Aviation high-temperature hydrogen fuel cell energy recycling system

Abstract

The invention provides an aviation high-temperature hydrogen fuel cell energy recycling system, relates to the technical field of energy recycling, and is used for recycling energy of fuel cell reaction waste gas / waste liquid so as to effectively improve the energy utilization efficiency of a high-temperature fuel cell. The system comprises a reaction waste gas power generation module, a reaction gas heating and pressurizing module and a high-temperature hydrogen fuel cell, the high-temperature hydrogen fuel cell is respectively connected with the reaction waste gas power generation module and the reaction gas heating and pressurizing module; the reaction gas heating and pressurizing module is used for providing air and gas hydrogen for the high-temperature hydrogen fuel cell; the high-temperature hydrogen fuel cell is used for generating reaction waste gas based on the operation of air and hydrogen provided by the reaction gas heating and pressurizing module; and the reaction waste gas power generation module is used for recycling high-temperature and high-pressure waste gas generated by the high-temperature hydrogen fuel cell, generating electric energy based on the high-temperature and high-pressure waste gas and supplying power to the reaction gas heating and pressurizing module.

Description

Technical Field

[0001] The present application relates to the field of energy recovery technology, and in particular to an aviation high-temperature hydrogen fuel cell energy recovery and utilization system. Background Art

[0002] Hydrogen fuel cells are a clean power device with high energy density, which has great potential application value in the aviation field. Existing hydrogen fuel cells mostly use heat exchangers to collect heat from reaction waste liquid or exhaust gas, and recover this energy through cogeneration, reforming hydrogen production, heating ammonia steam for power generation, etc.

[0003] At present, energy recovery solutions for fuel cells are all based on ground equipment. Due to the small pressure difference between the reaction exhaust gas and the atmospheric environment, the energy recovery efficiency of the fuel cell reaction exhaust gas / waste liquid is not high. Summary of the invention

[0004] The embodiment of the present application provides an aviation high-temperature hydrogen fuel cell energy recovery and utilization system for recovering the energy of fuel cell reaction exhaust gas / waste liquid, thereby effectively improving the energy utilization efficiency of the high-temperature fuel cell.

[0005] An embodiment of the present invention provides an aviation high-temperature hydrogen fuel cell energy recovery and utilization system, the system comprising: a reaction exhaust gas power generation module, a reaction gas heating and pressurizing module, and a high-temperature hydrogen fuel cell; the high-temperature hydrogen fuel cell is connected to the reaction exhaust gas power generation module and the reaction gas heating and pressurizing module respectively;

[0006] The reaction gas heating and pressurizing module is used to provide air and gaseous hydrogen to the high-temperature hydrogen fuel cell;

[0007] The high temperature hydrogen fuel cell generates reaction exhaust gas based on the operation of air and gaseous hydrogen provided by the reaction gas heating and pressurizing module;

[0008] The reaction exhaust gas power generation module is used to recover the high-temperature and high-pressure exhaust gas generated by the high-temperature hydrogen fuel cell, generate electrical energy based on the high-temperature and high-pressure exhaust gas, and supply power to the reaction gas heating and boosting module.

[0009] In an optional embodiment, the system further comprises: a fuel cell cooling module connected to the high temperature hydrogen fuel cell;

[0010] The fuel cell cooling module is used to provide cooling liquid or cooling gas for the fuel cell cooling module.

[0011] In an optional embodiment, the system further comprises: a power transmission and distribution device and an aircraft power transmission and distribution network; the power transmission and distribution device is respectively connected to the aircraft power transmission and distribution network, the reaction exhaust gas power generation module, the reaction gas heating and pressurizing module, and the fuel cell cooling module;

[0012] The power transmission and distribution device is used to receive the electric energy transmitted by the reaction exhaust gas power generation module, and to supply power to the reaction gas heating and pressurization module, the fuel cell cooling module, and the aircraft power transmission and distribution network.

[0013] In an optional embodiment, the system further comprises: an avionics network;

[0014] The avionics network is respectively connected to the fuel cell cooling module, the reaction gas heating and boosting module, and the aircraft power transmission and distribution network, and is used to provide flight altitude data for the fuel cell cooling module, the reaction gas heating and boosting module, and the aircraft power transmission and distribution network.

