An aviation high-temperature hydrogen fuel cell energy recycling system
By designing an energy recovery and utilization system for high-temperature hydrogen fuel cells in aviation, which uses exhaust gas turbines and generators to generate electricity, the problem of low energy recovery efficiency in existing technologies has been solved, and efficient energy utilization and power distribution have been achieved.
Patent Information
- Application Number
- CN202520499765.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-20
- Publication Date
- 2026-08-25
- Estimated Expiration
- 2035-03-20
AI Technical Summary
Existing hydrogen fuel cell energy recovery solutions in the aviation field are limited by the small pressure difference between the reaction exhaust gas and the atmospheric environment, resulting in low energy recovery efficiency.
Design an aviation high-temperature hydrogen fuel cell energy recovery and utilization system, including a reaction exhaust gas power generation module, a reaction gas heating and pressurization module, and a high-temperature hydrogen fuel cell. The system generates electrical energy through an exhaust gas turbine and a generator, and uses a simulation device to optimize hardware parameters to improve energy utilization efficiency.
This technology enables efficient power generation from the exhaust gas of high-temperature hydrogen fuel cells, improving energy utilization efficiency and meeting the power distribution needs of aircraft at different flight altitudes.
Smart Images
Figure CN224683107U_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of energy recovery technology, and in particular to an energy recovery and utilization system for high-temperature hydrogen fuel cells used in aviation. Background Technology
[0002] Hydrogen fuel cells are clean power devices with high energy density and have enormous potential applications in the aviation industry. Current energy recovery methods for hydrogen fuel cells primarily involve collecting heat from reaction waste liquids or gases using heat exchangers, and then recovering this energy through combined heat and power (CHP), reforming to produce hydrogen, or heating ammonia vapor to generate electricity.
[0003] Currently, energy recovery solutions for fuel cells are all based on ground-based equipment. Due to the small pressure difference between the reaction exhaust gas and the atmospheric environment, the energy recovery efficiency of fuel cell reaction exhaust gas / waste liquid is not high. Utility Model Content
[0004] This application provides an energy recovery and utilization system for high-temperature hydrogen fuel cells in aviation, which is used to recover the energy of fuel cell reaction waste gas / waste liquid, thereby effectively improving the energy utilization efficiency of high-temperature fuel cells.
[0005] This utility model provides an energy recovery and utilization system for a high-temperature hydrogen fuel cell in aviation. The system includes: a reaction exhaust gas power generation module, a reaction gas heating and pressurization 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 pressurization module respectively.
[0006] The reaction gas heating and pressurization module is used to provide air and gaseous hydrogen for the high-temperature hydrogen fuel cell;
[0007] The high-temperature hydrogen fuel cell generates reaction waste gas based on the air and gaseous hydrogen provided by the reaction gas heating and pressurization module.
[0008] The reaction waste gas power generation module is used to recover the high-temperature and high-pressure waste gas generated by the high-temperature hydrogen fuel cell, generate electricity based on the high-temperature and high-pressure waste gas, and supply power to the reaction gas heating and pressurization module.
[0009] In an optional embodiment, the system further includes a fuel cell cooling module connected to the high-temperature hydrogen fuel cell;
[0010] The fuel cell cooling module is used to provide coolant or cooling gas to the fuel cell cooling module.
[0011] In an optional embodiment, the system further includes: a power transmission and distribution device and an aircraft power transmission and distribution network; the power transmission and distribution device is connected to the aircraft power transmission and distribution network, the reaction exhaust gas power generation module, the reaction gas heating and pressurization module, and the fuel cell cooling module, respectively.
[0012] The power transmission and distribution device is used to receive electrical energy from the reaction waste 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 includes: an avionics network;
[0014] The avionics network is connected to the fuel cell cooling module, the reaction gas heating and pressurization module, and the aircraft power transmission and distribution network, respectively, and is used to provide flight altitude data to the fuel cell cooling module, the reaction gas heating and pressurization 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 and a generator;
[0016] The exhaust gas turbine is used to collect the reaction exhaust gas from the high-temperature fuel cell, and the exhaust gas turbine drives the coaxially connected generator to generate electricity.
[0017] In an optional embodiment, the reaction gas heating and pressurization 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 supply 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 to deliver the gaseous hydrogen to the high-temperature hydrogen fuel cell.
