Aero-engine modeling method and device, computer equipment, readable storage medium and program product

Abstract

The invention relates to an aero-engine modeling method and device, computer equipment, a computer readable storage medium and a computer program product. The method comprises the following steps: acquiring a basic model structure of the aero-engine and a first physical property parameter of liquid hydrogen, and determining a second physical property parameter of air according to the basic model structure; based on the first physical property parameter and the second physical property parameter, cooling of the liquid hydrogen to the aero-engine is simulated, and a first outlet physical property parameter corresponding to the liquid hydrogen in the heat exchanger and a second outlet physical property parameter corresponding to air are obtained; hydrogen fuel combustion is simulated based on the basic model structure, the first outlet physical property parameters, the second outlet physical property parameters and a physical property parameter correction assembly, and target physical property parameters are determined; and determining a simulation result of the aero-engine according to the target physical property parameters. By adopting the method, the hydrogen fuel engine can be subjected to analogue simulation, and the accuracy of a simulation result is ensured.

Description

Technical Field

[0001] The present application relates to the technical field of aero-engines, and particularly to a method, device, computer equipment, computer-readable storage medium, and computer program product for modeling an aero-engine. Background Art

[0002] With the development of aero-engine technology, hydrogen fuel aero-engines have emerged. However, directly conducting physical experiments on hydrogen fuel engines faces high costs and high risks. Therefore, the research and development of hydrogen fuel aero-engines can be carried out through simulation experiments using a mathematical model.

[0003] In traditional technologies, based on the geometric data and performance parameters of a kerosene engine, including the dimensions and material properties of key components such as the combustion chamber, turbine, and compressor, the flow, mixing, and combustion processes of air and kerosene inside the engine are simulated to establish a basic model structure for predicting the thrust, efficiency, and emission characteristics of the kerosene engine.

[0004] However, in current traditional technologies, due to the different characteristics of hydrogen fuel and traditional aviation kerosene, there are significant differences in the structure between hydrogen fuel aero-engines and kerosene engines. Therefore, existing kerosene engine models cannot be directly used for the simulation of hydrogen fuel engines. Furthermore, there is an urgent need for a method that can simulate hydrogen fuel engines. Summary of the Invention

[0005] Based on this, in view of the above technical problems, it is necessary to provide a method, device, computer equipment, computer-readable storage medium, and computer program product for modeling an aero-engine.

[0006] In a first aspect, the present application provides a method for modeling an aero-engine, including:

[0007] Obtaining a basic model structure of an aero-engine and first physical property parameters of liquid hydrogen, and determining second physical property parameters of air according to the basic model structure;

[0008] Simulating the cooling of the aero-engine by the liquid hydrogen based on the first physical property parameters and the second physical property parameters to obtain first outlet physical property parameters corresponding to the liquid hydrogen and second outlet physical property parameters corresponding to the air in a heat exchanger;

[0009] Simulating hydrogen fuel combustion based on the basic model structure, the first outlet physical property parameters, the second outlet physical property parameters, and a physical property parameter correction component to determine target physical property parameters;

[0010] Determining a simulation result of the aero-engine according to the target physical property parameters.

[0011] In one embodiment, simulating the cooling of the aeroengine by the liquid hydrogen based on the first physical property parameter and the second physical property parameter to obtain the first outlet physical property parameter corresponding to the liquid hydrogen and the second outlet physical property parameter corresponding to the air in the heat exchanger, includes:

[0012] Obtain the third physical property parameter and the heat exchanger attribute parameter between the liquid hydrogen and the air;

[0013] Determine the target heat transfer coefficient according to the first physical property parameter, the second physical property parameter, the third physical property parameter and the heat exchanger attribute parameter;

[0014] Determine the first outlet physical property parameter corresponding to the liquid hydrogen and the second outlet physical property parameter corresponding to the air based on the target heat transfer coefficient.

[0015] In one embodiment, simulating the combustion of hydrogen fuel based on the basic model structure, the first outlet physical property parameter, the second outlet physical property parameter and the physical property parameter correction component to determine the target physical property parameter, includes:

[0016] Determine the fuel-air ratio according to the first outlet physical property parameter and the second outlet physical property parameter;

[0017] Determine the mass fraction of each component in the liquid hydrogen gas according to the fuel-air ratio;

[0018] Simulate the combustion of hydrogen fuel based on the mass fraction, the first outlet physical property parameter and the second outlet physical property parameter to obtain the target physical property parameter.

[0019] In one embodiment, when the type of the heat exchanger is a pre-cooling heat exchanger, determining the second physical property parameter of the air according to the basic model structure, includes:

[0020] Obtain the initial parameters;

[0021] Determine the second physical property parameter of the air flowing out of the intake duct structure according to the intake duct structure in the basic model structure and the initial parameters;

[0022] Simulating the cooling of the liquid hydrogen to the air flowing out of the intake duct structure based on the first physical property parameter and the second physical property parameter to obtain the first outlet physical property parameter corresponding to the liquid hydrogen and the second outlet physical property parameter corresponding to the air in the heat exchanger, includes:

[0023] Simulate the cooling of the liquid hydrogen to the air flowing out of the intake duct structure based on the first physical property parameter and the second physical property parameter to obtain the first outlet physical property parameter corresponding to the liquid hydrogen and the second outlet physical property parameter corresponding to the air.

[0024] In one embodiment, the simulation results include thrust and efficiency; determining the simulation results of the aero-engine according to the target physical property parameters includes:

[0025] Determining intermediate physical property parameters of the power turbine structure according to the target physical property parameters;

[0026] Determining the thrust and efficiency of the aero-engine based on the intermediate physical property parameters.

[0027] In one embodiment, after simulating the cooling of the aero-engine by the liquid hydrogen based on the first physical property parameter and the second physical property parameter to obtain the first outlet physical property parameter corresponding to the liquid hydrogen and the second outlet physical property parameter corresponding to the air in the heat exchanger, the method further includes:

[0028] During the simulation of the aero-engine, when the current structure calls the preset physical property parameters, according to the interface corresponding to the preset physical property parameters, transmitting the total temperature, total pressure and fuel-air ratio in the current structure to the physical property parameter correction component;

[0029] Determining the mass fractions of the components in the liquid hydrogen gas according to the physical property parameter correction component and the fuel-air ratio;

[0030] Calculating target physical property parameters based on the physical property parameter correction component, the mass fractions, the total temperature and the total pressure, and feeding back the target physical property parameters to the current structure.