[0015] In an optional embodiment, the reaction exhaust gas power generation module includes: an exhaust gas turbine, a generator;

[0016] The exhaust gas turbine is used to collect the reaction exhaust gas of the high-temperature fuel cell, and the exhaust gas turbine drives the coaxially connected generator to work to generate electrical energy.

[0017] In an optional embodiment, the reaction gas heating and pressurizing module includes: an electric heating heat exchanger, an air compressor, and a liquid nitrogen storage tank;

[0018] The liquid nitrogen storage tank is used to store liquid nitrogen and transport liquid nitrogen to the electric heating heat exchanger;

[0019] The electric heating heat exchanger is used to heat the liquid nitrogen to produce gaseous hydrogen, and transport the gaseous hydrogen to the high-temperature hydrogen fuel cell;

[0020] The air compressor is used to extract air and deliver the extracted air to the high-temperature hydrogen fuel cell.

[0021] In an optional embodiment, the system further comprises: a simulation device;

[0022] The simulation device is used to determine the hardware parameters corresponding to the exhaust gas turbine, the generator, and the power transmission and distribution device at the cruising altitude;

[0023] The simulation device is also used to perform semi-physical field simulation based on the hardware parameters corresponding to the exhaust gas turbine, the generator, and the power transmission and distribution device, and obtain the power transmission and distribution parameters corresponding to the power transmission and distribution devices at different aircraft flight altitudes.

[0024] In an optional embodiment, the process of the simulation device determining the hardware parameters of the exhaust gas turbine at the cruising altitude is:

[0025] Step 1.1.1, determining the pressure drop ratio of the exhaust gas turbine at the cruising altitude of the aircraft according to the outlet exhaust gas pressure of the high-temperature hydrogen fuel cell and the pressure of the atmospheric environment at the cruising altitude, determining the type and size of the exhaust gas turbine according to the pressure drop ratio and the volume and weight limit allocated to the exhaust gas turbine by the aircraft, and determining the operating speed of the exhaust gas turbine at the cruising altitude according to the type and size of the exhaust gas turbine;

[0026] Step 1.1.2, determining a three-dimensional model of the exhaust gas turbine according to the type, size and operating speed of the exhaust gas turbine at a cruising altitude, and performing a three-dimensional flow field simulation on the three-dimensional model of the exhaust gas turbine to obtain a simulation result of the exhaust gas turbine;

[0027] Step 1.1.3, determine whether the simulation result of the exhaust gas turbine meets the preset conditions. If so, determine the current speed and torque of the exhaust gas turbine as the hardware parameters of the exhaust gas turbine; if not, modify the size and operating speed of the exhaust gas turbine, and jump to step 1.1.2 to continue execution.

[0028] In an optional embodiment, the process of the simulation device determining the hardware parameters of the generator at the cruising altitude is:

[0029] Step 1.2.1, determining the type, main dimensions, and winding parameters of the generator based on the finally determined speed and torque of the exhaust gas turbine, the load power demand, and the volume and weight of the aircraft allocated to the generator;

[0030] Step 1.2.2, determining a three-dimensional model of the generator according to the type, main dimensions, and winding parameters of the generator, and performing a three-dimensional electric-thermal joint simulation on the three-dimensional model of the generator to obtain a generator simulation result;

[0031] Step 1.2.3, if the simulation result of the generator meets the volume and weight requirements assigned to the generator by the aircraft and can meet the power demand of the load end, the current power generation parameters of the generator are determined as the hardware parameters of the generator; if the simulation result of the generator does not meet the volume and weight requirements assigned to the generator by the aircraft and can meet the power demand of the load end, the main dimensions and winding parameters of the generator are modified, and jump to step 1.2.2 to continue execution.

[0032] In an optional embodiment, the process of the simulation device determining the hardware parameters of the power transmission and distribution device at the cruising altitude is:

[0033] Step 1.3.1, determining the basic architecture and controller type of the power transmission and distribution device according to the power generation parameters of the generator and the power demand of each power-consuming device;

[0034] Step 1.3.2, at a cruising altitude, performing a semi-physical field simulation according to the basic architecture and controller type of the power transmission and distribution device to obtain a simulation result of the power transmission and distribution device;

[0035] Step 1.3.3, based on the simulation results of the power transmission and distribution device, verify whether the power transmission and distribution device can meet the aircraft's needs for power distribution at cruising altitude. If it can, output the power transmission and distribution device hardware and power transmission and distribution logic; if it cannot meet the aircraft's needs for power distribution at cruising altitude, optimize the design of the power transmission and distribution device by adjusting the control logic, and jump to step 1.3.2 to continue execution.