[0020] The air compressor is used to draw air and deliver the drawn air to the high-temperature hydrogen fuel cell.
[0021] In an optional embodiment, the system further includes: a simulation device;
[0022] The simulation device is used to determine the hardware parameters of the exhaust 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 turbine, the generator, and the power transmission and distribution device, respectively, to obtain the power transmission and distribution parameters corresponding to the power transmission and distribution device at different aircraft flight altitudes.
[0024] In an optional embodiment, the process by which the simulation device determines the hardware parameters of the exhaust turbine at cruising altitude is as follows:
[0025] Step 1.1.1: Determine the pressure drop ratio of the exhaust gas turbine at the aircraft's cruising altitude based on the outlet exhaust gas pressure of the high-temperature hydrogen fuel cell and the atmospheric pressure at the cruising altitude; determine the type and size of the exhaust gas turbine based on the pressure drop ratio and the volume and weight restrictions allocated to the exhaust gas turbine by the aircraft; and determine the operating speed of the exhaust gas turbine at the cruising altitude based on the type and size of the exhaust gas turbine.
[0026] Step 1.1.2: Determine the three-dimensional model of the exhaust gas turbine based on the type, size, and operating speed of the exhaust gas turbine at the cruising altitude, and perform three-dimensional flow field simulation on the three-dimensional model of the exhaust gas turbine to obtain the simulation results of the exhaust gas turbine.
[0027] Step 1.1.3: Determine whether the simulation results of the exhaust gas turbine meet the preset conditions. If the preset conditions are met, the current speed and torque of the exhaust gas turbine are determined as the hardware parameters of the exhaust gas turbine. If the preset conditions are not met, the size and operating speed of the exhaust gas turbine are modified, and the process jumps to step 1.1.2 to continue execution.
[0028] In an optional embodiment, the process by which the simulation device determines the hardware parameters of the generator at the cruising altitude is as follows:
[0029] Step 1.2.1: Based on the finally determined speed and torque of the exhaust turbine, the load power demand, and the volume and weight allocated to the generator by the aircraft, determine the type, main dimensions, and winding parameters of the generator;
[0030] Step 1.2.2: Determine the three-dimensional model of the generator based on its type, main dimensions, and winding parameters, and perform a three-dimensional electrothermal co-simulation on the generator model to obtain the generator simulation results;
[0031] Step 1.2.3: If the generator simulation results meet the volume and weight requirements allocated to the generator by the aircraft and can meet the power demand of the load, then the current generator power generation parameters are determined as the generator hardware parameters; if the generator simulation results do not meet the volume and weight requirements allocated to the generator by the aircraft and can meet the power demand of the load, then the main dimensions and winding parameters of the generator are modified, and the process jumps to step 1.2.2 to continue execution.
[0032] In an optional embodiment, the process by which the simulation device determines the hardware parameters of the power transmission and distribution equipment at the cruising altitude is as follows:
[0033] Step 1.3.1: Determine the basic architecture and controller type of the power transmission and distribution device based on the power generation parameters of the generator and the power consumption requirements of each electrical device;
[0034] Step 1.3.2: At the cruising altitude, perform a semi-physical field simulation based on the basic architecture and controller type of the power transmission and distribution device to obtain the simulation results 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 power distribution needs of the aircraft 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 power distribution needs of the aircraft 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 apparatus is specifically used for:
[0037] Step 2.1: Obtain the rotational speed and torque of the exhaust turbine at different flight altitudes;
[0038] Step 2.2: Simulate the generator using the exhaust turbine speed and torque obtained in Step 2.1 to obtain the generator's power generation parameters at different flight altitudes;
[0039] Step 2.3: Based on the power generation parameters of the generator at different aircraft flight altitudes, and the power consumption requirements of the fuel cell cooling module and the reaction gas heating and pressurization module at different aircraft flight altitudes, design the rectifier and related control logic in the power transmission and distribution device, and verify the performance 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] This invention provides an energy recovery and utilization system for a high-temperature hydrogen fuel cell in aviation. The system includes: a reaction exhaust gas power generation module, a reaction gas heating and pressurization module, and a high-temperature hydrogen fuel cell. The high-temperature hydrogen fuel cell is connected to both the reaction exhaust gas power generation module and the reaction gas heating and pressurization module. The reaction gas heating and pressurization module provides air and gaseous hydrogen to the high-temperature hydrogen fuel cell; the high-temperature hydrogen fuel cell generates reaction exhaust gas based on the air and gaseous hydrogen provided by the reaction gas heating and pressurization module; the reaction exhaust gas power generation module recovers the high-temperature, high-pressure exhaust gas generated by the high-temperature hydrogen fuel cell, generates electricity from the high-temperature, high-pressure exhaust gas, and supplies power to the reaction gas heating and pressurization module. Thus, this application realizes the generation of electricity from the reaction exhaust gas of the high-temperature hydrogen fuel cell, effectively improving the energy utilization efficiency of the high-temperature hydrogen fuel cell. Attached Figure Description