[0031] In a second aspect, the present application further provides an aero-engine modeling device, including:

[0032] An acquisition module, configured to acquire the basic model structure of the aero-engine and the first physical property parameter of the liquid hydrogen, and determine the second physical property parameter of the air according to the basic model structure;

[0033] A first simulation module, configured to simulate the cooling of the aero-engine by the liquid hydrogen based on the first physical property parameter and the second physical property parameter to obtain the first outlet physical property parameter corresponding to the liquid hydrogen and the second outlet physical property parameter corresponding to the air in the heat exchanger;

[0034] A second simulation module, configured to simulate the combustion of hydrogen fuel based on the basic model structure, the first outlet physical property parameter, the second outlet physical property parameter and the physical property parameter correction component to determine the target physical property parameters;

[0035] A determination module, configured to determine the simulation results of the aero-engine according to the target physical property parameters.

[0036] In one embodiment, the first simulation module is specifically configured to obtain a third physical property parameter and a heat exchanger property parameter between the liquid hydrogen and the air;

[0037] Determine a target heat transfer coefficient according to the first physical property parameter, the second physical property parameter, the third physical property parameter, and the heat exchanger property parameter;

[0038] Based on the target heat transfer coefficient, determine a first outlet physical property parameter corresponding to the liquid hydrogen and a second outlet physical property parameter corresponding to the air.

[0039] In one embodiment, the second simulation module is specifically configured to determine an oil-gas ratio according to the first outlet physical property parameter and the second outlet physical property parameter;

[0040] Determine the mass fraction of each component in the liquid hydrogen fuel gas according to the oil-gas ratio;

[0041] Based on the mass fraction, the first outlet physical property parameter, and the second outlet physical property parameter, simulate the combustion of hydrogen fuel to obtain a target physical property parameter.

[0042] In one embodiment, when the type of the heat exchanger is a precooling heat exchanger, the acquisition module is specifically configured to acquire initial parameters;

[0043] According to the intake duct structure in the basic model structure and the initial parameters, determine a second physical property parameter corresponding to the air flowing out of the intake duct structure;

[0044] The first simulation module is specifically configured to simulate the cooling of the air flowing out of the intake duct structure by the liquid hydrogen based on the first physical property parameter and the second physical property parameter, and obtain a first outlet physical property parameter corresponding to the liquid hydrogen and a second outlet physical property parameter corresponding to the air in the heat exchanger.

[0045] In one embodiment, the simulation result includes thrust and efficiency; the determination module is specifically configured to determine an intermediate physical property parameter of the power turbine structure according to the target physical property parameter;

[0046] Based on the intermediate physical property parameter, determine the thrust and efficiency of the aeroengine.

[0047] In one embodiment, the device further includes:

[0048] A transmission module, configured to, during the simulation of the aeroengine, when a preset physical property parameter is called by the current structure, transfer the total temperature, total pressure, and oil-gas ratio in the current structure to the physical property parameter correction component according to the interface corresponding to the preset physical property parameter;

[0049] A first calculation module, configured to determine the mass fractions of the components in the liquid hydrogen fuel gas according to the physical property parameter correction component and the oil-gas ratio;

[0050] A second calculation module, configured to calculate target physical property parameters based on the physical property parameter correction component, the mass fractions, the total temperature, and the total pressure, and feed back the target physical property parameters to the current structure.

[0051] In a third aspect, the present application further provides a computer device, including a memory and a processor, where the memory stores a computer program, and when the processor executes the computer program, the following steps are implemented:

[0052] Obtain a basic model structure of an aeroengine and first physical property parameters of liquid hydrogen, and determine second physical property parameters of air according to the basic model structure;

[0053] Simulate the cooling of the aeroengine by the liquid hydrogen based on the first physical property parameters and the second physical property parameters to obtain first outlet physical property parameters corresponding to the liquid hydrogen and second outlet physical property parameters corresponding to the air in the heat exchanger;

[0054] Simulate the combustion of hydrogen fuel based on the basic model structure, the first outlet physical property parameters, the second outlet physical property parameters, and the physical property parameter correction component to determine target physical property parameters;

[0055] Determine the simulation result of the aeroengine according to the target physical property parameters.

[0056] 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:

[0057] Obtain a basic model structure of an aeroengine and first physical property parameters of liquid hydrogen, and determine second physical property parameters of air according to the basic model structure;

[0058] Simulate the cooling of the aeroengine by the liquid hydrogen based on the first physical property parameters and the second physical property parameters to obtain first outlet physical property parameters corresponding to the liquid hydrogen and second outlet physical property parameters corresponding to the air in the heat exchanger;

[0059] Simulate the combustion of hydrogen fuel based on the basic model structure, the first outlet physical property parameters, the second outlet physical property parameters, and the physical property parameter correction component to determine target physical property parameters;

[0060] Determine the simulation result of the aeroengine according to the target physical property parameters.

[0061] In a fifth aspect, the present application further provides a computer program product, including a computer program which, when executed by a processor, implements the following steps:

[0062] Obtain the basic model structure of an aeroengine and the first physical property parameters of liquid hydrogen, and determine the second physical property parameters of air according to the basic model structure;

[0063] Based on the first physical property parameters and the second physical property parameters, simulate the cooling of the aeroengine by the liquid hydrogen to obtain the first outlet physical property parameters corresponding to the liquid hydrogen and the second outlet physical property parameters corresponding to the air in the heat exchanger;

[0064] Based on the basic model structure, the first outlet physical property parameters, the second outlet physical property parameters and a physical property parameter correction component, simulate the combustion of hydrogen fuel to determine the target physical property parameters;

[0065] Determine the simulation result of the aeroengine according to the target physical property parameters.

[0066] The above-mentioned aeroengine modeling method, device, computer device, computer-readable storage medium and computer program product obtain the initial model of a hydrogen fuel engine and the first physical property parameters of liquid hydrogen, and determine the second physical property parameters of air according to the initial model and the initial parameters; based on a heat exchange model, the first physical property parameters and the second physical property parameters, simulate the cooling of the hydrogen fuel engine by the liquid hydrogen to obtain the first outlet physical property parameters corresponding to the liquid hydrogen and the second outlet physical property parameters corresponding to the air in the heat exchanger; based on the initial model, the first outlet physical property parameters, the second outlet physical property parameters and a physical property parameter correction component, determine the target physical property parameters; determine the simulation result of the hydrogen fuel engine according to the target physical property parameters. By using this method, the cooling of the hydrogen fuel engine by the liquid hydrogen is simulated through a heat exchange model, and the first outlet physical property parameters corresponding to the liquid hydrogen and the second outlet physical property parameters corresponding to the air are calculated, realizing the modeling of the heat exchanger in the hydrogen fuel engine. Combining with a physical property parameter correction component, the combustion characteristics and physical changes of hydrogen fuel can be accurately calculated, realizing the simulation of the hydrogen fuel engine and ensuring the accuracy of the simulation result. Description of the Drawings

[0067] 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 to be used 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.