[0036] In an optional embodiment, the simulation device is specifically used for:

[0037] Step 2.1, obtaining the speed and torque of the exhaust gas turbine at different flight altitudes;

[0038] Step 2.2, using the exhaust gas turbine speed and torque obtained in step 2.1 to simulate the generator, and obtaining the power generation parameters of the generator at different flight altitudes;

[0039] Step 2.3, according to the power generation parameters of the generator at different aircraft flight altitudes, and the power requirements of the fuel cell cooling module and the reaction gas heating and boosting module at different aircraft flight altitudes, design a rectifier device and related control logic in the power transmission and distribution device, and perform performance verification through semi-physical field simulation. If the requirements are met, output the hardware parameters and power transmission and distribution logic of the power transmission and distribution device.

[0040] The present invention provides an aviation high-temperature hydrogen fuel cell energy recovery and utilization system, which includes: a reaction exhaust gas power generation module, a reaction gas heating and boosting module, and a high-temperature hydrogen fuel cell. Among them, the high-temperature hydrogen fuel cell is connected to the reaction exhaust gas power generation module and the reaction gas heating and boosting module respectively. The reaction gas heating and boosting module is used to provide air and gaseous hydrogen for the high-temperature hydrogen fuel cell; the high-temperature hydrogen fuel cell is used to generate reaction exhaust gas based on the operation of the air and gaseous hydrogen provided by the reaction gas heating and boosting module; the reaction exhaust gas power generation module is used to recover the high-temperature and high-pressure exhaust gas generated by the high-temperature hydrogen fuel cell, generate electrical energy based on the high-temperature and high-pressure exhaust gas, and supply power to the reaction gas heating and boosting module. Therefore, through this application, it is achieved to use the reaction exhaust gas of the high-temperature hydrogen fuel cell to generate electricity, effectively improving the energy utilization efficiency of the high-temperature fuel cell. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1A structural block diagram of an aviation high-temperature hydrogen fuel cell energy recovery and utilization system provided in this application;

[0042] Figure 2 A flow chart of a simulation device execution method provided by this application;

[0043] Figure 3 A flowchart of another simulation device execution method provided in this application. DETAILED DESCRIPTION

[0044] In order to better understand the above-mentioned technical scheme, the technical scheme of the embodiments of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical scheme of the embodiments of the present application, rather than limitations on the technical scheme of the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments may be combined with each other.

[0045] See also Figure 1 , an aviation high-temperature hydrogen fuel cell energy recovery and utilization system provided in an embodiment of the present invention, the system includes: a reaction exhaust gas power generation module, a reaction gas heating and pressurization module, and a high-temperature hydrogen fuel cell.

[0046] Specific as Figure 1 As shown, the high-temperature hydrogen fuel cell is connected to the reaction exhaust gas power generation module and the reaction gas heating and boosting module respectively. Among them, the reaction gas heating and boosting module is used to provide air and gaseous hydrogen for the high-temperature hydrogen fuel cell; the high-temperature hydrogen fuel cell is used to generate reaction exhaust gas based on the operation of the air and gaseous hydrogen provided by the reaction gas heating and boosting module; the reaction exhaust gas power generation module is used to recover the high-temperature and high-pressure exhaust gas generated by the high-temperature hydrogen fuel cell, generate electrical energy based on the high-temperature and high-pressure exhaust gas, and supply power to the reaction gas heating and boosting module. Therefore, through this application, it is achieved to generate electricity using the reaction exhaust gas of the high-temperature hydrogen fuel cell, effectively improving the energy utilization efficiency of the high-temperature fuel cell.

[0047] In an optional embodiment, the system further includes: a fuel cell cooling module connected to the high-temperature hydrogen fuel cell; the fuel cell cooling module is used to provide cooling liquid or cooling gas to the fuel cell cooling module.

