, a three-dimensional calculation model is used to simulate the changes in airflows and calculate parameters such as the flow field, temperature, and pressure of the gas inside the compressor, so as to determine the aerodynamic performance parameters of the compressor.

[0099] (3) Turbine component and nozzle component: The turbine component usually requires three-dimensional calculations to analyze the complex distribution of airflows and its impact on the turbine blades, and obtain aerodynamic performance parameters such as the temperature, rotational speed, and load of the turbine.

[0100] (3) Combustion chamber: The combustion chamber and nozzle components usually use the zero-dimensional calculation model to focus on analyzing combustion efficiency, gas flow rate, temperature, and pressure, etc.

[0101] The calculation results of each engine component will be fed back to the next calculation step to determine the aerodynamic performance parameters of the subsequent components.

[0102] In the above embodiments, selecting an appropriate calculation model according to the dimension of the model can optimize the utilization of computing resources, avoid unnecessary computing burdens, and reasonably balance computing accuracy and efficiency according to the complexity of the components. Therefore, the computing accuracy and computing efficiency can be effectively improved, and the conversion between high-dimensional calculation models and zero-dimensional calculation models enables the calculation of each component to be processed most appropriately according to its specific requirements.

[0103] In an exemplary embodiment, "determining the input parameters of each component model using the target-dimensional calculation model corresponding to each engine component" in the above embodiments includes:

[0104] In Case 1, when the target-dimensional calculation model corresponding to the engine component is a zero-dimensional calculation model, the input parameters of the component model are determined according to the input parameters and output parameters of the zero-dimensional calculation model.

[0105] In Case 2, when the target-dimensional calculation model corresponding to the engine component is a multi-dimensional calculation model, the multi-dimensional calculation model is called, and the input parameters of the component model are determined based on the input parameters and output parameters of the multi-dimensional calculation model.

[0106] In the embodiment of the present application, when the target-dimensional calculation model corresponding to the engine component is a zero-dimensional calculation model, the computer device first inputs the vector of the co-working equations to be solved into the zero-dimensional calculation model. After the zero-dimensional calculation model completes the calculation, a set of output parameters will be generated, such as compression ratio, air flow rate, temperature change, etc. These output parameters will be passed to the next engine component as the input parameters for the calculation of this component, and subsequent calculations will continue.

[0107] If the target-dimensional calculation model corresponding to the engine component is a multi-dimensional calculation model (such as a two-dimensional or three-dimensional model), then the corresponding multi-dimensional calculation model needs to be called first. After calling this model, the computer device uses the output parameters of the upstream engine component as the input parameters of the current component and performs calculations based on these input parameters. After the output parameters are generated by the multi-dimensional calculation model, they are passed to the downstream component as input parameters.

[0108] In the above embodiments, through the calculation method combining zero-dimensional and multi-dimensional models, while maintaining high accuracy, the calculation time required for convergence can be significantly reduced, improving the calculation efficiency and accuracy. In addition, by selecting an appropriate calculation model, the convergence process of the aerodynamic performance parameters can be made faster and more stable. In the zero-dimensional model, due to the simplified calculation process, the aerodynamic performance parameters can usually reach convergence in a relatively short time. In the multi-dimensional model, although the calculation complexity is high, its accuracy is higher, and it can quickly determine the aerodynamic performance parameters of each component under accurate conditions.

[0109] In an exemplary embodiment, as Figure 4 shown, in the above embodiments, "calling the multi-dimensional calculation model" includes steps 401 to 402. Among them:

[0110] Step 401, obtain the zero-dimensional - multi-dimensional interaction instruction set.

[0111] In the embodiments of the present application, a computer device obtains a zero-dimensional to multi-dimensional interaction instruction set. The multi-dimensional interaction instruction set contains the interaction rules between different-dimensional calculation models, defines how to switch from a zero-dimensional model to a multi-dimensional model, and how to transfer and feedback calculation results. The multi-dimensional interaction instruction set acts as a bridge during the calculation process, ensuring data consistency and coordination between different-dimensional calculation models.

[0112] Step 402, call a multi-dimensional calculation model based on the zero-dimensional to multi-dimensional interaction instruction set.