[0068] Figure 1 It is a schematic flowchart of the aeroengine modeling method in an embodiment;

[0069] Figure 2 Schematic diagram of the component structure of a twin-shaft turboprop engine in one embodiment;

[0070] Figure 3 Schematic diagram of the process of modeling a heat exchanger in one embodiment;

[0071] Figure 4 Schematic diagram of a heat exchanger model in one embodiment;

[0072] Figure 5 Schematic diagram of the process of modeling and simulating hydrogen fuel combustion in one embodiment;

[0073] Figure 6 Schematic diagram of the process of obtaining the second physical property parameters in the pre-cooled heat exchanger scenario in one embodiment;

[0074] Figure 7 Schematic diagram of a pre-cooled heat exchanger in one embodiment;

[0075] Figure 8 Schematic diagram of a tailpipe heat exchanger in one embodiment;

[0076] Figure 9 Schematic diagram of a turbine cooler heat exchanger in one embodiment;

[0077] Figure 10 Schematic diagram of the process of calculating thrust and efficiency steps in one embodiment;

[0078] Figure 11 Schematic diagram of the process of obtaining the target physical property parameters corresponding to hydrogen fuel combustion according to the interface in one embodiment;

[0079] Figure 12 Block diagram of the structure of an aeroengine modeling device in one embodiment;

[0080] Figure 13 Internal structure diagram of a computer device in one embodiment. Detailed implementation manners

[0081] 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.

[0082] In one embodiment, as Figure 1As shown, a method for modeling an aeroengine is provided. In this embodiment, an example is given where this method is applied to a terminal. It can be understood that this method can also be applied to a server, or to a system including a terminal and a server, and is implemented through the interaction between the terminal and the server. In this embodiment, the method includes the following steps:

[0083] Step 102: Obtain the basic model structure of the aeroengine and the first physical property parameters of liquid hydrogen, and determine the second physical property parameters of air according to the basic model structure.

[0084] In the embodiment of the present application, the basic model structure can be the same as the model structure of a traditional kerosene turboprop engine. Taking a twin-spool turboprop engine as an example of a traditional kerosene turboprop engine, as Figure 2 shown, the component structure of a twin-spool turboprop engine includes a propeller, an air intake, a compressor, a combustion chamber, a gas turbine, a power turbine, a tail nozzle, etc. Among them, the gas turbine drives the compressor through a gas turbine shaft, and the power turbine drives the propeller through a power turbine shaft to provide thrust. Here, taking the component structure of a twin-spool turboprop engine as an example to model the basic model structure, this basic model structure can be constructed in advance on the Simulink platform based on the component-level modeling method, and each component is combined to form a complete engine system according to the common working conditions of each component in the twin-spool turboprop engine. Finally, under the common working conditions of each component of the engine system, there is a common working equation, and then the terminal uses a numerical solution method to solve the common working equation to model and simulate the working state of the engine.

[0085] Optionally, in the basic model structure, the gas is regarded as an ideal gas, and the gas flow in the engine is processed as quasi-one-dimensional flow. It is assumed that the gas parameters on the same cross-section of the engine are evenly distributed, and the influence of the thermal inertia and combustion lag of the components on the engine performance and the influence of volume dynamics on the system are ignored, so that the basic model structure can accurately simulate the working state of the aeroengine.

[0086] Taking the aeroengine as a hydrogen fuel aeroengine as an example for modeling, first, the terminal obtains the pre-constructed basic model structure. Then, the terminal can obtain the first physical property parameters by simulating the storage state (temperature, pressure) of liquid hydrogen. The first physical property parameters of liquid hydrogen include the first flow rate and the first temperature corresponding to liquid hydrogen. For the second physical property parameters of air, the terminal can obtain the second physical property parameters of air through the simulation calculation of the previous component connected to the heat exchanger in the basic model structure. The second physical property parameters include the second flow rate and the second temperature corresponding to air.

[0087] Step 104: Simulate the cooling of aeroengine by liquid hydrogen based on the first physical property parameter and the second physical property parameter, and obtain the first outlet physical property parameter corresponding to liquid hydrogen and the second outlet physical property parameter corresponding to air in the heat exchanger.

[0088] In the embodiment of the present application, according to the low-temperature characteristics of liquid hydrogen fuel, the terminal sets a method for optimizing the performance of aeroengine through a heat exchanger and modeling. By reducing the inlet air temperature of the compressor, cooling the turbine cooling air or recovering the waste heat of the exhaust gas, the overall efficiency of the engine can be improved without increasing the engine power consumption, that is, model and simulate the above cooling process.

[0089] Specifically, when the terminal simulates the heat exchange process between liquid hydrogen and air according to the first physical property parameter of liquid hydrogen and the second physical property parameter of air, liquid hydrogen is used as the coolant, and the heat of air is absorbed through the heat exchanger to reduce the temperature of air, thereby improving the performance of the aeroengine. Then, after the heat exchange simulation based on the first physical property parameter of liquid hydrogen entering the heat exchanger and the second physical property parameter of air, the first outlet physical property parameter corresponding to the outlet liquid hydrogen and the second outlet physical property parameter corresponding to air in the heat exchanger are obtained. The first outlet physical property parameter and the second outlet physical property parameter can be used as the states of liquid hydrogen entering the combustion chamber and air entering the combustion chamber respectively to realize the modeling and simulation of the heat exchanger.

[0090] Step 106: Simulate the combustion of hydrogen fuel based on the basic model structure, the first outlet physical property parameter, the second outlet physical property parameter and the physical property parameter correction component, and determine the target physical property parameter.

[0091] In the embodiment of the present application, the terminal determines the first outlet physical property parameter and the second outlet physical property parameter as the states of liquid hydrogen and air entering the combustion chamber based on the basic simulation structure. Furthermore, the physical property parameter correction component calculates the first outlet physical property parameter and the second outlet physical property parameter to obtain the physical property parameter of the gas after the combustion of liquid hydrogen and air in the combustion chamber, that is, the target physical property parameter. Among them, the physical property parameter correction component (for example, REFPROP, a physical property database) is used to calculate the accurate physical property parameter of the gas.

[0092] Step 108: Determine the simulation result of the aeroengine according to the target physical property parameter.

[0093] In the embodiments of the present application, in the combustion chamber, liquid hydrogen and air burn to generate high-temperature and high-pressure gas. These gases then enter the turbine or nozzle, expand and do work, thereby generating thrust or mechanical power. To determine the performance of the engine, it is necessary to simulate the flow and expansion process of the gas in these components. The expansion of the gas in the turbine or nozzle can be regarded as an adiabatic expansion process, usually assumed to be a reversible process, that is, an isentropic expansion. In this process, the pressure and temperature of the gas decrease, and the velocity increases, thereby generating thrust or rotating the turbine blades to generate mechanical energy.

