Aeroengine simulation system and method

Abstract

The application relates to an aero-engine simulation system and method. The aero-engine simulation system comprises a first heat exchange module and a combustion module, and the first heat exchange module is connected with the combustion module. The first heat exchange module is used for delivering simulated hydrogen fuel to the combustion module, and the simulated hydrogen fuel is obtained by heating first liquid hydrogen by the first heat exchange module. The combustion module is used for receiving the simulated hydrogen fuel and burning the simulated hydrogen fuel to provide power for a simulated aircraft. The aero-engine simulation system provided by the application can adapt to emerging hydrogen fuel engine types.

Description

Technical Field

[0001] This application relates to the field of aero-engine modeling and control technology, and in particular to an aero-engine simulation system and method. Background Technology

[0002] In recent years, with the development of aero-engine technology and increased emphasis on environmental protection, the trend of replacing kerosene with hydrogen fuel as aviation fuel has been growing. Hydrogen fuel produces hydrogen gas with high calorific value and low pollution. The calorific value of hydrogen is approximately 3-4 times that of aviation kerosene, and its energy density is much higher than that of aviation kerosene. Higher energy density means less fuel mass, which can reduce the weight load of the aircraft.

[0003] Research on hydrogen-fueled aircraft engines began in the 1950s; however, despite hydrogen's superior energy density, its limitations due to its gaseous state and cost prevented it from entering the market and being put into use. In recent years, due to the urgent need for decarbonization in aviation, new hydrogen-fueled engine designs and technical solutions have been proposed.

[0004] However, current aero-engine simulation platforms are mainly designed for traditional kerosene-fueled aero-engines and cannot adapt to emerging hydrogen fuel cell engines. Summary of the Invention

[0005] Therefore, it is necessary to provide an aero-engine simulation system and method that can adapt to emerging hydrogen fuel cell engine configurations to address the aforementioned technical problems.

[0006] In a first aspect, this application provides an aero-engine simulation system. The system includes a first heat exchange module and a combustion module; the first heat exchange module is connected to the combustion module.

[0007] The first heat exchange module is used to supply simulated hydrogen fuel to the combustion module; the simulated hydrogen fuel is obtained by heating the first liquid hydrogen in the first heat exchange module.

[0008] The combustion module is used to receive the simulated hydrogen fuel and burn it to power the simulated aircraft.

[0009] In one embodiment, the system further includes a second heat exchange module; a first end of the second heat exchange module is connected to the first heat exchange module, and a second end of the second heat exchange module is connected to the combustion module;

[0010] The second heat exchange module is used to supply the first steam to the combustion module;

[0011] The combustion module is used to burn the simulated hydrogen fuel under the action of the first steam to provide power to the simulated aircraft.

[0012] In one embodiment, the system further includes a fuel delivery module connected to the first heat exchange module;

[0013] The fuel transfer module is used to deliver the first liquid hydrogen to the first heat exchange module via a simulated pipeline;

[0014] The first heat exchange module is used to receive the first liquid hydrogen and use the exhaust gas generated by the combustion module to heat the first liquid hydrogen to obtain the simulated hydrogen fuel.

[0015] In one embodiment, the system further includes:

[0016] The first heat exchange module is used to condense the second vapor in the exhaust gas generated by the combustion module using the first liquid hydrogen to obtain the target liquid, and then transfer the target liquid to the second heat exchange module.

[0017] In one embodiment, the system further includes:

[0018] The second heat exchange module is used to heat the target liquid to obtain the first steam, and to transmit the first steam to the simulated compressor stage for heat exchange and cooling of each simulated compressor; the simulated compressor provides air to the combustion module.

[0019] In one embodiment, the combustion module includes a combustion unit;

[0020] The combustion unit is used to control the flow rate and injection temperature of the first steam according to user instructions.

[0021] In one embodiment, the system further includes:

[0022] The combustion module is used to determine the heat value absorbed by the second steam based on the flow rate and injection temperature of the first steam.

[0023] In one embodiment, the combustion module includes an evaluation unit;

[0024] This assessment unit is used to determine the amount of pollutants emitted based on the combustion temperature when the combustion module burns the simulated hydrogen fuel.

[0025] In one embodiment, the first heat exchange module is a module modeled based on the flow rate of the simulated hydrogen fuel and the flow rate of the air.

[0026] Secondly, this application also provides a method for simulating an aero-engine. The method includes:

[0027] Simulated hydrogen fuel is supplied to the combustion module using the first heat exchange module; the simulated hydrogen fuel is obtained by heating the first liquid hydrogen using the first heat exchange module.

[0028] The simulated hydrogen fuel is received and burned using a combustion module to power the simulated aircraft.