[0113] In the embodiments of the present application, the computer device selects an appropriate multi-dimensional calculation model (zero-dimensional calculation model or multi-dimensional calculation model) according to the rules in the zero-dimensional to multi-dimensional interaction instruction set, and transfers relevant input parameters to the corresponding multi-dimensional calculation model.

[0114] The method further includes:

[0115] Write the input parameters of the component model determined based on the multi-dimensional calculation model into the zero-dimensional to multi-dimensional interaction instruction set.

[0116] In the embodiments of the present application, after obtaining the aerodynamic performance parameters of the multi-dimensional calculation model, write the input parameters of the component model determined based on the multi-dimensional calculation model into the zero-dimensional to multi-dimensional interaction instruction set. This step ensures that the aerodynamic performance parameters can be correctly transferred and stored, and enables subsequent calculations to be based on the updated aerodynamic performance parameters.

[0117] In the above embodiments, by writing the output result into the interaction instruction set, the computer device can ensure seamless connection between different-dimensional calculation models and guarantee the consistency and integrity of the calculation results of each engine component. In addition, by writing and transferring the aerodynamic performance parameters in the interaction instruction set, calculation errors caused by data loss or incorrect transfer are avoided. This helps to improve the stability and convergence of the entire calculation process.

[0118] In an exemplary embodiment, as Figure 5 shown, in the above embodiments, "determine the performance parameters of an aero-engine based on the throttle lever position and the input parameters of each component model" includes steps 501 to 502. Among them:

[0119] Step 501, determine the parameter convergence situation according to the input parameters of multiple component models.

[0120] In the embodiments of the present application, determine the parameter convergence situation according to the input parameters of multiple component models.

[0121] In some embodiments, for the multi-dimensional physical field parameters determined based on the multi-dimensional calculation model, the multi-dimensional physical field parameters may be the multi-dimensional physical field parameters of one surface of an engine component. To convert them into a form convenient for subsequent analysis, it is necessary to perform dimensionality reduction on these aerodynamic performance parameters and convert the multi-dimensional physical field parameters of one surface into a 1×n matrix, where n is the parameter information, which may be pressure, temperature, flow rate, rotation speed, etc.

[0122] The conversion process may be as follows: for each parameter information, calculate the average value of this parameter information within this surface, thereby obtaining a 1×n matrix.

[0123] Next, the computer device will compare the difference between the 1×n matrix determined in the previous round of calculation and the 1×n matrix determined in the current round of calculation. To determine whether the parameters have converged, the computer device will calculate the residuals between the elements at the corresponding positions in these two matrices. If the magnitude of the residual is less than a preset threshold (such as 10 -3 ), it indicates that the input parameters of the component model have converged. At this time, the calculation can be stopped, and the multi-dimensional physical field parameters are regarded as stable. If the convergence condition is not met, continue the calculation and adjust the vector to be solved in the co-working equation set until the convergence criterion is satisfied.

[0124] Step 502, in the case where the input parameters of multiple component models have converged, determine the performance parameters of the aeroengine based on the throttle lever position.

[0125] In the embodiments of the present application, in the case where the input parameters of multiple component models have converged, the computer device may further calculate and determine the performance parameters of the aeroengine based on the stabilized aerodynamic performance parameters and other relevant throttle lever positions.

[0126] Among them, common performance parameters include:

[0127] (1) Thrust: By comprehensively considering the working states of each component, calculate the total thrust generated by the engine, which is usually closely related to air flow, temperature, pressure, and combustion efficiency.

[0128] (2) Fuel efficiency: Evaluate the energy efficiency level of the engine by calculating the ratio between the input energy and the output energy of the engine, usually evaluated by data such as specific fuel consumption and flight time.

[0129] (3) Exhaust gas temperature: Calculate the exhaust gas temperature based on the aerodynamic performance parameters of the combustion chamber and the state of the turbine section, which is crucial for judging the thermal efficiency and combustion efficiency of the engine.

[0130] (4) Emission level: Estimate the concentration of harmful gases (such as nitrogen oxides, hydrocarbons, etc.) in the exhaust gas according to the combustion state in the combustion chamber and the working conditions of the turbine.

