Liquid hydrogen gasification heat exchange system of hydrogen energy aircraft

Abstract

The utility model provides a liquid hydrogen gasification heat exchange system of a hydrogen energy aircraft, relates to the technical field of hydrogen fuel transmission, and is used for realizing conversion from liquid hydrogen to gas hydrogen of the hydrogen energy aircraft. The system comprises a liquid hydrogen storage tank, a comprehensive controller, a first liquid hydrogen gasification device, a second liquid hydrogen gasification device and a hydrogen engine, the output end of the liquid hydrogen storage tank is connected with the input end of the first liquid hydrogen gasification device, and the output end of the first liquid hydrogen gasification device is connected with the input end of the hydrogen engine, so that gas hydrogen generated by the first liquid hydrogen gasification device is supplied to the hydrogen engine; liquid hydrogen required to be used is stored in the liquid hydrogen storage tank; the output end of the first liquid hydrogen gasification device is connected with the input end of the second liquid hydrogen gasification device through a bypass valve, and the output end of the second liquid hydrogen gasification device is connected with the input end of the hydrogen engine; the comprehensive controller is connected with the first liquid hydrogen gasification device and the bypass valve and used for controlling the first liquid hydrogen gasification device to convert input liquid hydrogen into gas hydrogen and controlling opening and closing of the bypass valve.

Description

Technical Field

[0001] This application relates to the field of hydrogen fuel transport technology, and in particular to a liquid hydrogen vaporization heat exchange system for hydrogen-powered aircraft. Background Technology

[0002] Liquid hydrogen fuel has a higher energy density and is more environmentally friendly than fuel oil, leading domestic and international companies and research institutions to invest more resources in developing hydrogen-powered aircraft. Liquid hydrogen has a storage temperature of approximately -252.8℃, a density of approximately 70.8 kg / m³ at this temperature, and a storage pressure of approximately 3 MPa. Since hydrogen turbine engines, as the power source for hydrogen-powered aircraft, can only use gaseous hydrogen as fuel, a hydrogen supply system is needed to convert liquid hydrogen into gaseous hydrogen. Because liquid hydrogen has a large amount of cooling capacity, this cooling capacity can be extracted to provide heat dissipation for thermal equipment in civil aircraft, while simultaneously reducing the energy consumption of electric heating.

[0003] Because hydrogen-powered aircraft are a relatively new technological field, there are few related patents in the aviation sector. However, in the field of hydrogen-powered vehicles, there are some related technical solutions and methods both domestically and internationally. The principle involves using a fuel exchange module (FCE) to extract heat from the atmosphere to heat liquid hydrogen. However, for civilian aircraft, the atmospheric temperature at high altitudes is too low (approximately -50°C at a cruising altitude of 40,000 ft), and extracting heat from the atmosphere would also result in significant fuel loss. Therefore, the method of extracting heat from the atmosphere is not suitable for hydrogen-powered aircraft. Utility Model Content

[0004] This application provides a liquid hydrogen vaporization heat exchange system for hydrogen-powered aircraft, used to realize the conversion of liquid hydrogen to gaseous hydrogen in hydrogen-powered aircraft.

[0005] This utility model provides a liquid hydrogen vaporization heat exchange system for a hydrogen-powered aircraft. The system includes: a liquid hydrogen storage tank, a comprehensive controller, a first liquid hydrogen vaporization device, a second liquid hydrogen vaporization device, and a hydrogen engine.

[0006] The output end of the liquid hydrogen storage tank is connected to the input end of the first liquid hydrogen vaporization device, and the output end of the first liquid hydrogen vaporization device is connected to the input end of the hydrogen engine, so that the gaseous hydrogen generated by the first liquid hydrogen vaporization device is supplied to the hydrogen engine; the liquid hydrogen storage tank stores the liquid hydrogen that needs to be used.

[0007] The output of the first liquid hydrogen vaporization device is connected to the input of the second liquid hydrogen vaporization device via a bypass valve, and the output of the second liquid hydrogen vaporization device is connected to the input of the hydrogen engine.

[0008] The integrated controller is connected to the first liquid hydrogen vaporization device and the bypass valve, and is used to control the first liquid hydrogen vaporization device to convert the input liquid hydrogen into gaseous hydrogen, and to control the opening and closing of the bypass valve.