[0029] The aforementioned aero-engine simulation system and method include an aero-engine simulation system comprising a first heat exchange module and a combustion module; the first heat exchange module is connected to the combustion module. The first heat exchange module is used to supply simulated hydrogen fuel to the combustion module; the simulated hydrogen fuel is obtained by heating first liquid hydrogen in the first heat exchange module. The combustion module is used to receive and burn the simulated hydrogen fuel to provide power to the simulated aircraft. Traditional aero-engine simulation platforms are mainly designed for conventional kerosene-fueled aero-engines, and current aero-engine simulation platforms cannot adapt to emerging hydrogen fuel engine configurations. However, in the aero-engine simulation system of this application embodiment, the first heat exchange module is used to transfer simulated hydrogen fuel to the combustion module, which then completes the combustion of the simulated hydrogen fuel to provide power to the simulated aircraft. The aero-engine simulation system provided in this application embodiment can adapt to emerging hydrogen fuel engine configurations. Attached Figure Description

[0030] Figure 1 This is one of the structural block diagrams of an aero-engine simulation system provided in an embodiment of this application;

[0031] Figure 2 A second structural block diagram of an aero-engine simulation system provided in this application embodiment;

[0032] Figure 3 A schematic diagram of a simulated operating condition for an aero-engine is provided for an embodiment of this application;

[0033] Figure 4 A schematic diagram illustrating the change in hydrogen fuel flow rate during a simulation process, provided for an embodiment of this application;

[0034] Figure 5 One of the flowcharts of an aero-engine simulation method provided in this application embodiment;

[0035] Figure 6 A second schematic flowchart illustrating an aero-engine simulation method provided in this application embodiment;

[0036] Figure 7 A schematic flowchart illustrating a method for determining simulated hydrogen fuel provided in an embodiment of this application;

[0037] Figure 8 This is an internal structural diagram of a computer device provided in an embodiment of this application. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0039] Currently, mainstream aero-engine simulation systems are mainly designed for traditional kerosene-fueled aero-engines, supporting only fuel changes on traditional aero-engine simulation systems. They lack support for modules such as low-emission hydrogen combustion chambers, heat exchangers, and backfire modules, and cannot adapt to the changing configurations of emerging hydrogen fuel cell engines. Therefore, this application proposes a simulation system and method suitable for hydrogen fuel cell aero-engines, providing a foundation for the performance analysis, overall design, and research and development of control systems for hydrogen fuel cell aero-engines.

[0040] In one embodiment, Figure 1 This is one of the structural block diagrams of an aero-engine simulation system provided in an embodiment of this application, such as... Figure 1 As shown, the system includes a first heat exchange module 101 and a combustion module 102; the first heat exchange module 101 is connected to the combustion module 102.

[0041] The first heat exchange module 101 is used to supply simulated hydrogen fuel to the combustion module 102; the simulated hydrogen fuel is obtained by heating the first liquid hydrogen in the first heat exchange module 101.

[0042] The first liquid hydrogen may include cryogenic liquid hydrogen, meaning its temperature is below a preset temperature threshold. The aero-engine simulation system is a simulation platform used to simulate aero-engines. This aero-engine simulation system is used to simulate emerging hydrogen fuel cell aero-engines. The first heat exchange module 101 may be a simulated regenerative heat exchanger.

[0043] In this embodiment, the aero-engine simulation system may include a first heat exchange module 101 and a combustion module 102. The first heat exchange module 101 can be connected to the combustion module 102. A simulated liquid hydrogen tank may exist. The first heat exchange module 101 obtains cryogenic liquid hydrogen from the simulated liquid hydrogen tank and heats it. After being heated, the first liquid hydrogen becomes simulated hydrogen fuel. At this time, the first heat exchange module 101 can deliver the simulated hydrogen fuel to the combustion module 102. For example, the simulated hydrogen fuel can be heated to 700K and injected into the combustion module 102.

[0044] It should be noted that the aero-engine simulation system may include modules corresponding to the stable motion simulation system at the component level of a traditional civil turbofan engine established using the cavity method, a first heat exchange module 101, and a combustion module 102.

[0045] Combustion module 102 is used to receive and burn simulated hydrogen fuel to power the simulated aircraft.

[0046] In this embodiment of the application, the combustion module 102 can be the combustion chamber of an aircraft engine that simulates a real-world scenario. The combustion module 102 can receive simulated hydrogen fuel from the first heat exchange module 101 and burn the simulated hydrogen fuel to provide power to the simulated aircraft.