[0094] Based on the expansion process and thermodynamic properties of the gas, the terminal can calculate the performance parameters of the engine, such as thrust, power, efficiency, etc., according to the target physical property parameters.

[0095] In the above aero-engine modeling method, the cooling of the hydrogen fuel engine by liquid hydrogen is simulated through a heat transfer model, and the first outlet physical property parameters corresponding to liquid hydrogen and the second outlet physical property parameters corresponding to air are calculated, realizing the modeling of the heat exchanger in the hydrogen fuel engine. Combining with the physical property parameter correction component, the combustion characteristics and physical changes of hydrogen fuel can be accurately calculated, realizing the simulation of the hydrogen fuel engine and ensuring the accuracy of the simulation results.

[0096] In an exemplary embodiment, as Figure 3 shown, step 104 includes steps 302 to 306. Among them:

[0097] Step 302, obtain the third physical property parameters and heat exchanger attribute parameters between liquid hydrogen and air.

[0098] In the embodiments of the present application, the terminal environment is set to assume that liquid hydrogen and air have constant physical properties during the heat exchange process. Then, by calling the REFPROP software, the physical property parameters of liquid hydrogen and air are calculated, including specific heat, dynamic viscosity, thermal conductivity, Prandtl number, etc., as the third physical property parameters, and the heat exchanger attribute parameters, including volume, frontal area, etc., are determined according to the model information of the heat exchanger.

[0099] Step 304, determine the target heat transfer coefficient according to the first physical property parameters, the second physical property parameters, the third physical property parameters and the heat exchanger attribute parameters.

[0100] In the embodiments of the present application, the target heat transfer coefficient can be the total heat transfer coefficient on the air side. To realize the simulation analysis of the heat exchanger, the terminal uses the effectiveness-number of transfer units method to model the heat exchanger model. First, the terminal calculates the first physical property parameters, the second physical property parameters, the third physical property parameters and the heat exchanger attribute parameters by the effectiveness-number of transfer units method to obtain the total heat transfer coefficient on the air side as the target heat transfer coefficient. Specifically, under the condition of ignoring the additional thermal resistance brought by the fouling on the heat exchanger, the total heat transfer coefficient on the air side can be expressed as:

[0101]

[0102] in, They respectively represent the convective heat transfer coefficient on the liquid hydrogen side, the convective heat transfer coefficient on the air side, the heat exchange area on the liquid hydrogen side, the heat exchange area on the air side, the thermal resistance of the tube wall, and the total efficiency of the fins.

[0103] Among them, for The determination is calculated by the terminal based on the first physical property parameter and the third physical property parameter using the similarity criterion relationship given by Gnielinski, which is applicable to a wide range of Reynolds numbers including the transition zone. The convective heat transfer coefficient on the liquid hydrogen side is calculated using the Gnielinski similarity criterion formula, and its similarity criterion relationship is applicable to a wide range of Reynolds numbers, including the transition zone. The friction factor on the liquid hydrogen side assumes that the pipeline is smooth and is calculated using the standard formula. The convective heat transfer coefficient on the air side is determined by the Kolben factor and Reynolds number relationship. The fin efficiency on the air side is calculated using the single fin efficiency formula. Among them, It is calculated by the terminal based on the relationship between the second physical property parameter (air flow rate, temperature, etc.), Kolben factor and Reynolds number. Finally, the terminal can derive the total heat transfer coefficient on the air side.

[0104] Step 306: Determine a first outlet physical property parameter corresponding to liquid hydrogen and a second outlet physical property parameter corresponding to air based on the target heat transfer coefficient.

[0105] The first outlet physical property parameter includes the outlet temperature of liquid hydrogen, and the second outlet physical property parameter includes the outlet temperature and pressure drop of air.

[0106] In the present application embodiment, Figure 4 As shown, the terminal simulates the cooling process of liquid hydrogen to air in the heat exchanger according to the inlet liquid hydrogen parameters (first physical property parameters), inlet air parameters (second physical property parameters) and heat exchanger size parameters (heat exchanger property parameters) of the input heat exchanger, and obtains the outlet liquid hydrogen parameters (first outlet physical property parameters) and outlet air parameters (second outlet physical property parameters). Since the hot and cold side fluids of the heat exchanger are not mixed, the terminal determines the temperature difference relationship between the hot and cold fluids by retrieving the effectiveness relationship of the heat exchanger, and then calculates the actual heat exchange capacity by combining the relevant equations. The outlet temperatures of liquid hydrogen and air are calculated by the following formula:

[0107]

[0108]

[0109] in, is the inlet temperature of air at the heat exchanger in the second physical property parameter, is the inlet temperature of liquid hydrogen in the first physical property parameter, which is used as the input of the heat exchanger modeling model. is the outlet temperature of air in the heat exchanger, is the outlet temperature of liquid hydrogen in the heat exchanger, and respectively represent the flow rates of air and liquid hydrogen, and are the specific heat capacities of air and liquid hydrogen respectively, and can be calculated by calling the REFPROP software according to temperature and pressure. is the actual heat transfer rate. For the actual heat transfer rate , the terminal calculates it through the NTU method (Number of Transfer Units, effectiveness - heat transfer unit number method) and the target heat transfer coefficient. Specifically, the terminal determines the number of heat transfer units NTU according to the target heat transfer coefficient, and calculates the effectiveness according to the number of heat transfer units NTU , known according to the inlet conditions of the heat exchanger , then the actual heat transfer rate can be obtained .

[0110] In addition, when air flows through the heat exchanger, there will also be a pressure loss, and the pressure drop will be calculated according to the following formula:

[0111]

[0112] where are the inlet density, outlet density, and average density of air respectively. is the friction factor on the air side. is the free flow area of air, is the frontal area of the heat exchanger, is a known quantity, is the maximum flow rate per unit area of the heat exchanger, is the volume of the heat exchanger, is the heat transfer area / volume of the heat exchanger, is the fin area / total area. So far, the calculation of the heat exchanger is all completed.

[0113] In this embodiment, the hydrogen fuel aeroengine can utilize the low-temperature characteristics of liquid hydrogen to optimize the engine performance, reduce the power consumption of the compressor, improve the turbine efficiency, and recover the waste heat of the exhaust gas to enhance the overall thermal efficiency. By modeling the heat exchanger in the modeling simulation, the characteristics of the hydrogen fuel turboprop engine can be more accurately simulated.

[0114] In an exemplary embodiment, as Figure 5 shown, step 106 includes steps 502 to 506. Among them:

[0115] Step 502: Determine the oil-gas ratio based on the first outlet physical property parameters and the second outlet physical property parameters.

[0116] In the embodiments of the present application, the oil-gas ratio is the flow ratio of liquid hydrogen to air. The terminal determines the hydrogen flow rate and the air flow rate based on the first outlet physical property parameters and the second outlet physical property parameters in the outlet parameters of the heat exchanger, and then obtains the oil-gas ratio according to the ratio of the hydrogen flow rate to the air flow rate.