[0131] (5) Engine life prediction: Based on the input parameters of the component models, the service life and maintenance cycle of the engine can also be deduced.

[0132] In the above embodiments, by analyzing the convergence of the input parameters of multiple component models, it can be ensured that the calculation results of all components tend to be stable, and all aerodynamic performance parameters are within the expected range. This convergence judgment mechanism can effectively filter out possible calculation errors and inconsistent values, making the aerodynamic performance parameters of each component more reliable and consistent. Only when the aerodynamic performance parameters of each component converge will they be further used to deduce the performance parameters of the engine, ensuring the accuracy of the entire calculation process.

[0133] In an exemplary embodiment, as Figure 6 shown, the above method further includes:

[0134] Step 601, when the input parameters of multiple component models do not converge, update the initial guess values of the input parameters of the component models until the input parameters of multiple component models converge.

[0135] In the embodiments of the present application, when the input parameters of multiple component models do not converge, the computer device will recognize that there are still large changes in the aerodynamic performance parameters of each component, and the convergence standard is not met. In this case, the computer device will adjust the vector to be solved in the current co-working equations until the input parameters of multiple component models converge. For example, the vector to be solved in the co-working equations can be adjusted, that is, based on the previous round of calculation results, the vector to be solved in the co-working equations of each engine component needs to be modified. For example, parameters such as the gas flow temperature of the turbine and the pressure ratio of the compressor may need to be reset to better match the actual working conditions.

[0136] After updating the throttle lever position, the computer will re-perform a round of calculations of aerodynamic performance parameters. This calculation will be based on the newly adjusted conditions and continue to perform convergence determination. The computer device will update and optimize the input parameters of each component model through continuous iteration until all aerodynamic performance parameters are stable.

[0137] Step 602, determine the performance parameters of the aeroengine based on the updated input parameters of the component models.

[0138] In the embodiments of the present application, after the input parameters of multiple component models converge, that is, the change in the aerodynamic performance parameters of each component is less than a predetermined threshold, the computer device can finally determine the performance parameters of the aeroengine based on the updated input parameters of the component models.

[0139] In the above embodiments, when the aerodynamic performance parameters do not converge, by updating the initial guess values of the input parameters of the component models, the computer device can ensure that the aerodynamic performance parameters of each component gradually converge and finally obtain stable results. These stable aerodynamic performance parameters provide a reliable basis for calculating the comprehensive performance parameters of the aeroengine, thereby enabling accurate assessment of the overall performance of the engine.

[0140] Some embodiments of the present application provide a cross-dimensional calculation method for aeroengines, which may include the following steps:

[0141] Step 1, obtain the throttle lever position of the aeroengine and the component model types of each engine component in the aeroengine; the model type includes the dimension of the model and the function of the model.

[0142] Step 2, determine the vector to be solved for the common working equations of the zero-dimensional calculation model according to the throttle lever position.

[0143] Step 3, determine the calculation order of multiple engine components according to the function of the model.

[0144] Step 4, sequentially determine the target dimension calculation models corresponding to each engine component according to the calculation order and the dimension of the model.

[0145] Step 5, use the target dimension calculation models corresponding to each engine component to determine the input parameters of each component model; wherein, the target dimension calculation model is a zero-dimensional calculation model or a multi-dimensional calculation model.

[0146] In some embodiments, when the target dimension calculation model corresponding to the engine component is a zero-dimensional calculation model, determine the input parameters of the component model according to the input parameters and output parameters of the zero-dimensional calculation model.

[0147] In some embodiments, when the target dimension calculation model corresponding to the engine component is a multi-dimensional calculation model, obtain a zero-dimensional - multi-dimensional interaction instruction set, call the multi-dimensional calculation model based on the zero-dimensional - multi-dimensional interaction instruction set, and determine the input parameters of the component model based on the input parameters and output parameters of the multi-dimensional calculation model.

[0148] Step 6, determine the parameter convergence situation according to the input parameters of multiple component models.

[0149] In some embodiments, when the input parameters of multiple component models converge, determine the performance parameters of the aeroengine based on the throttle lever position.