[0047] In this embodiment, the aero-engine simulation system includes a first heat exchange module 101 and a combustion module 102; the first heat exchange module 101 is connected to the combustion module 102. The first heat exchange module 101 is used to supply simulated hydrogen fuel to the combustion module 102; the simulated hydrogen fuel is obtained by heating first liquid hydrogen in the first heat exchange module 101. The combustion module 102 is used to receive the simulated hydrogen fuel and burn it to provide power to the simulated aircraft. Traditional aero-engine simulation platforms are mainly designed for conventional configurations of kerosene-fueled aero-engines, and current aero-engine simulation platforms cannot adapt to emerging hydrogen fuel engine configurations. However, in the aero-engine simulation system of this application embodiment, the first heat exchange module is used to transfer simulated hydrogen fuel to the combustion module, and the combustion module completes the combustion of the simulated hydrogen fuel to provide power to the simulated aircraft. The aero-engine simulation system provided in this application embodiment can adapt to emerging hydrogen fuel engine configurations.

[0048] In one embodiment, Figure 2 This is a second structural block diagram of an aero-engine simulation system provided in an embodiment of this application, as shown below. Figure 2 As shown, the system also includes a second heat exchange module 201; the first end of the second heat exchange module 201 is connected to the first heat exchange module 101, and the second end of the second heat exchange module 201 is connected to the combustion module 102.

[0049] The second heat exchange module 201 is used to supply the first steam to the combustion module 102.

[0050] Combustion module 102 is used to burn simulated hydrogen fuel under the action of first steam to provide power to the simulated aircraft.

[0051] The first type of steam can be water vapor.

[0052] Specifically, the aircraft engine simulation system may further include a second heat exchange module 201. The first end of the second heat exchange module 201 can be connected to the first heat exchange module 101, and the second end can be connected to the combustion module 102. The second heat exchange module 201 can convert the liquid transmitted from the first heat exchange module into first steam and deliver the first steam to the combustion module 102. Upon receiving the first steam, the combustion module 102 can burn simulated hydrogen fuel under the action of the first steam to provide power to the simulated aircraft. For example, the second heat exchange module 201 can convert water transmitted from the first heat exchange module 101 into water vapor.

[0053] In this embodiment, the aircraft engine simulation system includes a second heat exchange module 201. A first end of the second heat exchange module 201 is connected to a first heat exchange module 101, and a second end of the second heat exchange module 201 is connected to a combustion module 102. The second heat exchange module 201 is used to supply first steam to the combustion module 102. The combustion module 102 is used to burn simulated hydrogen fuel under the action of the first steam to provide power to the simulated aircraft. Because the first steam is added to the combustion module 102, the high-temperature flame temperature generated by burning the simulated hydrogen fuel can be reduced, thus reducing the generation of nitrogen oxides and lowering environmental pollution.

[0054] In one embodiment, such as Figure 2 As shown, the aero-engine simulation system also includes a fuel transfer module 202, which is connected to the first heat exchange module 101.

[0055] Fuel transfer module 202 is used to deliver first liquid hydrogen to first heat exchange module 101 via a simulated pipeline.

[0056] In this embodiment, the aero-engine simulation system may further include a fuel transfer module 202, which serves as a transfer tool between the fuel tank 203 and the first heat exchange module 101. The fuel transfer module 202 can obtain first liquid hydrogen from the fuel tank and transfer it to the first heat exchange module 101 via a simulated pipeline. The fuel tank may be a hydrogen fuel tank, such as a liquid hydrogen tank.

[0057] The first heat exchange module 101 is used to receive the first liquid hydrogen and heat the first liquid hydrogen with the exhaust gas generated by the combustion module 102 to obtain simulated hydrogen fuel.

[0058] Specifically, the exhaust gas produced after the combustion module 102 burns the simulated hydrogen fuel is ejected from the simulated tailpipe, and this exhaust gas has a certain amount of residual heat. The first heat exchange module 101 can receive the first liquid hydrogen delivered by the fuel transfer module 202 through the simulated pipeline, and use the residual heat of the exhaust gas to heat the first liquid hydrogen, thereby obtaining simulated hydrogen fuel, that is, obtaining hydrogen.

[0059] In this embodiment, the aero-engine simulation system further includes a fuel transfer module 202, which is connected to the first heat exchange module 101. The fuel transfer module 202 is used to deliver first liquid hydrogen to the first heat exchange module 101 via a simulated pipeline. The first heat exchange module 101 receives the first liquid hydrogen and heats it with the exhaust gas generated by the combustion module 102 to obtain simulated hydrogen fuel. Since the exhaust gas generated by the combustion module 102 has a certain amount of waste heat, this waste heat can be used to heat the first liquid hydrogen to obtain simulated hydrogen fuel. This is equivalent to recycling the exhaust gas and eliminates the need for additional heating equipment to heat the first liquid hydrogen, making it more environmentally friendly and reducing costs.