[0048] In an optional embodiment, the system also includes: a power transmission and distribution device, an aircraft power transmission and distribution network; the power transmission and distribution device is respectively connected to the aircraft power transmission and distribution network, the reaction exhaust gas power generation module, the reaction gas heating and boosting module, and the fuel cell cooling module; the power transmission and distribution device is used to receive the electric energy transmitted by the reaction exhaust gas power generation module, and to supply power to the reaction gas heating and boosting module, the fuel cell cooling module, and the aircraft power transmission and distribution network.

[0049] In an optional embodiment, the system also includes: an avionics network; the avionics network is respectively connected to the fuel cell cooling module, the reaction gas heating and boosting module, and the aircraft power transmission and distribution network, and is used to provide flight altitude data for the fuel cell cooling module, the reaction gas heating and boosting module, and the aircraft power transmission and distribution network.

[0050] Specifically, the avionics network can provide an altitude signal to the fuel cell cooling module, so that the fuel cell cooling module provides a corresponding cooling function for the high-temperature hydrogen fuel cell based on the altitude signal and the temperature signal provided by the high-temperature hydrogen fuel cell, such as determining the operating power of the cooling device according to the specific altitude and temperature, thereby achieving effective cooling of the high-temperature hydrogen fuel cells according to the altitude and temperature.

[0051] Specific as Figure 1 As shown, in an optional embodiment, the reaction exhaust gas power generation module includes: an exhaust gas turbine and a generator; the exhaust gas turbine is used to collect the reaction exhaust gas of the high-temperature fuel cell, and the exhaust gas turbine drives the coaxially connected generator to work to generate electricity. The reaction gas heating and boosting module includes: an electric heating heat exchanger, an air compressor, and a liquid nitrogen storage tank; the liquid nitrogen storage tank is used to store liquid nitrogen and transport liquid nitrogen to the electric heating heat exchanger; the electric heating heat exchanger is used to heat the liquid nitrogen to produce gaseous hydrogen, and transport the gaseous hydrogen to the high-temperature hydrogen fuel cell; the air compressor is used to extract air and transport the extracted air to the high-temperature hydrogen fuel cell.

[0052] In this embodiment, the high-temperature hydrogen fuel cell generates high-temperature and high-pressure exhaust gas when it is working. The exhaust gas turbine in this system collects the reaction exhaust gas of the high-temperature hydrogen fuel cell. The exhaust gas turbine drives the coaxial generator to work. After generating electricity, the power transmission and distribution device provides electricity to the fuel cell cooling module, the reaction heating and boosting module, and the aircraft power transmission and distribution network. Therefore, this application realizes the use of the reaction exhaust gas of the high-temperature hydrogen fuel cell to generate electricity, effectively improving the energy utilization efficiency of the high-temperature fuel cell.

[0053] An embodiment of the present invention provides an aviation high-temperature hydrogen fuel cell energy recovery and utilization system, which includes: a reaction exhaust gas power generation module, a reaction gas heating and boosting module, and a high-temperature hydrogen fuel cell. Among them, the high-temperature hydrogen fuel cell is connected to the reaction exhaust gas power generation module and the reaction gas heating and boosting module respectively. The reaction gas heating and boosting module is used to provide air and gaseous hydrogen for the high-temperature hydrogen fuel cell; the high-temperature hydrogen fuel cell is used to generate reaction exhaust gas based on the operation of the air and gaseous hydrogen provided by the reaction gas heating and boosting module; the reaction exhaust gas power generation module is used to recover the high-temperature and high-pressure exhaust gas generated by the high-temperature hydrogen fuel cell, generate electrical energy based on the high-temperature and high-pressure exhaust gas, and supply power to the reaction gas heating and boosting module. Therefore, through this application, it is achieved to use the reaction exhaust gas of the high-temperature hydrogen fuel cell to generate electricity, effectively improving the energy utilization efficiency of the high-temperature fuel cell.

[0054] like Figure 2 As shown, the present application can determine the hardware parameters corresponding to the exhaust gas turbine, generator, and power transmission and distribution device in the aviation high-temperature hydrogen fuel cell energy recovery and utilization system through a simulation device. The execution process of the simulation device is:

[0055] Step 1, determining the hardware parameters corresponding to the exhaust gas turbine, the generator, and the power transmission and distribution device at the cruising altitude.