[0117] Step 504: Determine the mass fractions of the components in the liquid hydrogen gas based on the oil-gas ratio.

[0118] In the embodiments of the present application, hydrogen fuel usually burns under lean oil conditions. At the same time, according to the theory of chemical reaction equilibrium, the combustion of hydrogen is an irreversible reaction. The gas after the combustion of hydrogen fuel only includes air and hydrogen. The chemical reaction equation for the combustion of hydrogen fuel is as follows:

[0119]

[0120] Since air is only composed of nitrogen, oxygen, and argon, with proportions of 75.57%, 23.16%, and 1.27% respectively, and other components are ignored. Since the hydrogen fuel burns completely, the gas only contains nitrogen, oxygen, argon, and water vapor. It can be determined that the components in the liquid hydrogen gas are nitrogen, oxygen, argon, and water vapor. Then, based on the air composition, the chemical reaction equation for the combustion of hydrogen fuel, and the oil-gas ratio of the current cross-section , the mass fractions of the components in the liquid hydrogen gas can be calculated. The calculation formulas for the mass fractions of the components in the liquid hydrogen gas are as follows:

[0121]

[0122]

[0123]

[0124]

[0125] Among them, respectively represent the mass fractions of nitrogen, oxygen, argon, and water vapor.

[0126] Step 506: Simulate the combustion of hydrogen fuel based on the mass fractions, the first outlet physical property parameters, and the second outlet physical property parameters to obtain the target physical property parameters.

[0127] Among them, the target physical property parameters include the total enthalpy, total temperature, entropy, and specific heat ratio in the physical property parameters of the aero-engine.

[0128] In the embodiments of the present application, the terminal can calculate the target physical property parameters by invoking the REFPROP software according to the known mass fractions of the components of the fuel gas and the known cross-sectional physical property parameters (air flow rate, total temperature, total pressure).

[0129] In this embodiment, the mass fractions of the components in the liquid hydrogen fuel gas are determined by the oil-gas ratio, and then the target physical property parameters of the fuel and the fuel gas are accurately calculated, ensuring that the engine model can accurately reflect the combustion characteristics and physical changes after the hydrogen fuel replaces kerosene.

[0130] In an exemplary embodiment, as Figure 6 shown, when the type of the heat exchanger is a precooling heat exchanger, step 102 includes steps 602 to 604. Among them:

[0131] Step 602, obtain the initial parameters.

[0132] In the embodiments of the present application, the initial parameters are used to simulate the calculation of the intake duct, including environmental parameters, flight conditions, intake duct structure parameters, and other relevant parameters. For example, the environmental parameters include environmental temperature, environmental pressure, etc., the flight conditions include flight altitude, flight speed, etc., the intake duct structure parameters include the geometric dimensions of the intake duct, etc., and the other relevant parameters can be the flow rate, flow velocity, etc. of the external air. The terminal can obtain the initial parameters according to the real environmental data as the basic data for calculating the air parameters of the intake duct.

[0133] Step 604, determine the second physical property parameters corresponding to the outflow air of the intake duct structure according to the intake duct structure and the initial parameters in the basic model structure.

[0134] In the embodiments of the present application, as Figure 7 shown, the precooling heat exchanger is arranged between the intake duct and the compressor. The terminal simulates the flow process of the air in the intake duct based on the initial parameters and the intake duct structure in the basic model structure, and calculates the second physical property parameters of the air after flowing through the intake duct structure, including temperature, pressure, flow velocity, etc.

[0135] When the type of the heat exchanger is a precooling heat exchanger, step 104 includes:

[0136] Step 1041, simulate the cooling of the outflow air of the intake duct structure by the liquid hydrogen based on the first physical property parameters and the second physical property parameters, and obtain the first outlet physical property parameters corresponding to the liquid hydrogen in the heat exchanger and the second outlet physical property parameters corresponding to the air.

[0137] In the embodiments of the present application, when the heat exchanger is a front-cooling heat exchanger, the heat exchanger cools the air flowing out of the intake duct structure. Furthermore, the terminal calculates the heat exchange process between the liquid hydrogen and the air flowing out of the intake duct structure in the heat exchanger according to the heat exchange model, and the first outlet physical property parameters corresponding to the liquid hydrogen and the second outlet physical property parameters corresponding to the air are used as the output of the heat exchanger. Among them, the specific process of the simulated cooling calculation is the same as that of steps 302 to 306, and will not be elaborated in this actual example.

[0138] In an alternative embodiment, the heat exchanger model is integrated into the basic model structure. At the same time, the heat exchanger also has multiple heat exchange paths. By introducing different heat exchange structures into the model, the enhancement effect of the low-temperature characteristics of liquid hydrogen on the performance of the aero-engine is simulated. The specific heat transfer paths and effects of each heat exchange scheme are as Figure 8 and Figure 9 shown, Figure 8 is the nozzle heat exchanger, Figure 9 is the turbine cooler heat exchanger. When the heat exchanger is the nozzle heat exchanger, as Figure 8 shown, the heat exchanger is arranged behind the nozzle. The heat exchanger cools the gas flowing out of the nozzle structure. Furthermore, the terminal simulates and emulates the cooling process of the nozzle heat exchanger. Specifically, the terminal simulates the combustion of hydrogen fuel in the combustion chamber according to the same process as steps 502 to 506, and simulates and analyzes the physical property parameters of the gas in the gas turbine, power turbine, and nozzle according to the target physical property parameters, obtains the physical property parameters output by the nozzle structure (i.e., the input of the nozzle heat exchanger), and then simulates and analyzes the heat exchange between the hydrogen fuel and the air in the nozzle heat exchanger.

[0139] When the heat exchanger is a turbine cooler heat exchanger, the heat exchanger is arranged at the outlet of the compressor and the inlet of the combustion chamber. The compressor inputs air into the heat exchanger and respectively inputs the cooled air into the gas turbine, power turbine, and combustion chamber. Specifically, the terminal obtains the physical property parameters of the air at the outlet of the compressor, including temperature, pressure, flow rate, etc. The physical property parameters of the air at the outlet of the compressor are used as the input of the heat exchanger and perform heat exchange with the liquid hydrogen in the turbine cooler heat exchanger. By simulating the cooling effect of the liquid hydrogen on the air, the physical property parameters of the cooled air can be obtained. The cooled air is then respectively transported to the gas turbine, power turbine, and combustion chamber to provide cooling or participate in the combustion process, so as to realize the process of simulating the heat exchange between the air and the liquid hydrogen in the turbine cooler heat exchanger.