[0060] In one embodiment, the aero-engine simulation system further includes: a first heat exchange module 101, used to obtain a target liquid by condensing the second vapor in the exhaust gas generated by the first liquid hydrogen combustion module 102, and to transfer the target liquid to the second heat exchange module 201.

[0061] The target liquid can be water.

[0062] Specifically, after the combustion module 102 burns the simulated hydrogen fuel, the product obtained is water vapor, i.e., the second steam. The first heat exchange module 101 can use first liquid hydrogen that has reached a preset low temperature to condense the second steam in the exhaust gas generated by the combustion module 102, and obtain water after condensation. The first heat exchange module 101 can transfer the water to the second heat exchange module 201 so that the second heat exchange module 201 can obtain water vapor to cool the combustion module 102 and each simulated compressor.

[0063] In one embodiment, the aero-engine simulation system further includes a second heat exchange module 201, which heats the target liquid to obtain first steam and transmits the first steam to the simulated compressor stages for heat exchange and cooling of each simulated compressor; the simulated compressor provides air to the combustion module.

[0064] Specifically, after the first heat exchange module 101 transfers water to the second heat exchange module 201, the second heat exchange module 201 can heat the water to obtain first steam (water vapor) and transfer the first steam to the simulated compressor stage for heat exchange and cooling of the intermediate-pressure compressor 204 and the high-pressure compressor 205. The intermediate-pressure compressor 204 and the high-pressure compressor 205 can provide air for the combustion module 102.

[0065] In this embodiment, cooling heat exchange is achieved by injecting first steam into the interstage of the simulated compressor, which reduces the interstage temperature of the engine, decreases the compressor blade load, increases the working capacity of the impeller machinery, and improves the engine pressure ratio.

[0066] In one embodiment, the combustion module includes a combustion unit for controlling the flow rate and injection temperature of the first steam according to user instructions.

[0067] The combustion unit can be a low-emission combustion unit.

[0068] Specifically, the combustion unit can be used to control the flow rate and injection temperature of the first steam, providing a control interface for the hydrogen fuel cell aircraft engine. Preferably, the flow rate of the first steam can be 3% of the air flow rate, and the injection temperature of the first steam can be 100 degrees Celsius.

[0069] In this embodiment, since a combustion unit is provided that can control the flow rate and injection temperature of the first steam, the emission of nitrogen oxides can be reduced by adjusting the injection temperature of the first steam.

[0070] In one embodiment, the system further includes a combustion module 102 for determining the heat value absorbed by the first steam based on the flow rate and injection temperature of the first steam.

[0071] Specifically, the combustion module 102 included in the aero-engine simulation system can determine the heat value absorbed by the first steam based on the received first steam flow rate and first steam injection temperature, using a preset algorithm. The formula for determining the heat value absorbed by the first steam is as follows:

[0072]

[0073] Among them, W steam Represents the flow rate of the first steam. This represents the temperature at t0 = 0℃, t f The average specific heat capacity of water at 100℃ This represents the temperature at t0 = 0℃, t f The average specific heat capacity of water at time T4. Where t... f T1 represents the injection temperature of the first steam, and T4 represents the outlet temperature of the combustion module.

[0074] In this embodiment, the system also includes a combustion module 102, which is used to determine the heat value absorbed by the first steam based on the flow rate and injection temperature of the first steam, thus facilitating the calculation of the heat value absorbed by the first steam.

[0075] In one embodiment, the combustion module 102 includes an evaluation unit;

[0076] An evaluation unit is used to determine the amount of pollutants emitted based on the combustion temperature of simulated hydrogen fuel when combustion module 102 burns it.

[0077] Pollutants may include nitrogen oxides (NOx).

[0078] Specifically, the assessment unit can be used to quickly assess nitrogen oxide emissions. For the same aero-engine, there is a unique functional relationship between the converted fuel flow rate and the reference nitrogen oxide emission index. Furthermore, there is a one-to-one correspondence between the converted fuel flow rate and the temperature after the combustion chamber. Therefore, nitrogen oxide emissions can be quickly assessed using the temperature after the combustion chamber. That is, the assessment unit can determine the pollutant emissions based on the combustion temperature when the combustion module 102 burns simulated hydrogen fuel.

[0079] In this embodiment, the evaluation unit can determine the amount of pollutants emitted based on the combustion temperature when the combustion module 102 burns simulated hydrogen fuel. This improves the convenience of obtaining the amount of pollutants emitted.