[0056] like Figure 3 As shown, in an optional embodiment, the process of the simulation device determining the hardware parameters of the exhaust gas turbine at the cruising altitude is:

[0057] Step 1.1.1, determining the pressure drop ratio of the exhaust gas turbine at the cruising altitude of the aircraft according to the outlet exhaust gas pressure of the high-temperature hydrogen fuel cell and the pressure of the atmospheric environment at the cruising altitude, determining the type and size of the exhaust gas turbine according to the pressure drop ratio and the volume and weight limit allocated to the exhaust gas turbine by the aircraft, and determining the operating speed of the exhaust gas turbine at the cruising altitude according to the type and size of the exhaust gas turbine;

[0058] Step 1.1.2, determining a three-dimensional model of the exhaust gas turbine according to the type, size and operating speed of the exhaust gas turbine at a cruising altitude, and performing a three-dimensional flow field simulation on the three-dimensional model of the exhaust gas turbine to obtain a simulation result of the exhaust gas turbine;

[0059] In this embodiment, step 1.1.2 is to model and simulate the design of the exhaust gas turbine. Since the type of the exhaust gas turbine and its approximate operating speed at the aircraft cruising altitude are determined in step 1.1.1, a speed can be set first, and the size and three-dimensional model of the exhaust gas turbine can be determined using the three-dimensional design software, and then the three-dimensional flow field simulation can be performed using the three-dimensional model of the exhaust gas turbine.

[0060] Step 1.1.3, determine whether the simulation result of the exhaust gas turbine meets the preset conditions. If so, determine the current speed and torque of the exhaust gas turbine as the hardware parameters of the exhaust gas turbine; if not, modify the size and operating speed of the exhaust gas turbine, and jump to step 1.1.2 to continue execution.

[0061] In this embodiment, step 1.1.3 is an optimization iteration of the exhaust gas turbine three-dimensional model. Analyze the simulation results of the exhaust gas turbine in step 1.1.2. If the simulation results of the exhaust gas turbine can meet the design point requirements, such as the pressure drop ratio, the weight and volume restrictions allocated to the exhaust gas turbine by the aircraft, then output the exhaust gas turbine three-dimensional model, exhaust gas turbine speed and torque. If the simulation results of the exhaust gas turbine cannot meet the design point requirements, the exhaust gas turbine model structure is optimized, such as by changing the blade angle, overall size and speed to adjust the three-dimensional model of the exhaust gas turbine, and jump to step 1.1.2 to continue. Finally, determine the exhaust gas turbine three-dimensional model and the design point speed and torque of the exhaust gas turbine at the aircraft cruising altitude.

[0062] like Figure 3 As shown, in an optional embodiment, the process of the simulation device determining the hardware parameters of the generator at the cruising altitude is:

[0063] Step 1.2.1, determining the type, main dimensions, and winding parameters of the generator based on the finally determined speed and torque of the exhaust gas turbine, the load power demand, and the volume and weight of the aircraft allocated to the generator;

[0064] The speed and torque of the exhaust gas turbine are the final results obtained in step 1.1.3.

[0065] Step 1.2.2, determining a three-dimensional model of the generator according to the type, main dimensions, and winding parameters of the generator, and performing a three-dimensional electric-thermal joint simulation on the three-dimensional model of the generator to obtain a generator simulation result;

[0066] Step 1.2.2 is to model and simulate the design of the generator. Since the type, main dimensions and winding parameters of the generator are established in step 1.2.1, in this embodiment, a parameter combination can be selected to design a three-dimensional model of the generator using a three-dimensional design software, and then the three-dimensional electric-thermal joint simulation is performed using the three-dimensional model of the generator to obtain the generator simulation result.

[0067] Step 1.2.3, if the simulation result of the generator meets the volume and weight requirements assigned to the generator by the aircraft and can meet the power demand of the load end, the current power generation parameters of the generator are determined as the hardware parameters of the generator; if the simulation result of the generator does not meet the volume and weight requirements assigned to the generator by the aircraft and can meet the power demand of the load end, the main dimensions and winding parameters of the generator are modified, and jump to step 1.2.2 to continue execution.