[0140] In this embodiment, the design of the heat exchanger supports different heat exchange schemes, including the front-cooling heat exchanger, the nozzle heat exchanger, and the turbine cooler heat exchanger, which can meet the performance optimization requirements under various working conditions and improve the flexibility and adaptability of the system. By utilizing the low-temperature characteristics of liquid hydrogen, the present invention can effectively improve the fuel utilization rate and system efficiency during the long-term operation of the engine and reduce fuel consumption.

[0141] In an exemplary embodiment, the simulation results include thrust and efficiency, as Figure 10 shown, step 108 includes steps 1002 to 1004. Among them:

[0142] Step 1002, determine the intermediate physical property parameters of the power turbine structure according to the target physical property parameters.

[0143] In the embodiment of the present application, the terminal calculates the geometric structure parameters and target physical property parameters of the power turbine structure according to the basic model structure, and simulates and analyzes the operating states of the gas turbine structure and the power turbine structure according to the target physical property parameters of the gas flowing out of the combustion chamber after hydrogen fuel combustion, and obtains parameters such as the temperature, pressure, and velocity distribution inside the turbine as the intermediate physical property parameters.

[0144] Step 1004, determine the thrust and efficiency of the aeroengine based on the intermediate physical property parameters.

[0145] In the embodiment of the present application, for a twin-spool turboprop engine, the terminal determines the output power of the power turbine to the reducer and the propeller according to the intermediate physical property parameters, and then determines the thrust and efficiency of the aeroengine. Specifically, the terminal calculates the mechanical work generated by the turbine based on the gas energy change in the power turbine structure, and then calculates the power transmitted to the propeller according to the transmission ratio and efficiency of the reducer in the basic model structure. Then, the terminal determines the thrust generated by the gas discharged from the tail nozzle and the thrust of the propeller according to the design parameters of the propeller (for example, diameter and pitch) in the basic model structure in combination with the environmental parameters (for example, flight speed, air density, etc.), and then obtains the thrust of the aeroengine according to the thrust of the propeller and the thrust of the tail nozzle. Furthermore, the terminal obtains the efficiency of the aeroengine according to the ratio of the thrust generated by the aeroengine to the consumed liquid hydrogen.

[0146] In this embodiment, by performing a detailed simulation analysis on the power turbine structure of the twin-spool turboprop engine and combining the target physical property parameters after hydrogen fuel combustion, the terminal can accurately calculate the intermediate physical property parameters such as the temperature, pressure, and velocity distribution inside the turbine. Based on these intermediate physical property parameters, the terminal further calculates the power output by the power turbine to the reducer and the propeller, thereby determining the propeller thrust and the tail nozzle thrust, and finally obtaining the total thrust and efficiency of the aeroengine. This systematic processing method not only improves the accuracy of the engine model, but also can effectively evaluate the impact of hydrogen fuel on the engine performance, providing strong support for engine design optimization.

[0147] In an exemplary embodiment, as Figure 11 shown, after step 104, the method further includes steps 1102 to 1106. Among them:

[0148] Step 1102, during the simulation of an aeroengine, when the preset physical property parameters are called in the current structure, according to the interfaces corresponding to the preset physical property parameters, the total temperature, total pressure, and fuel-air ratio in the current structure are transmitted to the physical property parameter correction component.

[0149] In the embodiment of the present application, interfaces for defining key physical property parameters (the key physical property parameters include physical property parameters such as total enthalpy, total temperature, entropy, specific heat ratio, and total pressure) are preset in the basic model structure as the preset physical property parameters to enable real-time data interaction with the fuel and gas property correction program and the heat exchanger module. The interfaces include the total enthalpy, total temperature, entropy, specific heat ratio, total pressure, etc. of each interface of the engine, ensuring the input and output of the physical property parameters after conversion to a hydrogen fuel engine through this interface.

[0150] For the physical property parameter correction component, the terminal realizes the dynamic correction of the gas properties through the set parameter interface, and adjusts the key physical property parameters of the aeroengine in real time according to the hydrogen combustion characteristics and the calculation results of the gas components, ensuring that the engine model can accurately reflect the combustion characteristics of hydrogen fuel and its impact on the system performance.

[0151] During the simulation of the aeroengine, when the terminal calls the preset physical property parameters, it determines the interfaces corresponding to the preset physical property parameters, and transmits the relevant parameters (the total temperature, total pressure, and fuel-air ratio in the current structure) to the physical property parameter correction component through the interfaces, and then calculates the target physical property parameters of hydrogen fuel through the physical property parameter correction component.

[0152] Step 1104, determine the mass fractions of the components in the liquid hydrogen gas based on the physical property parameter correction component and the fuel-air ratio.

[0153] In the embodiment of the present application, the terminal adjusts the preset physical property parameters related to the hydrogen fuel combustion in the aeroengine in real time according to the hydrogen combustion characteristics and the calculation results of the gas components. The physical property parameter correction component first determines the fuel-air ratio based on the hydrogen fuel flow rate and the air flow rate, and calculates the mass fractions of the components in the liquid hydrogen gas based on the fuel-air ratio. The calculation process of the mass fractions is the same as that in Steps 502 to 504, and will not be elaborated in this embodiment.

[0154] Step 1106, calculate the target physical property parameters based on the physical property parameter correction component, the mass fractions, the total temperature, and the total pressure, and feedback the target physical property parameters to the current structure.

[0155] In the embodiments of the present application, the terminal combines the mass fraction with the total temperature and total pressure in the preset physical property parameters according to the physical property parameter correction component, calculates the target physical property parameters of the gas after hydrogen fuel combustion, including physical property parameters such as total enthalpy, entropy, and specific heat ratio, and feeds back the target new parameters to the current result to perform modeling analysis according to the physical property parameters of hydrogen fuel in each structure, ensuring the simulation accuracy of the hydrogen fuel aeroengine model.

[0156] In this embodiment, by setting the parameter interface, the connection between the basic model structure and the hydrogen fuel engine characteristic model is realized, ensuring the scalability and compatibility of the model, avoiding the problem of inaccurate models caused by changes in fuel properties in traditional modeling methods, and being able to better adapt to the complex dynamic characteristics of the engine under hydrogen fuel usage conditions. At the same time, through precise parameter interface design and model integration, the applicability and practicality of the hydrogen fuel turboprop engine model are significantly improved, and through the physical property parameter correction component and the heat exchanger model based on liquid hydrogen, it is not necessary to rebuild a new engine model after replacing fuel oil with hydrogen fuel, reducing the development cost and workload.

[0157] It should be understood that although the steps in the flowcharts involved in the above-mentioned embodiments are shown in sequence according to the arrows, these steps do not necessarily have to be executed in the order indicated by the arrows. Unless there is a clear indication in this article, the execution of these steps has no strict order limit, and these steps can be executed in other orders. Moreover, at least a part of the steps in the flowcharts involved in the above-mentioned embodiments may include multiple steps or multiple stages. These steps or stages do not necessarily have to be executed at the same time, but can be executed at different times, and the execution order of these steps or stages does not necessarily have to be sequential, but can be executed alternately or alternately with at least a part of the steps or stages in other steps or other steps.