[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 flowchart of a simulation device execution method is provided in this application;
[0043] Figure 3 A flowchart of another simulation device execution method provided in this application. Detailed Implementation
[0044] To better understand the above technical solutions, the technical solutions of the embodiments of this application will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments of this application and the specific features in the embodiments are detailed descriptions of the technical solutions of the embodiments of this application, rather than limitations on the technical solutions of this application. In the absence of conflict, the embodiments of this application and the technical features in the embodiments can be combined with each other.
[0045] Please see Figure 1 This invention provides an aviation high-temperature hydrogen fuel cell energy recovery and utilization system, which includes: a reaction waste gas power generation module, a reaction gas heating and pressurization module, and a high-temperature hydrogen fuel cell.
[0046] Specific examples Figure 1 As shown, the high-temperature hydrogen fuel cell is connected to both the reaction exhaust gas power generation module and the reaction gas heating and pressurization module. The reaction gas heating and pressurization module provides air and gaseous hydrogen to the high-temperature hydrogen fuel cell; the high-temperature hydrogen fuel cell generates reaction exhaust gas based on the air and gaseous hydrogen provided by the reaction gas heating and pressurization module; the reaction exhaust gas power generation module recovers the high-temperature, high-pressure exhaust gas generated by the high-temperature hydrogen fuel cell, generates electricity from the high-temperature, high-pressure exhaust gas, and supplies power to the reaction gas heating and pressurization module. Thus, this application realizes the generation of electricity using the reaction exhaust gas of a 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 coolant or cooling gas to the fuel cell cooling module.
[0048] In an optional embodiment, the system further includes: a power transmission and distribution device and an aircraft power transmission and distribution network; the power transmission and distribution device is connected to the aircraft power transmission and distribution network, the reaction exhaust gas power generation module, the reaction gas heating and pressurization module, and the fuel cell cooling module, respectively; the power transmission and distribution device is used to receive electrical 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.
[0049] In an optional embodiment, the system further includes an avionics network; the avionics network is connected to the fuel cell cooling module, the reactant gas heating and pressurizing module, and the aircraft power transmission and distribution network respectively, and is used to provide flight altitude data to the fuel cell cooling module, the reactant gas heating and pressurizing 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, enabling the fuel cell cooling module to provide corresponding cooling functions to the high-temperature hydrogen fuel cell based on the altitude signal and the temperature signal provided by the high-temperature hydrogen fuel cell. For example, the operating power of the cooling device can be determined based on the specific altitude and temperature, thereby achieving effective cooling of the high-temperature hydrogen fuel cell based on altitude and temperature.
[0051] Specific examples 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 generate electricity. The reaction gas heating and pressurization 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 supply liquid nitrogen to the electric heating heat exchanger; the electric heating heat exchanger is used to heat the liquid nitrogen to generate gaseous hydrogen and supply the gaseous hydrogen to the high-temperature hydrogen fuel cell; the air compressor is used to draw air and supply the drawn air to the high-temperature hydrogen fuel cell.
[0052] In this embodiment, the high-temperature hydrogen fuel cell generates high-temperature, high-pressure exhaust gas during operation. This exhaust gas is collected by an exhaust turbine within the system. The turbine drives a coaxial generator to produce electricity, which is then transmitted and distributed to the fuel cell cooling module, the reaction heating and pressurization module, and the aircraft's power transmission and distribution network. Thus, this application achieves power generation using the reaction exhaust gas of the high-temperature hydrogen fuel cell, effectively improving the energy utilization efficiency of the high-temperature hydrogen fuel cell.