[0009] In an optional embodiment, the first liquid hydrogen vaporization device includes: an electric heater and a liquid-cooled heat exchanger, wherein the electric heater and the liquid-cooled heat exchanger are connected in series;

[0010] The output end of the liquid hydrogen storage tank is connected to the input end of the electric heater. The electric heater is powered by a power system to heat the liquid hydrogen flowing into the liquid hydrogen storage tank and increase the temperature of the liquid hydrogen.

[0011] The output end of the electric heater is connected to the input end of the liquid-cooled heat exchanger, and the liquid-cooled heat exchanger exchanges heat with the liquid hydrogen flowing into the electric heater to obtain the physical properties of the hydrogen.

[0012] In an optional embodiment, the first liquid hydrogen vaporization device further includes: an airborne system heat carrier and an electric pump, wherein the cooling medium of the airborne system heat carrier introduces heat to the liquid-cooled heat exchanger through the electric pump, providing thermal energy for the heated liquid hydrogen flowing into the liquid-cooled heat exchanger to obtain the physical properties of hydrogen.

[0013] In an optional embodiment, one end of the integrated controller is connected to the electric pump for controlling the operation of the electric pump.

[0014] In an optional embodiment, the system further includes a temperature sensor and a pressure sensor disposed between the check valve and the hydrogen engine;

[0015] The integrated controller is connected to the temperature sensor, the pressure sensor, and the electric pump to acquire temperature and pressure data, and to control the operation of the electric pump based on the pressure and temperature data.

[0016] In an optional embodiment, the system further includes a check valve disposed between the liquid-cooled heat exchanger and the hydrogen engine.

[0017] In an optional embodiment, the system further includes a temperature sensor and a pressure sensor disposed between the check valve and the hydrogen engine;

[0018] The integrated controller is connected to the temperature sensor and the pressure sensor to acquire temperature and pressure data, determine the physical properties of hydrogen based on the pressure and temperature data, and control the opening and closing of the bypass valve based on the physical properties of hydrogen.

[0019] In an optional embodiment, the second liquid hydrogen vaporization device is a gas heat exchanger;

[0020] If the physical state of the hydrogen is hydrogen gas, then the bypass valve is closed so that the hydrogen gas output from the liquid-cooled heat exchanger is supplied to the hydrogen engine.

[0021] If the hydrogen is in liquid state, the bypass valve is opened, allowing the liquid hydrogen output from the liquid-cooled heat exchanger to flow into the gas heat exchanger through the opened bypass valve. The gas heat exchanger heats the flowing liquid hydrogen to produce hydrogen gas, which is then input into the hydrogen engine through the output end of the gas heat exchanger.

[0022] In an optional embodiment, one end of the integrated controller is connected to the electric heater for controlling the operation of the electric heater.

[0023] In an optional embodiment, the system further includes: a total flow control valve;

[0024] One end of the integrated controller is connected to the total flow control valve and is used to control the opening and closing of the total flow control valve to regulate the flow rate of liquid hydrogen into the electric heater.

[0025] In an optional embodiment, the integrated controller is further configured to control the opening degree of the bypass valve and the heating power of the electric heater based on the gas temperature of the hydrogen engine.

[0026] This invention provides a liquid hydrogen vaporization heat exchange system for a hydrogen-powered aircraft. The system includes a liquid hydrogen storage tank, a comprehensive controller, a first liquid hydrogen vaporization device, a second liquid hydrogen vaporization device, and a hydrogen engine. The output of the liquid hydrogen storage tank is connected to the input of the first liquid hydrogen vaporization device, and the output of the first liquid hydrogen vaporization device is connected to the input of the hydrogen engine, allowing the gaseous hydrogen produced by the first liquid hydrogen vaporization device to be supplied to the hydrogen engine. The liquid hydrogen storage tank stores the required liquid hydrogen. The output of the first liquid hydrogen vaporization device is connected to the input of the second liquid hydrogen vaporization device via a bypass valve, and the output of the second liquid hydrogen vaporization device is connected to the input of the hydrogen engine. The comprehensive controller is connected to the first liquid hydrogen vaporization device and the bypass valve, and is used to control the conversion of the input liquid hydrogen into gaseous hydrogen by the first liquid hydrogen vaporization device, and the opening and closing of the bypass valve. Thus, this application uses the first and second liquid hydrogen vaporization devices to convert the liquid hydrogen output from the liquid hydrogen storage tank into gaseous hydrogen, and extracts a certain amount of cooling energy to dissipate heat from the aircraft's thermal load through the second liquid hydrogen vaporization device. Attached Figure Description

[0027] Figure 1 This application provides a structural diagram of a hydrogen-powered aircraft liquid hydrogen vaporization heat exchange system. Detailed Implementation

[0028] 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.