[0150] In some embodiments, when the input parameters of multiple component models do not converge, update the initial guess values of the input parameters of the component models until the input parameters of multiple component models converge; determine the performance parameters of the aeroengine based on the updated input parameters of the component models.

[0151] It should be understood that although the steps in the flowcharts involved in the above embodiments are shown in sequence according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise clearly stated in this article, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. Moreover, at least a part of the steps in the flowcharts involved in the above embodiments may include multiple steps or multiple stages. These steps or stages are not necessarily executed 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 executed alternately or in turn with at least a part of other steps or steps or stages in other steps.

[0152] Based on the same inventive concept, an embodiment of the present application further provides an aero-engine cross-dimensional calculation device for implementing the above-mentioned aero-engine cross-dimensional calculation method. The solution provided by this device to solve the problem is similar to the solution described in the above method. Therefore, the specific limitations in one or more embodiments of the aero-engine cross-dimensional calculation device provided below can refer to the limitations on the aero-engine cross-dimensional calculation method in the above text, and will not be repeated here.

[0153] In an exemplary embodiment, as Figure 7 shown, an aero-engine cross-dimensional calculation device is provided, including: an acquisition module 701, a calculation module 702, and a determination module 703, where:

[0154] The acquisition module 701 is configured to acquire the throttle lever position of the aero-engine and the component model types of each engine component in the aero-engine;

[0155] The calculation module 702 is configured to perform corresponding-dimensional calculation processing on each engine component in sequence according to the throttle lever position and the component model type to obtain the input parameters of each component model; wherein, the physical field characterization dimensions adopted by different-dimensional models of engine components are different;

[0156] The determination module 703 is configured to determine the performance parameters of the aero-engine based on the throttle lever position and the input parameters of each component model.

[0157] In an exemplary embodiment, the component model type includes the dimensions of the model and the functions of the model. The above-mentioned calculation module 702 is specifically configured to determine the vector to be solved of the simultaneous working equations of the zero-dimensional calculation model according to the throttle lever position; determine the calculation sequence of multiple engine components according to the functions of the model; according to the calculation sequence and the dimensions of the model, sequentially determine the target dimension calculation models corresponding to each engine component, and use the target dimension calculation models corresponding to each engine component to determine the input parameters of each component model; wherein, the target dimension calculation model is a zero-dimensional calculation model or a multi-dimensional calculation model.

[0158] In an exemplary embodiment, the above-mentioned calculation module 702 is specifically configured to, when the target dimension calculation model corresponding to the engine component is a zero-dimensional calculation model, determine the input parameters of the component model according to the input parameters and output parameters of the zero-dimensional calculation model; when the target dimension calculation model corresponding to the engine component is a multi-dimensional calculation model, call the multi-dimensional calculation model, and determine the input parameters of the component model based on the input parameters and output parameters of the multi-dimensional calculation model.

[0159] In an exemplary embodiment, the above-mentioned calculation module 702 is specifically configured to obtain a zero-dimensional - multi-dimensional interaction instruction set; call the multi-dimensional calculation model based on the zero-dimensional - multi-dimensional interaction instruction set; write the input parameters of the component model determined based on the multi-dimensional calculation model into the zero-dimensional - multi-dimensional interaction instruction set.

[0160] In an exemplary embodiment, the above-mentioned determination module 703 is specifically configured to determine the parameter convergence situation according to the input parameters of multiple component models; when the input parameters of multiple component models converge, determine the performance parameters of the aeroengine based on the throttle lever position.

[0161] In an exemplary embodiment, the above-mentioned determination module 703 is specifically configured to, when the input parameters of multiple component models do not converge, update the initial guess values of the input parameters of the component model until the input parameters of multiple component models converge; determine the performance parameters of the aeroengine based on the updated input parameters of the component model.

[0162] Each module in the above-mentioned aeroengine cross-dimension calculation device can be implemented in whole or in part by software, hardware, and their combination. The above-mentioned modules can be embedded in the processor of the computer device in hardware form or be independent of it, or can be stored in the memory of the computer device in software form, so that the processor can call and execute the operations corresponding to the above-mentioned modules.