[0053] This utility model provides an energy recovery and utilization system for a high-temperature hydrogen fuel cell in aviation. The system includes: a reaction exhaust gas power generation module, a reaction gas heating and pressurization module, and a high-temperature hydrogen fuel cell. The high-temperature hydrogen fuel cell is connected to both the reaction exhaust gas power generation module and the reaction gas heating and pressurization module. The reaction gas heating and pressurization module provides air and gaseous hydrogen to the high-temperature hydrogen fuel cell; the high-temperature hydrogen fuel cell generates reaction exhaust gas based on the air and gaseous hydrogen provided by the reaction gas heating and pressurization module; the reaction exhaust gas power generation module recovers the high-temperature, high-pressure exhaust gas generated by the high-temperature hydrogen fuel cell, generates electricity from the high-temperature, high-pressure exhaust gas, and supplies power to the reaction gas heating and pressurization module. Thus, this application realizes the generation of electricity from the reaction exhaust gas of the high-temperature hydrogen fuel cell, effectively improving the energy utilization efficiency of the high-temperature hydrogen fuel cell.
[0054] like Figure 2 As shown, this application can determine the hardware parameters corresponding to the exhaust turbine, generator, and power transmission and distribution equipment 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 as follows:
[0055] Step 1: Determine the hardware parameters corresponding to the exhaust turbine, generator, and power transmission and distribution device at the cruising altitude.
[0056] like Figure 3 As shown, in an optional embodiment, the process by which the simulation device determines the hardware parameters of the exhaust turbine at cruising altitude is as follows:
[0057] Step 1.1.1: Determine the pressure drop ratio of the exhaust gas turbine at the aircraft's cruising altitude based on the outlet exhaust gas pressure of the high-temperature hydrogen fuel cell and the atmospheric pressure at the cruising altitude; determine the type and size of the exhaust gas turbine based on the pressure drop ratio and the volume and weight restrictions allocated to the exhaust gas turbine by the aircraft; and determine the operating speed of the exhaust gas turbine at the cruising altitude based on the type and size of the exhaust gas turbine.
[0058] Step 1.1.2: Determine the three-dimensional model of the exhaust gas turbine based on the type, size, and operating speed of the exhaust gas turbine at the cruising altitude, and perform three-dimensional flow field simulation on the three-dimensional model of the exhaust gas turbine to obtain the simulation results of the exhaust gas turbine.
[0059] In this embodiment, step 1.1.2 involves the design, modeling, and simulation of the exhaust gas turbine. Since the type of exhaust gas turbine and its approximate operating speed at the aircraft's cruising altitude were determined in step 1.1.1, a speed can be set first. Based on this, 3D design software can be used to determine the dimensions and 3D model of the exhaust gas turbine, and then the 3D model of the exhaust gas turbine can be used to perform 3D flow field simulation.
[0060] Step 1.1.3: Determine whether the simulation results of the exhaust gas turbine meet the preset conditions. If the preset conditions are met, the current speed and torque of the exhaust gas turbine are determined as the hardware parameters of the exhaust gas turbine. If the preset conditions are not met, the size and operating speed of the exhaust gas turbine are modified, and the process jumps to step 1.1.2 to continue execution.
[0061] In this embodiment, step 1.1.3 is an iterative optimization of the three-dimensional model of the exhaust turbine. The simulation results of the exhaust turbine in step 1.1.2 are analyzed. If the simulation results meet the design requirements, such as the pressure ratio and the weight and volume constraints allocated to the exhaust turbine by the aircraft, the three-dimensional model of the exhaust turbine, its rotational speed, and torque are output. If the simulation results do not meet the design requirements, the exhaust turbine model structure is optimized, such as by changing the blade angle, overall dimensions, and rotational speed to adjust the three-dimensional model, and the process jumps back to step 1.1.2 to continue execution. Finally, the three-dimensional model of the exhaust turbine and the design point rotational speed and torque of the exhaust turbine at the aircraft's cruising altitude are determined.