[0029] Please see Figure 1 This utility model provides a liquid hydrogen vaporization heat exchange system for a hydrogen-powered aircraft. The system includes: a liquid hydrogen storage tank 1, a comprehensive controller 2, a first liquid hydrogen vaporization device 3, a second liquid hydrogen vaporization device 4, and a hydrogen engine 5. The liquid hydrogen storage tank 1 stores the liquid hydrogen to be used, i.e., liquid hydrogen that needs to be converted into gaseous hydrogen. The second liquid hydrogen vaporization device 4 can be a gas heat exchanger.

[0030] The output end of the liquid hydrogen storage tank 1 is connected to the input end of the first liquid hydrogen vaporization device 3, and the output end of the first liquid hydrogen vaporization device 3 is connected to the input end of the hydrogen engine 5, so that the gaseous hydrogen generated by the first liquid hydrogen vaporization device 1 is supplied to the hydrogen engine 5.

[0031] The output end of the first liquid hydrogen vaporization device 3 is connected to the input end of the second liquid hydrogen vaporization device 4 through a bypass valve 6, and the output end of the second liquid hydrogen vaporization device 4 is connected to the input end of the hydrogen engine 5.

[0032] The integrated controller 2 is connected to the first liquid hydrogen vaporization device 3 and the bypass valve 6, and is used to control the first liquid hydrogen vaporization device 3 to convert the input liquid hydrogen into gaseous hydrogen, and to control the opening and closing of the bypass valve 6. By adjusting the opening degree, the bypass valve 6 allows the hydrogen that has passed through the electric heater 31 and the liquid-cooled heat exchanger 32 to be vaporized by exchanging heat with the gas heat exchanger as needed, and then supplied to the hydrogen engine 5.

[0033] In an optional embodiment, the first liquid hydrogen vaporization device 3 includes: an electric heater 31 and a liquid-cooled heat exchanger 32, wherein the electric heater 31 and the liquid-cooled heat exchanger 32 are connected in series.

[0034] The output end of the liquid hydrogen storage tank 1 is connected to the input end of the electric heater 31. The electric heater 31 is powered by a power system to heat the liquid hydrogen flowing into the liquid hydrogen storage tank 1 and increase its temperature. The output end of the electric heater 31 is connected to the input end of the liquid-cooled heat exchanger 32. The liquid-cooled heat exchanger 32 exchanges heat with the liquid hydrogen flowing into the electric heater 31 to obtain the physical properties of the hydrogen.

[0035] In an optional embodiment, the first liquid hydrogen vaporization device 3 further includes: an airborne system heat load 33 and an electric pump 34. The cooling medium of the airborne system heat load 33 introduces heat into the liquid-cooled heat exchanger 32 through the electric pump 34, providing thermal energy for the heated liquid hydrogen flowing into the liquid-cooled heat exchanger 32 to obtain the physical properties of hydrogen.

[0036] In an optional embodiment, the system further includes a check valve 7 disposed between the liquid-cooled heat exchanger 32 and the hydrogen engine 5, the check valve 7 being provided to prevent hydrogen backflow.

[0037] In an optional embodiment, the system further includes a temperature sensor and a pressure sensor disposed between the check valve 7 and the hydrogen engine 5; the integrated controller 2 is connected 34 to the temperature sensor, the pressure sensor and the electric pump to acquire temperature data and pressure data, and to control the operation of the electric pump based on the pressure data and the temperature data.

[0038] In an optional embodiment, the system further includes a temperature sensor and a pressure sensor disposed between the check valve 7 and the hydrogen engine; the integrated controller 2 is connected to the temperature sensor and the pressure sensor to acquire temperature data and pressure data, and to determine the physical properties of hydrogen based on the pressure data and the temperature data, and to control the opening and closing of the bypass valve 6 based on the physical properties of hydrogen.