[0068] Step 1.2.3 is the optimization of the generator structure. If the generator simulation results can meet the volume and weight requirements assigned to the generator by the aircraft and can meet the power demand of the load end, the three-dimensional model of the generator is output. If the above requirements cannot be met, the generator is optimized, such as adjusting the three-dimensional model of the generator by changing the winding parameters, overall dimensions and resistance and reactance parameters, and repeating step 1.2.2. Finally, through step 1.2, the three-dimensional model and power generation parameters of the generator under the aircraft cruising state need to be determined.

[0069] like Figure 3 As shown, in an optional embodiment, the process of the simulation device determining the hardware parameters of the power transmission and distribution device at the cruising altitude is:

[0070] Step 1.3.1, determining the basic architecture and controller type of the power transmission and distribution device according to the power generation parameters of the generator and the power demand of each power-consuming device;

[0071] Step 1.3.2, at a cruising altitude, performing a semi-physical field simulation according to the basic architecture and controller type of the power transmission and distribution device to obtain a simulation result of the power transmission and distribution device;

[0072] Step 1.3.2 is to design the power transmission and distribution logic and the power transmission and distribution device hardware. When the aircraft is in cruising state, the power transmission and distribution system should give priority to supplying the power generated by the generator to the high-temperature hydrogen fuel cell auxiliary system (i.e., the reaction gas heating and boosting module and the fuel cell cooling module). After meeting the power demand of the high-temperature hydrogen fuel cell auxiliary system, the excess power will be supplied to the aircraft power transmission and distribution network. After completing the design of the power transmission and distribution device in this embodiment, semi-physical field simulation is required to obtain the simulation results of the power transmission and distribution device, so as to verify the performance of the power transmission and distribution device according to the simulation results of the power transmission and distribution device.

[0073] Step 1.3.3, based on the simulation results of the power transmission and distribution device, verify whether the power transmission and distribution device can meet the aircraft's needs for power distribution at cruising altitude. If it can, output the power transmission and distribution device hardware and power transmission and distribution logic; if it cannot meet the aircraft's needs for power distribution at cruising altitude, optimize the design of the power transmission and distribution device by adjusting the control logic, and jump to step 1.3.2 to continue execution.

[0074] Step 1.3.3 is the optimization of the power transmission and distribution device. Through the semi-physical field simulation in step 1.3.2, it can be verified whether the power transmission and distribution device can meet the needs of the aircraft for power distribution in the cruising state according to the simulation results of the power transmission and distribution device. If it can be met, the power transmission and distribution device hardware and power transmission and distribution logic are output; if it cannot meet the needs of the aircraft for power distribution in the cruising state, the power transmission and distribution device is optimized by adjusting the control logic, and step 1.3.2 is repeated. Finally, the power transmission and distribution logic and the power transmission and distribution device hardware need to be determined through step 1.3.3.

[0075] Step 2: Perform a semi-physical field simulation based on the hardware parameters corresponding to the exhaust gas turbine, the generator, and the power transmission and distribution device, and obtain the power transmission and distribution parameters corresponding to the power transmission and distribution device at different aircraft flight altitudes.

[0076] In this embodiment, the core is the design of the power transmission and distribution system around the exhaust gas turbine speed at different aircraft flight altitudes. Since the three-dimensional model of the exhaust gas turbine is determined in step 1, the pressure ratio between the high-temperature hydrogen fuel cell reaction exhaust gas and the atmospheric environment will change at different flight altitudes, which will cause the exhaust gas turbine speed to change, thereby causing the power generation parameters output by the generator to fluctuate. Therefore, it is necessary to optimize the rectification capacity and power transmission and distribution control logic of the power transmission and distribution system.

[0077] Step 2.1, obtaining the speed and torque of the exhaust gas turbine at different flight altitudes;

[0078] Step 2.2, using the exhaust gas turbine speed and torque obtained in step 2.1 to simulate the generator, and obtaining the power generation parameters of the generator at different flight altitudes;

[0079] In this embodiment, first, the speed and torque of the exhaust gas turbine at different aircraft flight altitudes must be obtained according to step 2.1, and the speed and torque of the exhaust gas turbine obtained in step 2.1 are output to step 2.2 to simulate the generator, and the generator power generation parameters are obtained and output to step 2.3.

[0080] Step 2.3, according to the power generation parameters of the generator at different aircraft flight altitudes, and the power requirements of the fuel cell cooling module and the reaction gas heating and boosting module at different aircraft flight altitudes, design a rectifier device and related control logic in the power transmission and distribution device, and perform performance verification through semi-physical field simulation. If the requirements are met, output the hardware parameters and power transmission and distribution logic of the power transmission and distribution device.