[0158] Based on the same inventive concept, the embodiments of the present application also provide an aeroengine modeling device for implementing the above-mentioned aeroengine modeling 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 aeroengine modeling device provided below can refer to the limitations on the aeroengine modeling method in the above text, and will not be repeated here.

[0159] In an exemplary embodiment, as Figure 12 shown, an aeroengine modeling device is provided, including: an acquisition module 1201, a first simulation module 1202, a second simulation module 1203, and a determination module 1204, where:

[0160] An acquisition module 1201, configured to acquire a basic model structure of an aero-engine and first physical property parameters of liquid hydrogen, and determine second physical property parameters of air according to the basic model structure;

[0161] A first simulation module 1202, configured to simulate the cooling of the aero-engine by liquid hydrogen based on the first physical property parameters and the second physical property parameters, and obtain first outlet physical property parameters corresponding to the liquid hydrogen and second outlet physical property parameters corresponding to the air in a heat exchanger;

[0162] A second simulation module 1203, configured to simulate hydrogen fuel combustion based on the basic model structure, the first outlet physical property parameters, the second outlet physical property parameters, and a physical property parameter correction component, and determine target physical property parameters;

[0163] A determination module 1204, configured to determine a simulation result of the aero-engine according to the target physical property parameters.

[0164] In one embodiment, the first simulation module 1202 is specifically configured to acquire third physical property parameters and heat exchanger attribute parameters between the liquid hydrogen and the air;

[0165] Determine a target heat transfer coefficient according to the first physical property parameters, the second physical property parameters, the third physical property parameters, and the heat exchanger attribute parameters;

[0166] Determine first outlet physical property parameters corresponding to the liquid hydrogen and second outlet physical property parameters corresponding to the air based on the target heat transfer coefficient.

[0167] In one embodiment, the second simulation module 1203 is specifically configured to determine an oil-gas ratio according to the first outlet physical property parameters and the second outlet physical property parameters;

[0168] Determine the mass fraction of each component in the liquid hydrogen gas according to the oil-gas ratio;

[0169] Simulate hydrogen fuel combustion based on the mass fraction, the first outlet physical property parameters, and the second outlet physical property parameters to obtain target physical property parameters.

[0170] In one embodiment, when the type of the heat exchanger is a pre-cooling heat exchanger, the acquisition module 1201 is specifically configured to acquire initial parameters;

[0171] Determine second physical property parameters of the air flowing out of the intake duct structure according to the intake duct structure and the initial parameters in the basic model structure;

[0172] The first simulation module 1202 is specifically configured to simulate the cooling of the air flowing out of the intake duct structure by the liquid hydrogen based on the first physical property parameters and the second physical property parameters, and obtain first outlet physical property parameters corresponding to the liquid hydrogen and second outlet physical property parameters corresponding to the air in the heat exchanger.

[0173] In one embodiment, the simulation results include thrust and efficiency; the determination module 1204 is specifically configured to determine the intermediate physical property parameters of the power turbine structure according to the target physical property parameters;

[0174] Based on the intermediate physical property parameters, determine the thrust and efficiency of the aeroengine.

[0175] In one embodiment, the device 1200 further includes:

[0176] A transmission module, configured to, during the simulation of the aeroengine, when the current structure calls the preset physical property parameters, transfer the total temperature, total pressure, and fuel-air ratio in the current structure to the physical property parameter correction component according to the interface corresponding to the preset physical property parameters;

[0177] A first calculation module, configured to determine the mass fraction of each component in the liquid hydrogen gas based on the physical property parameter correction component and the fuel-air ratio;

[0178] A second calculation module, configured to calculate the target physical property parameters based on the physical property parameter correction component, the mass fraction, the total temperature, and the total pressure, and feedback the target physical property parameters to the current structure.

[0179] Each module in the above aeroengine modeling device can be implemented in whole or in part by software, hardware, and their combination. The above modules can be embedded in the processor in the computer device in the form of hardware or be independent of it, or can be stored in the memory in the computer device in the form of software, so that the processor can call and execute the operations corresponding to the above modules.

[0180] In an exemplary embodiment, a computer device is provided. The computer device can be a server, and its internal structure diagram can be as Figure 13 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 the 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 physical property parameter data. The input / output interface of the computer device is used for the processor to exchange information with external devices. The communication interface of the computer device is used to communicate with an external terminal through a network connection. The computer program, when executed by the processor, implements an aeroengine modeling method.

[0181] Those skilled in the art can understand, Figure 13The structure shown is only a block diagram of some structures related to the solution of this application, and does not constitute a limitation on the computer device to which the solution of this application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine some components, or have different component arrangements.

[0182] 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:

[0183] Obtain the basic model structure of the aeroengine and the first physical property parameters of liquid hydrogen, and determine the second physical property parameters of air according to the basic model structure;

[0184] Based on the first physical property parameters and the second physical property parameters, simulate the cooling of the aeroengine by liquid hydrogen to obtain the first outlet physical property parameters corresponding to liquid hydrogen and the second outlet physical property parameters corresponding to air in the heat exchanger;

[0185] Based on the basic model structure, the first outlet physical property parameters, the second outlet physical property parameters, and the physical property parameter correction component, simulate the combustion of hydrogen fuel to determine the target physical property parameters;

[0186] Determine the simulation result of the aeroengine according to the target physical property parameters.

[0187] In one embodiment, when the processor executes the computer program, the following steps are further implemented:

[0188] Obtain the third physical property parameters and the heat exchanger attribute parameters between liquid hydrogen and air;

[0189] Determine the target heat transfer coefficient according to the first physical property parameters, the second physical property parameters, the third physical property parameters, and the heat exchanger attribute parameters;

[0190] Based on the target heat transfer coefficient, determine the first outlet physical property parameters corresponding to liquid hydrogen and the second outlet physical property parameters corresponding to air.

[0191] In one embodiment, when the processor executes the computer program, the following steps are further implemented:

[0192] Determine the oil-gas ratio according to the first outlet physical property parameters and the second outlet physical property parameters;

[0193] Determine the mass fraction of each component in the liquid hydrogen gas according to the oil-gas ratio;

[0194] Based on the mass fraction, the first outlet physical property parameters, and the second outlet physical property parameters, simulate the combustion of hydrogen fuel to obtain the target physical property parameters.