[0039] In this embodiment, the integrated controller 2 determines the physical state of hydrogen using pressure and temperature data. Specifically, when the pressure is less than or equal to 1.297 MPa and the temperature is greater than 33.3 K, hydrogen is determined to be in a gaseous state (hydrogen gas). If the physical state of hydrogen is hydrogen gas, the bypass valve 6 is closed, allowing the hydrogen gas output from the liquid-cooled heat exchanger 32 to be supplied to the hydrogen engine 5. If the physical state of hydrogen is liquid hydrogen, the bypass valve 6 is opened, allowing the liquid hydrogen output from the liquid-cooled heat exchanger 32 to flow into the gas heat exchanger 4 through the open bypass valve 6. The gas heat exchanger 4 heats the flowing liquid hydrogen to obtain hydrogen gas, which is then input into the hydrogen engine 5 through the output terminal of the gas heat exchanger 4.

[0040] In an optional embodiment, one end of the integrated controller 2 is connected to the electric pump 34 for controlling the operation of the electric pump 34; the other end of the integrated controller 2 is also connected to the electric heater 31 for controlling the operation of the electric heater 31.

[0041] In an optional embodiment, the system further includes: a total flow control valve 8; one end of the integrated controller 2 is connected to the total flow control valve 6 and is used to control the opening and closing of the total flow control valve 8 to regulate the flow rate of liquid hydrogen into the electric heater 31.

[0042] It should be noted that in this embodiment, when the hydrogen engine 5 starts, the heat of the outside air needs to be taken into account, and the heating power of the electric heater 31 needs to be controlled. Through the heating power of the electric heater 31, the liquid hydrogen is converted into gaseous hydrogen and the hydrogen engine 5 is successfully started. After the hydrogen engine 5 starts successfully, if the gas temperature after the hydrogen engine 5 starts is high enough, the integrated controller needs to control the opening of the bypass valve 6, thereby controlling the flow rate of liquid hydrogen through the gas heat exchanger 4, so as to realize the cooling of the aircraft's heat load by the liquid hydrogen in the gas heat exchanger 4. At the same time, combined with the heat power of the airborne system, the power of the electric heater 31 is reduced as much as possible or even the electric heater 31 is turned off, so as to achieve the energy optimization of the liquid hydrogen vaporization system.

[0043] In this embodiment, the heating power of the electric heater 31 required to convert a certain mass flow rate of liquid hydrogen into gaseous hydrogen is assumed to be P (its value varies depending on the engine status), the effective heat power transmitted from the airborne system to the liquid-cooled heat exchanger 32 is Pj (a constant value kW), the power of the electric heater 31 is Pe, and the effective heat power of the gas heat exchanger 4 is Pg (its range is 0 kW to a constant value kW, affected by the heat exchange efficiency). The heating power is then calculated using the formula P = Pj + Pe + Pg.

[0044] Throughout the entire flight phase, Pj is generally a constant value, meaning Pj is a constant. Therefore, the specific bypass valve opening issue is P0 = (P - Pj) = Pe + Pg. Here, P0 is the total thermal power required by the engine under different conditions, which is the effective thermal power of the liquid-cooled heat exchanger 32.

[0045] The energy optimization problem of the liquid hydrogen vaporization system is actually the problem of starting the hydrogen engine 5 with the minimum opening of the bypass valve 6 - State 1; and the problem of extracting Pg heat power after the hydrogen engine 5 starts - State 2.

[0046] Therefore, energy optimization is simplified to P0{state 1} = Pe{electric heating power required by electric heater 31 under state 1} + Pg{heat power of air heat exchange in the initial state---constant value}; thus, under P0{state 1}, the bypass valve 6 is at a certain constant opening, causing the engine to start, and this part of the energy cannot be optimized; after the engine starts, until the aircraft is in the full state from takeoff to landing and the engine stops (state 2); P0{state 2} = Pe{state 2} + Pg{actual heat exchange power of gas heat exchanger under state 2}; when Pg{maximum heat exchange power of gas heat exchanger under state 2} ≥ P0{state 2}, the bypass valve is fully open, and Pe{state 2} = 0 kW; when Pg{maximum heat exchange power of gas heat exchanger under state 2} < P0{state 2}, Pe{state 2} = P0{state 2} - Pg{actual heat exchange power of gas heat exchanger under state 2}, the bypass valve is fully open. In this way, the energy utilization of the engine is optimized throughout the entire flight (total power consumption is minimized).