[0163] In an exemplary embodiment, a computer device is provided, including a memory and a processor. A computer program is stored in the memory, and when the processor executes the computer program, the following steps are implemented:

[0164] Obtain the throttle lever position of the aero-engine and the component model types of each engine component in the aero-engine;

[0165] According to the throttle lever position and the component model types, perform calculation processing on each engine component in corresponding dimensions in sequence to obtain the input parameters of each component model; among them, the physical field characterization dimensions adopted by different dimensional models of engine components are different;

[0166] Determine the performance parameters of the aero-engine based on the throttle lever position and the input parameters of each component model.

[0167] In one embodiment, the model type includes the dimension of the model and the function of the model. When the processor executes the computer program, the following steps are also implemented:

[0168] Determine the vector to be solved of the common working equations of the zero-dimensional calculation model according to the throttle lever position;

[0169] Determine the calculation sequence of multiple engine components according to the function of the model;

[0170] According to the calculation sequence and the dimension of the model, determine the target dimension calculation model corresponding to each engine component in sequence, and use the target dimension calculation model corresponding to each engine component to determine the input parameters of each component model; among them, the target dimension calculation model is a zero-dimensional calculation model or a multi-dimensional calculation model.

[0171] In one embodiment, when the processor executes the computer program, the following steps are also implemented:

[0172] When the target dimension calculation model corresponding to the engine component is a zero-dimensional calculation model, determine the input parameters of the component model according to the input parameters and output parameters of the zero-dimensional calculation model;

[0173] When the target dimension calculation model corresponding to the engine component is a multi-dimensional calculation model, call the multi-dimensional calculation model, and determine the input parameters of the component model based on the input parameters and output parameters of the multi-dimensional calculation model.

[0174] In one embodiment, when the processor executes the computer program, the following steps are also implemented:

[0175] Obtain the zero-dimensional - multi-dimensional interaction instruction set;

[0176] Call the multi-dimensional calculation model based on the zero-dimensional - multi-dimensional interaction instruction set;

[0177] Write the input parameters of the component model determined based on the multi-dimensional calculation model into the zero-dimensional - multi-dimensional interaction instruction set.

[0178] In one embodiment, when the processor executes the computer program, the following steps are also implemented:

[0179] Determine the parameter convergence situation according to the input parameters of multiple component models;

[0180] When the input parameters of multiple component models converge, determine the performance parameters of the aeroengine based on the throttle lever position.

[0181] In one embodiment, when the processor executes the computer program, the following steps are further implemented:

[0182] When the input parameters of multiple component models do not converge, update the initial guess values of the input parameters of the component models until the input parameters of multiple component models converge;

[0183] Determine the performance parameters of the aeroengine based on the updated input parameters of the component models.

[0184] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the following steps are implemented:

[0185] Obtain the throttle lever position of the aeroengine and the component model types of each engine component in the aeroengine;

[0186] According to the throttle lever position and the component model types, perform calculation processing on each engine component in corresponding dimensions in sequence to obtain the input parameters of each component model; wherein, the physical field characterization dimensions adopted by different dimensional models of the engine components are different;

[0187] Determine the performance parameters of the aeroengine based on the throttle lever position and the input parameters of each component model.

[0188] In one embodiment, the model type includes the dimension of the model and the function of the model. When the computer program is executed by a processor, the following steps are further implemented:

[0189] Determine the vector to be solved of the common working equations of the zero-dimensional calculation model according to the throttle lever position;

[0190] Determine the calculation order of multiple engine components according to the function of the model;

[0191] According to the calculation order and the dimension of the model, determine the target dimension calculation models corresponding to each engine component in sequence, and use the target dimension calculation models corresponding to each engine component to determine the input parameters of each component model; wherein, the target dimension calculation model is a zero-dimensional calculation model or a multi-dimensional calculation model.

[0192] In one embodiment, when the computer program is executed by a processor, the following steps are further implemented:

[0193] When the target dimension calculation model corresponding to the engine component is a zero-dimensional calculation model, determine the input parameters of the component model according to the input parameters and output parameters of the zero-dimensional calculation model;

[0194] When the target dimension calculation model corresponding to the engine component is a multi-dimensional calculation model, call the multi-dimensional calculation model and determine the input parameters of the component model based on the input parameters and output parameters of the multi-dimensional calculation model.