[0195] In one embodiment, when the type of the heat exchanger is a precooling heat exchanger, when the processor executes the computer program, the following steps are further implemented:

[0196] Obtain initial parameters;

[0197] Determine the second physical property parameters corresponding to the outflow air of the intake duct structure according to the intake duct structure and the initial parameters in the basic model structure;

[0198] Simulate the cooling of liquid hydrogen to the aero-engine based on the first physical property parameters and the second physical property parameters, and obtain the first outlet physical property parameters corresponding to the liquid hydrogen and the second outlet physical property parameters corresponding to the air in the heat exchanger, including:

[0199] Simulate the cooling of the outflow air of the intake duct structure by liquid hydrogen based on the first physical property parameters and the second physical property parameters, and obtain the first outlet physical property parameters corresponding to the liquid hydrogen and the second outlet physical property parameters corresponding to the air in the heat exchanger.

[0200] In one embodiment, the simulation results include thrust and efficiency; when the processor executes the computer program, the following steps are further implemented:

[0201] Determine the intermediate physical property parameters of the power turbine structure according to the target physical property parameters;

[0202] Determine the thrust and efficiency of the aero-engine based on the intermediate physical property parameters.

[0203] In one embodiment, when the processor executes the computer program, the following steps are further implemented:

[0204] During the simulation of the aero-engine, when the current structure calls the preset physical property parameters, transfer the total temperature, total pressure and fuel-air ratio in the current structure to the physical property parameter correction component according to the interface corresponding to the preset physical property parameters;

[0205] Determine the mass fraction of each component in the liquid hydrogen gas according to the physical property parameter correction component and the fuel-air ratio;

[0206] Calculate the target physical property parameters based on the physical property parameter correction component, the mass fraction, the total temperature and the total pressure, and feedback the target physical property parameters to the current structure.

[0207] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored, and when the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0208] In one embodiment, a computer program product is provided, including a computer program, and when the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0209] 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 for analysis, stored data, displayed data, etc.) involved in this application are all information and data that have been authorized by the user or fully authorized by all parties, and the collection, use, and processing of relevant data need to comply with relevant regulations.

[0210] 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.

[0211] 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.

[0212] 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 scope of the patent 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 method for modeling an aeroengine, characterized in that: The method comprises: Acquire a basic model structure of the aircraft engine and first physical property parameters of liquid hydrogen, and determine second physical property parameters of air according to the basic model structure; Based on the first physical property parameter and the second physical property parameter, the cooling of the aircraft engine by the liquid hydrogen is simulated to obtain a first outlet physical property parameter corresponding to the liquid hydrogen and a second outlet physical property parameter corresponding to the air in the heat exchanger; Based on the basic model structure, the first outlet physical property parameter, the second outlet physical property parameter and the physical property parameter correction component, simulate hydrogen fuel combustion to determine target physical property parameters; The simulation result of the aircraft engine is determined according to the target physical property parameters.

2. The method according to claim 1, characterized in that: The method of simulating the cooling of the aircraft engine by the liquid hydrogen based on the first physical property parameter and the second physical property parameter to obtain the first outlet physical property parameter corresponding to the liquid hydrogen and the second outlet physical property parameter corresponding to the air in the heat exchanger includes: Acquiring a third physical property parameter and a heat exchanger property parameter between the liquid hydrogen and the air; Determine a target heat transfer coefficient according to the first physical property parameter, the second physical property parameter, the third physical property parameter and the heat exchanger attribute parameter; A first outlet physical property parameter corresponding to the liquid hydrogen and a second outlet physical property parameter corresponding to the air are determined based on the target heat exchange coefficient.

3. The method according to claim 1, characterized in that The method of simulating hydrogen fuel combustion based on the basic model structure, the first outlet physical property parameter, the second outlet physical property parameter and the physical property parameter correction component to determine the target physical property parameter includes: Determining the oil-gas ratio according to the first outlet physical property parameter and the second outlet physical property parameter; Determining the mass fraction of each component in the liquid hydrogen fuel gas according to the oil-gas ratio; The hydrogen fuel combustion is simulated based on the mass fraction, the first outlet physical property parameter and the second outlet physical property parameter to obtain the target physical property parameter.

4. The method according to claim 1, characterized in that: If the type of the heat exchanger is a front-cooling heat exchanger, determining the second physical property parameter of the air according to the basic model structure includes: Get initial parameters; Determining a second physical property parameter corresponding to outflow air of the intake duct structure according to the intake duct structure in the basic model structure and the initial parameters; The method of simulating the cooling of the aircraft engine by the liquid hydrogen based on the first physical property parameter and the second physical property parameter to obtain the first outlet physical property parameter corresponding to the liquid hydrogen and the second outlet physical property parameter corresponding to the air in the heat exchanger includes: The cooling of the outflowing air of the inlet duct structure by the liquid hydrogen is simulated based on the first physical property parameter and the second physical property parameter to obtain the first outlet physical property parameter corresponding to the liquid hydrogen and the second outlet physical property parameter corresponding to the air in the heat exchanger.

5. The method according to claim 1, characterized in that: The simulation results include thrust and efficiency; the simulation results of the aircraft engine are determined according to the target physical property parameters, including: Determining intermediate physical property parameters of the power turbine structure according to the target physical property parameters; The thrust and efficiency of the aircraft engine are determined based on the intermediate physical property parameters.

6. The method according to claim 1, characterized in that After simulating the cooling of the aircraft engine by the liquid hydrogen based on the first physical property parameter and the second physical property parameter to obtain the first outlet physical property parameter corresponding to the liquid hydrogen in the heat exchanger and the second outlet physical property parameter corresponding to the air, the method further includes: In the process of simulating the aircraft engine, when the current structure calls the preset physical property parameters, the total temperature, total pressure and oil-gas ratio in the current structure are transmitted to the physical property parameter correction component according to the interface corresponding to the preset physical property parameters; Determining the mass fraction of each component in the liquid hydrogen fuel gas according to the physical property parameter correction component and the oil-gas ratio; Target physical property parameters are calculated based on the physical property parameter correction component, the mass fraction, the total temperature and the total pressure, and the target physical property parameters are fed back to the current structure.

7. An aircraft engine modeling device, characterized in that: The device comprises: An acquisition module, used to acquire a basic model structure of an aircraft engine and a first physical property parameter of liquid hydrogen, and determine a second physical property parameter of air according to the basic model structure; A first simulation module is used to simulate the cooling of the aircraft engine by the liquid hydrogen based on the first physical property parameter and the second physical property parameter to obtain a first outlet physical property parameter corresponding to the liquid hydrogen and a second outlet physical property parameter corresponding to the air in the heat exchanger; A second simulation module simulates hydrogen fuel combustion based on the basic model structure, the first outlet physical property parameter, the second outlet physical property parameter and a physical property parameter correction component to determine target physical property parameters; A determination module is used to determine the simulation result of the aircraft engine according to the target physical property parameters.

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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