[0080] In one embodiment, the first heat exchange module 101 is a module obtained by modeling based on the simulated flow rate of hydrogen fuel and the flow rate of air.

[0081] Specifically, the modeling principle formula for the first heat exchange module 101 is the enthalpy increase and enthalpy decrease of the heat exchange medium:

[0082]

[0083] in T represents mass flow rate, and C represents temperature. P The value represents the specific heat at constant pressure, with the subscript H2 representing hydrogen and air representing air. That is, the model is based on the simulated flow rates of hydrogen fuel, air, hydrogen specific heat at constant pressure, air specific heat at constant pressure, and the current temperature.

[0084] In this embodiment, the first heat exchange module 101, which is modeled based on the simulated flow rate of hydrogen fuel and the flow rate of air, has higher accuracy.

[0085] Optionally, the system may also include a flashback module, which is used in the case of combustion module 102 burning simulated hydrogen fuel. Since the combustion speed of hydrogen fuel is relatively fast, the combustion speed may be greater than the injection speed. To improve safety, the combustion flame will return to the nozzle.

[0086] It should be noted that, as Figure 2 As shown, the aero-engine simulation system may also include an air intake module 206, an outer bypass module 207, a simulated outer bypass nozzle 208, a simulated fan 209, a simulated environment 210, a simulated high-pressure turbine 211, a simulated low-pressure turbine 212, a simulated core nozzle 213, etc.

[0087] In a real-world simulation scenario, such as Figure 3 As shown, Figure 3This document provides a schematic diagram of an aero-engine simulation operating condition as an embodiment of this application. The simulation environment 210 can be configured and commands input can be set as follows: altitude can be set to 0m, 0m, 4500m, 7500m, 10000m, 10000m, 0m; Mach number can be set to 0, 0.2, 0.6, 0.7, 0.8, 0.77, 0; and throttle commands can be set to 65°, 50°, 50°, 50°, 50°, 20°, 15°. After the simulation begins, it is designed to complete all simulations within 5.6 seconds. Performance parameters of the aero-engine during the simulation, such as hydrogen fuel consumption, unit fuel consumption rate, thrust, turbine inlet temperature, airflow, jet velocity, nitrogen oxide emission index, fuel-air ratio, and temperature and pressure of various major engine interfaces, can be extracted and analyzed. The change process of hydrogen fuel flow rate during the simulation can be referenced... Figure 4 , Figure 4 This is a schematic diagram illustrating the change in hydrogen fuel flow rate during a simulation process, as provided in an embodiment of this application.

[0088] The aero-engine simulation system provided in this application can be used to evaluate the overall performance of hydrogen fuel cell engines (NOx emission index, heat absorbed by water vapor, thrust speed, fuel consumption rate, etc.). Through correction using experimental data, the dynamic characteristics of the hydrogen fuel cell engine can be reflected. Furthermore, this simulation system can be used to enable a control system to control performance parameters such as nitrogen oxide emissions based on the information obtained from the system.

[0089] The modules in the aforementioned aero-engine simulation device can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device, or stored in the computer device's memory as software, so that the processor can call and execute the corresponding operations of each module.

[0090] Based on the same inventive concept, this application also provides an aero-engine simulation method for implementing the aero-engine simulation system described above. The solution provided by this method is similar to the implementation scheme described in the above system; therefore, the specific limitations in one or more aero-engine simulation method embodiments provided below can be found in the limitations of the aero-engine simulation system described above, and will not be repeated here.

[0091] Figure 5 This is one of the flowcharts illustrating an aero-engine simulation method provided in this application embodiment, such as... Figure 5 As shown, an aero-engine simulation method is provided, including the following steps:

[0092] S501. Simulated hydrogen fuel is supplied to the combustion module using the first heat exchange module; the simulated hydrogen fuel is obtained by heating the first liquid hydrogen using the first heat exchange module.

[0093] S502: The combustion module receives and burns simulated hydrogen fuel to power the simulated aircraft.

[0094] In the aforementioned aero-engine simulation method, the aero-engine simulation system includes a first heat exchange module 101 and a combustion module 102; the first heat exchange module 101 is connected to the combustion module 102. The first heat exchange module 101 is used to supply simulated hydrogen fuel to the combustion module 102; the simulated hydrogen fuel is obtained by heating first liquid hydrogen in the first heat exchange module 101. The combustion module 102 is used to receive the simulated hydrogen fuel and burn it to provide power to the simulated aircraft. Traditional aero-engine simulation platforms are mainly designed for conventional configurations of kerosene-fueled aero-engines, and current aero-engine simulation platforms cannot adapt to emerging hydrogen fuel engine configurations. However, in the aero-engine simulation system of this application embodiment, the first heat exchange module is used to transfer simulated hydrogen fuel to the combustion module, and the combustion module completes the combustion of the simulated hydrogen fuel to provide power to the simulated aircraft. The aero-engine simulation system provided in this application embodiment can adapt to emerging hydrogen fuel engine configurations.