[0195] In one embodiment, when the computer program is executed by the processor, the following steps are further implemented:

[0196] Obtain the zero-dimensional-multi-dimensional interaction instruction set;

[0197] Call the multi-dimensional calculation model based on the zero-dimensional-multi-dimensional interaction instruction set;

[0198] Write the input parameters of the component model determined based on the multi-dimensional calculation model into the zero-dimensional-multi-dimensional interaction instruction set.

[0199] In one embodiment, when the computer program is executed by the processor, the following steps are further implemented:

[0200] Determine the parameter convergence situation according to the input parameters of multiple component models;

[0201] When the input parameters of multiple component models converge, determine the performance parameters of the aeroengine based on the throttle lever position.

[0202] In one embodiment, when the computer program is executed by the processor, the following steps are further implemented:

[0203] When the input parameters of multiple component models do not converge, update the initial guess values of the input parameters of the component models until the input parameters of multiple component models converge;

[0204] Determine the performance parameters of the aeroengine based on the updated input parameters of the component models.

[0205] In one embodiment, a computer program product is provided, including a computer program, and when the computer program is executed by the processor, the following steps are implemented:

[0206] Obtain the throttle lever position of the aeroengine and the component model types of each engine component in the aeroengine;

[0207] According to the throttle lever position and the component model types, perform corresponding dimension calculation processing on each engine component in turn to obtain the input parameters of each component model; wherein, the physical field characterization dimensions adopted by different dimension models of the engine components are different;

[0208] Determine the performance parameters of an aeroengine based on the throttle lever position and the input parameters of each component model.

[0209] In one embodiment, the model type includes the dimension of the model and the function of the model. When the computer program is executed by the processor, the following steps are further implemented:

[0210] Determine the vector to be solved in the common working equation set of the zero-dimensional calculation model according to the throttle lever position;

[0211] Determine the calculation order of multiple engine components according to the function of the model;

[0212] According to the calculation order and the dimension of the model, sequentially determine the target dimension calculation models corresponding to each engine component, and use the target dimension calculation models corresponding to each engine component to determine the input parameters of each component model; wherein, the target dimension calculation model is a zero-dimensional calculation model or a multi-dimensional calculation model.

[0213] In one embodiment, when the computer program is executed by the processor, the following steps are further implemented:

[0214] When the target dimension calculation model corresponding to the engine component is a zero-dimensional calculation model, determine the input parameters of the component model according to the input parameters and output parameters of the zero-dimensional calculation model;

[0215] When the target dimension calculation model corresponding to the engine component is a multi-dimensional calculation model, call the multi-dimensional calculation model, and determine the input parameters of the component model based on the input parameters and output parameters of the multi-dimensional calculation model.

[0216] In one embodiment, when the computer program is executed by the processor, the following steps are further implemented:

[0217] Obtain a zero-dimensional - multi-dimensional interaction instruction set;

[0218] Call the multi-dimensional calculation model based on the zero-dimensional - multi-dimensional interaction instruction set;

[0219] Write the input parameters of the component model determined based on the multi-dimensional calculation model into the zero-dimensional - multi-dimensional interaction instruction set.

[0220] In one embodiment, when the computer program is executed by the processor, the following steps are further implemented:

[0221] Determine the parameter convergence situation according to the input parameters of multiple component models;

[0222] When the input parameters of multiple component models converge, determine the performance parameters of the aeroengine based on the throttle lever position.

[0223] In one embodiment, when the computer program is executed by the processor, the following steps are further implemented:

[0224] In the case where the input parameters of multiple component models do not converge, update the initial guess values of the input parameters of the component models until the input parameters of the multiple component models converge;

[0225] Determine the performance parameters of the aeroengine based on the updated input parameters of the component models.

[0226] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above methods. Among them, any reference to a memory, database, or other medium used in the embodiments provided in this application can include at least one of non-volatile memory 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), magnetoresistive 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 be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM), etc. The databases involved in the embodiments provided in this application can include at least one of relational databases and non-relational databases. Non-relational databases can include distributed databases based on blockchain, etc., without limitation. The processors involved in the embodiments provided in this application can be general-purpose processors, central processors, graphics processors, digital signal processors, programmable logic devices, data processing logics based on quantum computing, artificial intelligence (AI) processors, etc., without limitation.