[0081] Step 2.3 is to optimize the design of the power transmission and distribution device at different aircraft flight altitudes. Step 2.2 can obtain the generator power generation parameters at different aircraft flight altitudes. Combined with the power demand of the hydrogen fuel cell auxiliary system at different aircraft flight altitudes, the rectifier and related control logic can be designed in the power transmission and distribution device, and the performance can be verified through semi-physical field simulation. If the requirements are met, the hardware parameters and power transmission and distribution logic of the power transmission and distribution device are output. Finally, step 2.3 needs to determine the power transmission and distribution device hardware and the power transmission and distribution logic at different aircraft flight altitudes.

[0082] It should be understood that the order of execution of the steps in the above embodiment does not necessarily mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiment of the present invention.

[0083] Those of ordinary skill in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing related hardware through a computer program, and 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-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application may include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), RAMbus direct RAM (RDRAM), direct RAMbus dynamic RAM (DRDRAM), and RAMbus dynamic RAM (RDRAM), etc.

[0084] Those skilled in the art can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional units and modules is used as an example. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above.

[0085] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention.

Claims

1. An aviation high-temperature hydrogen fuel cell energy recovery and utilization system, characterized in that: The system comprises: a reaction waste gas power generation module, a reaction gas heating and pressurizing module, and a high-temperature hydrogen fuel cell; the high-temperature hydrogen fuel cell is connected to the reaction waste gas power generation module and the reaction gas heating and pressurizing module respectively; The reaction gas heating and pressurizing module is used to provide air and gaseous hydrogen to the high-temperature hydrogen fuel cell; The high temperature hydrogen fuel cell generates reaction exhaust gas based on the operation of air and gaseous hydrogen provided by the reaction gas heating and pressurizing module; The reaction exhaust gas power generation module is used to recover the high-temperature and high-pressure exhaust gas generated by the high-temperature hydrogen fuel cell, generate electrical energy based on the high-temperature and high-pressure exhaust gas, and supply power to the reaction gas heating and boosting module.

2. The system according to claim 1, characterized in that The system further comprises: a fuel cell cooling module connected to the high temperature hydrogen fuel cell; The fuel cell cooling module is used to provide cooling liquid or cooling gas for the fuel cell cooling module.

3. The system according to claim 2, characterized in that The system further comprises: a power transmission and distribution device and an aircraft power transmission and distribution network; the power transmission and distribution device is respectively connected to the aircraft power transmission and distribution network, the reaction exhaust gas power generation module, the reaction gas heating and pressurizing module, and the fuel cell cooling module; The power transmission and distribution device is used to receive the electric energy transmitted by the reaction exhaust gas power generation module, and to supply power to the reaction gas heating and pressurization module, the fuel cell cooling module, and the aircraft power transmission and distribution network.

4. The system according to claim 3, characterized in that The system also includes: an avionics network; The avionics network is respectively connected to the fuel cell cooling module, the reaction gas heating and boosting module, and the aircraft power transmission and distribution network, and is used to provide flight altitude data for the fuel cell cooling module, the reaction gas heating and boosting module, and the aircraft power transmission and distribution network.

5. The system according to any one of claims 1 to 4, characterized in that: The reaction exhaust gas power generation module comprises: an exhaust gas turbine and a generator; The exhaust gas turbine is used to collect the reaction exhaust gas of the high-temperature fuel cell, and the exhaust gas turbine drives the coaxially connected generator to work to generate electrical energy.

6. The system according to any one of claims 1 to 4, characterized in that: The reaction gas heating and pressurizing module comprises: an electric heating heat exchanger, an air compressor, and a liquid hydrogen storage tank; The liquid nitrogen storage tank is used to store liquid nitrogen and transport liquid nitrogen to the electric heating heat exchanger; The electric heating heat exchanger is used to heat the liquid nitrogen to produce gaseous hydrogen, and transport the gaseous hydrogen to the high-temperature hydrogen fuel cell; The air compressor is used to extract air and deliver the extracted air to the high-temperature hydrogen fuel cell.