[0095] In one embodiment, Figure 6 This is a second flowchart illustrating an aero-engine simulation method provided in this application. The method further includes:

[0096] S601. The first steam is supplied to the combustion module using the second heat exchange module.

[0097] S602. The combustion module burns simulated hydrogen fuel under the action of the first steam to provide power to the simulated aircraft.

[0098] In one embodiment, Figure 7 This application provides a flowchart illustrating a method for determining simulated hydrogen fuel, which further includes:

[0099] S701. The first liquid hydrogen is delivered to the first heat exchange module via a simulated pipeline using the fuel transfer module.

[0100] S702. The first liquid hydrogen is received by the first heat exchange module and heated by the exhaust gas generated by the combustion module to obtain simulated hydrogen fuel.

[0101] In one embodiment, the method further includes:

[0102] The first heat exchange module uses the first liquid hydrogen to condense the second vapor in the exhaust gas generated by the combustion module to obtain the target liquid, and then transfers the target liquid to the second heat exchange module.

[0103] In one embodiment, the method further includes:

[0104] The target liquid is heated by the second heat exchange module to obtain the first steam, and the first steam is transmitted to the simulated compressor stage for heat exchange and cooling of each simulated compressor; the simulated compressor provides air to the combustion module.

[0105] In one embodiment, the method further includes:

[0106] The combustion unit controls the flow rate and injection temperature of the first steam according to user instructions.

[0107] In one embodiment, the method further includes:

[0108] The combustion module determines the heat value absorbed by the first steam based on the flow rate and injection temperature of the first steam.

[0109] In one embodiment, the method further includes:

[0110] The emission of pollutants is determined by using the evaluation unit based on the combustion temperature of simulated hydrogen fuel in the combustion module.

[0111] In one embodiment, the first heat exchange module is a module obtained by modeling based on the simulated flow rate of hydrogen fuel and the flow rate of air.

[0112] It should be understood that although the steps in the flowcharts of the above embodiments are shown sequentially according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some steps in the flowcharts of the above embodiments may include multiple steps or multiple stages. These steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these steps or stages is not necessarily sequential, but can be performed alternately or in turn with other steps or at least some of the steps or stages of other steps.

[0113] In one embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as follows: Figure 8As shown, the computer device includes a processor, memory, input / output interface, communication interface, display unit, and input device. The processor, memory, and input / output interface are connected via a system bus, and the communication interface, display unit, and input device are also connected to the system bus via the input / output interface. The processor provides computational and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The input / output interface is used for exchanging information between the processor and external devices. The communication interface is used for wired or wireless communication with external terminals; wireless communication can be achieved through Wi-Fi, mobile cellular networks, NFC (Near Field Communication), or other technologies. When the computer program is executed by the processor, it implements an aero-engine simulation method. The display unit is used to form a visually visible image and can be a display screen, projection device, or virtual reality imaging device. The display screen can be an LCD screen or an e-ink screen. The input device of the computer device can be a touch layer covering the display screen, or buttons, trackballs, or touchpads set on the casing of the computer device, or external keyboards, touchpads, or mice, etc.

[0114] Those skilled in the art will understand that Figure 8 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0115] In one embodiment, a computer device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to perform the following steps:

[0116] Simulated hydrogen fuel is supplied to the combustion module using the first heat exchange module; the simulated hydrogen fuel is obtained by heating the first liquid hydrogen using the first heat exchange module.

[0117] The combustion module receives and burns simulated hydrogen fuel to power the simulated aircraft.

[0118] In one embodiment, the processor, when executing a computer program, also performs the following steps:

[0119] The second heat exchange module is used to supply the first steam to the combustion module;

[0120] The combustion module uses a first steam source to burn simulated hydrogen fuel to power the simulated aircraft.

[0121] In one embodiment, the processor, when executing a computer program, also performs the following steps:

[0122] The first liquid hydrogen is delivered to the first heat exchange module via a simulated pipeline using the fuel transfer module.

[0123] The first liquid hydrogen is received by the first heat exchange module and heated by the exhaust gas generated by the combustion module to obtain simulated hydrogen fuel.

[0124] In one embodiment, the processor, when executing a computer program, also performs the following steps:

[0125] The first heat exchange module uses the first liquid hydrogen to condense the second vapor in the exhaust gas generated by the combustion module to obtain the target liquid, and then transfers the target liquid to the second heat exchange module.