[0227] The technical features of the above embodiments can be combined arbitrarily. For the sake of concise description, 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, it should be considered as the scope recorded in this application.

[0228] The above-described embodiments merely represent several implementation manners of this application. The description is relatively specific and detailed, but it should not be construed as a limitation on the patent scope of this application. It should be noted that for those of ordinary skill in the art, without departing from the concept of this application, several modifications and improvements can still be made, and these all belong to the protection scope of this application. Therefore, the protection scope of this application shall be subject to the appended claims.

Claims

1. A cross-dimensional calculation method for an aircraft engine, characterized in that: The method comprises: Acquire a throttle lever position of an aircraft engine and a component model type of each engine component in the aircraft engine; According to the throttle lever position and the component model type, the corresponding dimension calculation processing is performed on each of the engine components in turn to obtain input parameters of each component model; wherein different dimensional models of the engine components adopt different physical field representation dimensions; A performance parameter of the aircraft engine is determined based on the throttle lever position and input parameters of each of the component models.

2. The method according to claim 1, characterized in that The component model type includes the dimension of the model and the function of the model; the corresponding dimension calculation processing is performed on each of the engine components in turn according to the throttle lever position and the component model type to obtain the input parameters of each component model, including: Determine the vector to be solved of the common working equation group of the zero-dimensional calculation model according to the throttle lever position; determining a calculation order of a plurality of the engine components according to the functions of the model; According to the calculation order and the dimension of the model, the target dimension calculation model corresponding to each of the engine components is determined in turn, and the input parameters of each component model are determined using the target dimension calculation model corresponding to each of the engine components; wherein the target dimension calculation model is the zero-dimensional calculation model or the multi-dimensional calculation model.

3. The method according to claim 2, characterized in that The step of determining the input parameters of each component model by using the target dimension calculation model corresponding to each engine component includes: In a case where the target dimensional calculation model corresponding to the engine component is the zero-dimensional calculation model, determining the input parameters of the component model according to the input parameters and output parameters of the zero-dimensional calculation model; In the case where the target dimensional calculation model corresponding to the engine component is the multidimensional calculation model, the multidimensional calculation model is called, and the input parameters of the component model are determined based on the input parameters and output parameters of the multidimensional calculation model.

4. The method according to claim 3, characterized in that: Calling the multidimensional computing model includes: Obtain zero-dimensional-multi-dimensional interaction instruction set; Calling the multi-dimensional computing model based on the zero-dimensional-multi-dimensional interactive instruction set; The method further comprises: The input parameters of the component model determined based on the multi-dimensional computing model are written into the zero-dimensional-multi-dimensional interactive instruction set.

5. The method according to claim 1, characterized in that The determining of the performance parameters of the aircraft engine based on the throttle lever position and the input parameters of each of the component models comprises: Determining parameter convergence according to a plurality of input parameters of the component models; When the input parameters of the plurality of component models converge, the performance parameters of the aircraft engine are determined based on the throttle lever position.

6. The method according to claim 5, characterized in that The method further comprises: When the input parameters of the plurality of component models do not converge, updating the throttle lever position until the input parameters of the plurality of component models converge; Performance parameters of the aircraft engine are determined based on the input parameters of the updated component model.

7. An aircraft engine cross-dimensional computing device, characterized in that: The device comprises: An acquisition module, used to acquire a throttle lever position of an aircraft engine and a component model type of each engine component in the aircraft engine; A calculation module, used for performing calculation processing of corresponding dimensions on each of the engine components in turn according to the throttle lever position and the component model type, to obtain input parameters of each component model; wherein different dimensional models of the engine components adopt different physical field representation dimensions; A determination module is used to determine the performance parameters of the aircraft engine based on the throttle lever position and the input parameters of each of the component models.

8. A computer device comprising a memory and a processor, wherein the memory stores a computer program, wherein: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 6 are implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

10. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

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