7. The system according to claim 3, characterized in that The system also includes: a simulation device; The simulation device is used to determine the hardware parameters corresponding to the exhaust gas turbine, the generator, and the power transmission and distribution device at the cruising altitude; The simulation device is also used to perform semi-physical field simulation based on the hardware parameters corresponding to the exhaust gas turbine, the generator, and the power transmission and distribution device, and obtain the power transmission and distribution parameters corresponding to the power transmission and distribution devices at different aircraft flight altitudes.

8. The system according to claim 7, characterized in that The process of the simulation device determining the hardware parameters of the exhaust gas turbine at the cruising altitude is as follows: Step 1.1.1, determining the pressure drop ratio of the exhaust gas turbine at the cruising altitude of the aircraft according to the outlet exhaust gas pressure of the high-temperature hydrogen fuel cell and the pressure of the atmospheric environment at the cruising altitude, determining the type and size of the exhaust gas turbine according to the pressure drop ratio and the volume and weight limit allocated to the exhaust gas turbine by the aircraft, and determining the operating speed of the exhaust gas turbine at the cruising altitude according to the type and size of the exhaust gas turbine; Step 1.1.2, determining a three-dimensional model of the exhaust gas turbine according to the type, size and operating speed of the exhaust gas turbine at a cruising altitude, and performing a three-dimensional flow field simulation on the three-dimensional model of the exhaust gas turbine to obtain a simulation result of the exhaust gas turbine; Step 1.1.3, determine whether the simulation result of the exhaust gas turbine meets the preset conditions. If so, determine the current speed and torque of the exhaust gas turbine as the hardware parameters of the exhaust gas turbine; if not, modify the size and operating speed of the exhaust gas turbine, and jump to step 1.1.2 to continue execution.

9. The system according to claim 8, characterized in that The process of the simulation device determining the hardware parameters of the generator at the cruising altitude is as follows: Step 1.2.1, determining the type, main dimensions, and winding parameters of the generator based on the finally determined speed and torque of the exhaust gas turbine, the load power demand, and the volume and weight of the aircraft allocated to the generator; Step 1.2.2, determining a three-dimensional model of the generator according to the type, main dimensions, and winding parameters of the generator, and performing a three-dimensional electric-thermal joint simulation on the three-dimensional model of the generator to obtain a generator simulation result; Step 1.2.3, if the simulation result of the generator meets the volume and weight requirements assigned to the generator by the aircraft and can meet the power demand of the load end, the current power generation parameters of the generator are determined as the hardware parameters of the generator; if the simulation result of the generator does not meet the volume and weight requirements assigned to the generator by the aircraft and can meet the power demand of the load end, the main dimensions and winding parameters of the generator are modified, and jump to step 1.2.2 to continue execution.

10. The system according to claim 9, characterized in that The process of the simulation device determining the hardware parameters of the power transmission and distribution device at the cruising altitude is as follows: Step 1.3.1, determining the basic architecture and controller type of the power transmission and distribution device according to the power generation parameters of the generator and the power demand of each power-consuming device; Step 1.3.2, at a cruising altitude, performing a semi-physical field simulation according to the basic architecture and controller type of the power transmission and distribution device to obtain a simulation result of the power transmission and distribution device; Step 1.3.3, based on the simulation results of the power transmission and distribution device, verify whether the power transmission and distribution device can meet the aircraft's needs for power distribution at cruising altitude. If it can, output the power transmission and distribution device hardware and power transmission and distribution logic; if it cannot meet the aircraft's needs for power distribution at cruising altitude, optimize the design of the power transmission and distribution device by adjusting the control logic, and jump to step 1.3.2 to continue execution.

11. The system according to claim 7, characterized in that The simulation device is specifically used for: Step 2.1, obtaining the speed and torque of the exhaust gas turbine at different flight altitudes; Step 2.2, using the exhaust gas turbine speed and torque obtained in step 2.1 to simulate the generator, and obtaining the power generation parameters of the generator at different flight altitudes; Step 2.3, according to the power generation parameters of the generator at different aircraft flight altitudes, and the power requirements of the fuel cell cooling module and the reaction gas heating and boosting module at different aircraft flight altitudes, design a rectifier device and related control logic in the power transmission and distribution device, and perform performance verification through semi-physical field simulation. If the requirements are met, output the hardware parameters and power transmission and distribution logic of the power transmission and distribution device.

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