[0126] In one embodiment, the processor, when executing a computer program, also performs the following steps:

[0127] The target liquid is heated by the second heat exchange module to obtain the first steam, and the first steam is transmitted to the simulated compressor stage for heat exchange and cooling of each simulated compressor; the simulated compressor provides air to the combustion module.

[0128] In one embodiment, the processor, when executing a computer program, also performs the following steps:

[0129] The combustion unit controls the flow rate and injection temperature of the first steam according to user instructions.

[0130] In one embodiment, the processor, when executing a computer program, also performs the following steps:

[0131] The combustion module determines the heat value absorbed by the first steam based on the flow rate and injection temperature of the first steam.

[0132] In one embodiment, the processor, when executing a computer program, also performs the following steps:

[0133] The emission of pollutants is determined by using the evaluation unit based on the combustion temperature of simulated hydrogen fuel in the combustion module.

[0134] In one embodiment, the processor, when executing a computer program, also performs the following steps:

[0135] The module is derived from modeling based on the simulated flow rates of hydrogen fuel and air.

[0136] In one embodiment, a computer-readable storage medium is provided having a computer program stored thereon, the computer program performing the following steps when executed by a processor:

[0137] Simulated hydrogen fuel is supplied to the combustion module using the first heat exchange module; the simulated hydrogen fuel is obtained by heating the first liquid hydrogen using the first heat exchange module.

[0138] The combustion module receives and burns simulated hydrogen fuel to power the simulated aircraft.

[0139] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0140] The second heat exchange module is used to supply the first steam to the combustion module;

[0141] The combustion module uses a first steam source to burn simulated hydrogen fuel to power the simulated aircraft.

[0142] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0143] The first liquid hydrogen is delivered to the first heat exchange module via a simulated pipeline using the fuel transfer module.

[0144] The first liquid hydrogen is received by the first heat exchange module and heated by the exhaust gas generated by the combustion module to obtain simulated hydrogen fuel.

[0145] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0146] The first heat exchange module uses the first liquid hydrogen to condense the second vapor in the exhaust gas generated by the combustion module to obtain the target liquid, and then transfers the target liquid to the second heat exchange module.

[0147] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0148] The target liquid is heated by the second heat exchange module to obtain the first steam, and the first steam is transmitted to the simulated compressor stage for heat exchange and cooling of each simulated compressor; the simulated compressor provides air to the combustion module.

[0149] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0150] The combustion unit controls the flow rate and injection temperature of the first steam according to user instructions.

[0151] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0152] The combustion module determines the heat value absorbed by the first steam based on the flow rate and injection temperature of the first steam.

[0153] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0154] The emission of pollutants is determined by using the evaluation unit based on the combustion temperature of simulated hydrogen fuel in the combustion module.

[0155] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0156] The module is derived from modeling based on the simulated flow rates of hydrogen fuel and air.

[0157] In one embodiment, a computer program product is provided, including a computer program that, when executed by a processor, performs the following steps:

[0158] Simulated hydrogen fuel is supplied to the combustion module using the first heat exchange module; the simulated hydrogen fuel is obtained by heating the first liquid hydrogen using the first heat exchange module.

[0159] The combustion module receives and burns simulated hydrogen fuel to power the simulated aircraft.

[0160] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0161] The second heat exchange module is used to supply the first steam to the combustion module;

[0162] The combustion module uses a first steam source to burn simulated hydrogen fuel to power the simulated aircraft.

[0163] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0164] The first liquid hydrogen is delivered to the first heat exchange module via a simulated pipeline using the fuel transfer module.

[0165] The first liquid hydrogen is received by the first heat exchange module and heated by the exhaust gas generated by the combustion module to obtain simulated hydrogen fuel.

[0166] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0167] The first heat exchange module uses the first liquid hydrogen to condense the second vapor in the exhaust gas generated by the combustion module to obtain the target liquid, and then transfers the target liquid to the second heat exchange module.

[0168] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0169] The target liquid is heated by the second heat exchange module to obtain the first steam, and the first steam is transmitted to the simulated compressor stage for heat exchange and cooling of each simulated compressor; the simulated compressor provides air to the combustion module.

[0170] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0171] The combustion unit controls the flow rate and injection temperature of the first steam according to user instructions.

[0172] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0173] The combustion module determines the heat value absorbed by the first steam based on the flow rate and injection temperature of the first steam.

[0174] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0175] The emission of pollutants is determined by using the evaluation unit based on the combustion temperature of simulated hydrogen fuel in the combustion module.