[0062] like Figure 3 As shown, in an optional embodiment, the process by which the simulation device determines the hardware parameters of the generator at the cruising altitude is as follows:
[0063] Step 1.2.1: Based on the finally determined speed and torque of the exhaust turbine, the load power demand, and the volume and weight allocated to the generator by the aircraft, determine the type, main dimensions, and winding parameters of 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: Determine the three-dimensional model of the generator based on its type, main dimensions, and winding parameters, and perform a three-dimensional electrothermal co-simulation on the generator model to obtain the generator simulation results;
[0066] Step 1.2.2 involves the design, modeling, and simulation of the generator. Since the generator type, main dimensions, and winding parameters were established in step 1.2.1, this embodiment can first select a parameter combination and use 3D design software to design a 3D model of the generator. Then, the 3D model of the generator can be used to perform a 3D electrothermal co-simulation to obtain the generator simulation results.
[0067] Step 1.2.3: If the generator simulation results meet the volume and weight requirements allocated to the generator by the aircraft and can meet the power demand of the load, then the current generator power generation parameters are determined as the generator hardware parameters; if the generator simulation results do not meet the volume and weight requirements allocated to the generator by the aircraft and can meet the power demand of the load, then the main dimensions and winding parameters of the generator are modified, and the process jumps to step 1.2.2 to continue execution.
[0068] Step 1.2.3 involves generator structure optimization. If the generator simulation results meet the volume and weight requirements allocated to the generator by the aircraft and satisfy the power demand of the load, then a 3D generator model is output. If these requirements are not met, the generator design is optimized, such as by changing winding parameters, overall dimensions, and resistance and reactance parameters to adjust the 3D generator model, and step 1.2.2 is repeated. Ultimately, step 1.2 determines the 3D generator model and power generation parameters under aircraft cruise conditions.
[0069] like Figure 3 As shown, in an optional embodiment, the process by which the simulation device determines the hardware parameters of the power transmission and distribution equipment at the cruising altitude is as follows:
[0070] Step 1.3.1: Determine the basic architecture and controller type of the power transmission and distribution device based on the power generation parameters of the generator and the power consumption requirements of each electrical device;
[0071] Step 1.3.2: At the cruising altitude, perform a semi-physical field simulation based on the basic architecture and controller type of the power transmission and distribution device to obtain the simulation results of the power transmission and distribution device;
[0072] Step 1.3.2 involves designing the power transmission and distribution logic and the hardware of the power transmission and distribution devices. During aircraft cruise, the power transmission and distribution system should prioritize supplying the generator's output to the high-temperature hydrogen fuel cell auxiliary systems (i.e., the reactant gas heating and pressurization module and the fuel cell cooling module). After meeting the power requirements of the high-temperature hydrogen fuel cell auxiliary systems, any excess power should be supplied to the aircraft's power transmission and distribution network. In this embodiment, after completing the power transmission and distribution device design, a semi-physical simulation is performed to obtain the simulation results, which will be used to verify the performance 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 power distribution needs of the aircraft 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 power distribution needs of the aircraft 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 involves optimizing the power transmission and distribution system. Using the semi-physics simulation in Step 1.3.2, the simulation results can be used to verify whether the power transmission and distribution system can meet the aircraft's power distribution needs during cruise. If it can, the hardware and logic of the power transmission and distribution system are output. If it cannot meet the aircraft's power distribution needs during cruise, the control logic is adjusted to optimize the design of the power transmission and distribution system, and Step 1.3.2 is repeated. Ultimately, Step 1.3.3 determines the power transmission and distribution logic and the hardware of the power transmission and distribution system.
[0075] Step 2: Perform semi-physical field simulation based on the hardware parameters corresponding to the exhaust turbine, the generator, and the power transmission and distribution device to 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 focus is on the design of the power transmission and distribution system based on the exhaust turbine speed at different aircraft flight altitudes. Since step 1 determines the three-dimensional model of the exhaust turbine, the pressure ratio between the high-temperature hydrogen fuel cell reaction exhaust gas and the atmospheric environment will change at different flight altitudes. This will cause changes in the exhaust turbine speed, resulting in fluctuations in the power generation parameters output by the generator. Therefore, it is necessary to optimize the rectification capability and power transmission and distribution control logic of the power transmission and distribution system.