[0176] In one embodiment, when the computer program is executed by a processor, it further performs the following steps:

[0177] The module is derived from modeling based on the simulated flow rates of hydrogen fuel and air.

[0178] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium. When executed, the computer program can include the processes of the embodiments of the above methods. Any references to memory, databases, or other media used in the embodiments provided in this application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetic random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM can take many forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM). The databases involved in the embodiments provided in this application may include at least one type of relational database and non-relational database. Non-relational databases may include, but are not limited to, blockchain-based distributed databases. The processors involved in the embodiments provided in this application may be general-purpose processors, central processing units, graphics processing units, digital signal processors, programmable logic devices, quantum computing-based data processing logic devices, etc., and are not limited to these.

[0179] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0180] The above embodiments are merely illustrative of several implementation methods of this application, and their descriptions are relatively specific and detailed. However, they should not be construed as limiting the scope of this application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. An aircraft engine simulation system, characterized in that, The system includes a first heat exchange module, a second heat exchange module, and a combustion module; the first heat exchange module is connected to the combustion module; a first end of the second heat exchange module is connected to the first heat exchange module, and a second end of the second heat exchange module is connected to the combustion module. The first heat exchange module is used to supply simulated hydrogen fuel to the combustion module; the simulated hydrogen fuel is obtained by heating the first liquid hydrogen with the first heat exchange module. The combustion module is used to receive the simulated hydrogen fuel and burn the simulated hydrogen fuel to provide power to the simulated aircraft. The second heat exchange module is used to supply first steam to the combustion module; The combustion module is used to burn the simulated hydrogen fuel under the action of the first steam to provide power to the simulated aircraft. The first heat exchange module is used to condense the second vapor in the exhaust gas generated by the combustion module using the first liquid hydrogen to obtain the target liquid, and then transfer the target liquid to the second heat exchange module. The second heat exchange module is used to heat the target liquid to obtain the first steam, and to transmit the first steam to the simulated compressor stage for heat exchange and cooling of each simulated compressor; the simulated compressor provides air to the combustion module.

2. The system according to claim 1, characterized in that, The system also includes a fuel transfer module, which is connected to the first heat exchange module; The fuel transfer module is used to deliver the first liquid hydrogen to the first heat exchange module via a simulated pipeline; The first heat exchange module is used to receive the first liquid hydrogen and heat the first liquid hydrogen with the exhaust gas generated by the combustion module to obtain the simulated hydrogen fuel.

3. The system according to claim 1, characterized in that, The combustion module includes a combustion unit; The combustion unit is used to control the flow rate and injection temperature of the first steam according to user instructions.

4. The system according to claim 3, characterized in that, The system also includes: The combustion module is used to determine the heat value absorbed by the first steam based on the received flow rate and injection temperature of the first steam.

5. The system according to claim 1, characterized in that, The combustion module includes an evaluation unit; The evaluation unit is used to determine the amount of pollutants emitted based on the combustion temperature when the combustion module burns the simulated hydrogen fuel.

6. The system according to claim 1, characterized in that, The first heat exchange module is a module obtained by modeling based on the flow rate of the simulated hydrogen fuel and the flow rate of the air.

7. The system according to claim 1, characterized in that, The flow rate of the first steam is 3% of the air flow rate, and the injection temperature of the first steam is 100 degrees Celsius.

8. The system according to claim 1, characterized in that, The first heat exchange module is a module obtained by modeling based on the simulated flow rate of hydrogen fuel and the flow rate of air.

9. The system according to claim 1, characterized in that, The combustion module calculates the heat value absorbed by the first steam based on the received flow rate and injection temperature of the first steam, using a preset algorithm.

10. A method for simulating an aero-engine, characterized in that, For an aero-engine simulation system as described in any one of claims 1 to 9, the method comprises: Simulated hydrogen fuel is supplied to the combustion module using the first heat exchange module; the simulated hydrogen fuel is obtained by heating the first liquid hydrogen using the first heat exchange module. The method involves receiving and burning the simulated hydrogen fuel using a combustion module to power a simulated aircraft; this includes supplying first steam to the combustion module via a second heat exchange module; and using the combustion module to burn the simulated hydrogen fuel under the action of the first steam to power the simulated aircraft. The first liquid hydrogen in the first heat exchange module is used to condense the second vapor in the exhaust gas generated by the combustion module to obtain the target liquid, and the target liquid is then transferred to the second heat exchange module. The target liquid is heated using the second heat exchange module to obtain the first steam, and the first steam is transmitted to the simulated compressor stage for heat exchange and cooling of each simulated compressor; the simulated compressor provides air to the combustion module.

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