[0077] Step 2.1: Obtain the rotational speed and torque of the exhaust turbine at different flight altitudes;
[0078] Step 2.2: Simulate the generator using the exhaust turbine speed and torque obtained in Step 2.1 to obtain the generator's power generation parameters at different flight altitudes;
[0079] In this embodiment, the first step is to obtain the speed and torque of the exhaust turbine at different aircraft flight altitudes according to step 2.1. The speed and torque of the exhaust turbine obtained in step 2.1 are then output to step 2.2 to simulate the generator, obtain the generator power generation parameters, and output them to step 2.3.
[0080] Step 2.3: Based on the power generation parameters of the generator at different aircraft flight altitudes, and the power consumption requirements of the fuel cell cooling module and the reaction gas heating and pressurization module at different aircraft flight altitudes, design the rectifier and related control logic in the power transmission and distribution device, and verify the performance 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 involves optimizing the power transmission and distribution system design at different aircraft flight altitudes. Step 2.2 provides the generator parameters at different flight altitudes. Combined with the power requirements of the hydrogen fuel cell auxiliary system at these altitudes, a rectifier and related control logic can be designed within the power transmission and distribution system. Performance verification is then performed using semi-physical simulation. If the requirements are met, the hardware parameters and power transmission and distribution logic are output. Ultimately, Step 2.3 determines the hardware of the power transmission and distribution system and the power transmission and distribution logic at different aircraft flight altitudes.
[0082] It should be understood that the sequence number of each step in the above embodiments does not imply 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 this utility model embodiment.
[0083] 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, storage, databases, or other media used in the embodiments provided in this application can 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 a variety of forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), RAMbus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).
[0084] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the above-described division of functional units and modules is used as an example. In practical applications, the above functions can be assigned to 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 this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model, and should all be included within the protection scope of this utility model.
Claims
1. An energy recovery and utilization system for high-temperature hydrogen fuel cells in aviation, characterized in that, The system includes: a reaction waste gas power generation module, a reaction gas heating and pressurization 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 pressurization module respectively; The reaction gas heating and pressurization module is used to provide air and gaseous hydrogen for the high-temperature hydrogen fuel cell; The high-temperature hydrogen fuel cell generates reaction waste gas based on the air and gaseous hydrogen provided by the reaction gas heating and pressurization module. The reaction waste gas power generation module is used to recover the high-temperature and high-pressure waste gas generated by the high-temperature hydrogen fuel cell, generate electricity based on the high-temperature and high-pressure waste gas, and supply power to the reaction gas heating and pressurization module.
2. The system according to claim 1, characterized in that, The system also includes a fuel cell cooling module connected to the high-temperature hydrogen fuel cell; The fuel cell cooling module is used to provide coolant or cooling gas to the fuel cell cooling module.
3. The system according to claim 2, characterized in that, The system also includes: a power transmission and distribution device and an aircraft power transmission and distribution network; the power transmission and distribution device is connected to the aircraft power transmission and distribution network, the reaction exhaust gas power generation module, the reaction gas heating and pressurization module, and the fuel cell cooling module, respectively; The power transmission and distribution device is used to receive electrical energy from the reaction waste 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: avionics network; The avionics network is connected to the fuel cell cooling module, the reaction gas heating and pressurization module, and the aircraft power transmission and distribution network, respectively, and is used to provide flight altitude data to the fuel cell cooling module, the reaction gas heating and pressurization module, and the aircraft power transmission and distribution network.
5. The system according to claim 4, characterized in that, The waste gas power generation module includes: a waste gas turbine and a generator; The exhaust gas turbine is used to collect the reaction exhaust gas from the high-temperature hydrogen fuel cell, and the exhaust gas turbine drives the coaxially connected generator to generate electricity.
6. The system according to any one of claims 1-4, characterized in that, The reaction gas heating and pressurization 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 supply 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 to deliver the gaseous hydrogen to the high-temperature hydrogen fuel cell. The air compressor is used to draw air and deliver the drawn air to the high-temperature hydrogen fuel cell.
7. The system according to claim 5, characterized in that, The system also includes: a simulation device; The simulation device is used to determine the hardware parameters of the exhaust 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 turbine, the generator, and the power transmission and distribution device, respectively, to obtain the power transmission and distribution parameters corresponding to the power transmission and distribution device at different aircraft flight altitudes.