[0047] This embodiment provides a liquid hydrogen vaporization heat exchange system for a hydrogen-powered aircraft. The system includes a liquid hydrogen storage tank, a comprehensive controller, a first liquid hydrogen vaporization device, a second liquid hydrogen vaporization device, and a hydrogen engine. The output of the liquid hydrogen storage tank is connected to the input of the first liquid hydrogen vaporization device, and the output of the first liquid hydrogen vaporization device is connected to the input of the hydrogen engine, allowing the gaseous hydrogen produced by the first liquid hydrogen vaporization device to be supplied to the hydrogen engine. The liquid hydrogen storage tank stores the required liquid hydrogen. The output of the first liquid hydrogen vaporization device is connected to the input of the second liquid hydrogen vaporization device via a bypass valve, and the output of the second liquid hydrogen vaporization device is connected to the input of the hydrogen engine. The comprehensive controller is connected to the first liquid hydrogen vaporization device and the bypass valve, and is used to control the conversion of the input liquid hydrogen into gaseous hydrogen by the first liquid hydrogen vaporization device, and the opening and closing of the bypass valve. Therefore, this application uses the first and second liquid hydrogen vaporization devices to convert the liquid hydrogen output from the liquid hydrogen storage tank into gaseous hydrogen, and extracts a certain amount of cooling energy to dissipate heat from the aircraft's thermal load through the second liquid hydrogen vaporization device.

[0048] 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, and when executed, it 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 can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various 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 RAMbus dynamic RAM (RDRAM), etc.

[0049] 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.

[0050] 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. A hydrogen-powered aircraft liquid hydrogen vaporization heat exchange system, characterized in that, The system includes: a liquid hydrogen storage tank, a comprehensive controller, a first liquid hydrogen vaporization unit, a second liquid hydrogen vaporization unit, and a hydrogen engine; The output end of the liquid hydrogen storage tank is connected to the input end of the first liquid hydrogen vaporization device, and the output end of the first liquid hydrogen vaporization device is connected to the input end of the hydrogen engine, so that the gaseous hydrogen generated by the first liquid hydrogen vaporization device is supplied to the hydrogen engine; the liquid hydrogen storage tank stores the liquid hydrogen that needs to be used. The output of the first liquid hydrogen vaporization device is connected to the input of the second liquid hydrogen vaporization device via a bypass valve, and the output of the second liquid hydrogen vaporization device is connected to the input of the hydrogen engine. The integrated controller is connected to the first liquid hydrogen vaporization device and the bypass valve, and is used to control the first liquid hydrogen vaporization device to convert the input liquid hydrogen into gaseous hydrogen, and to control the opening and closing of the bypass valve.

2. The system according to claim 1, characterized in that, The first liquid hydrogen vaporization device includes: an electric heater and a liquid-cooled heat exchanger, wherein the electric heater and the liquid-cooled heat exchanger are connected in series; The output end of the liquid hydrogen storage tank is connected to the input end of the electric heater. The electric heater is powered by a power system to heat the liquid hydrogen flowing into the liquid hydrogen storage tank and increase the temperature of the liquid hydrogen. The output end of the electric heater is connected to the input end of the liquid-cooled heat exchanger, and the liquid-cooled heat exchanger exchanges heat with the liquid hydrogen flowing into the electric heater to obtain the physical properties of the hydrogen.

3. The system according to claim 2, characterized in that, The first liquid hydrogen vaporization device further includes: an airborne system heat carrier and an electric pump. The cooling medium of the airborne system heat carrier introduces heat into the liquid-cooled heat exchanger through the electric pump, providing thermal energy for the heated liquid hydrogen flowing into the liquid-cooled heat exchanger to obtain the physical properties of hydrogen.

4. The system according to claim 3, characterized in that, One end of the integrated controller is connected to the electric pump and is used to control the operation of the electric pump.

5. The system according to claim 4, characterized in that, The system also includes a check valve disposed between the liquid-cooled heat exchanger and the hydrogen engine.

6. The system according to claim 5, characterized in that, The system also includes a temperature sensor and a pressure sensor disposed between the check valve and the hydrogen engine; The integrated controller is connected to the temperature sensor, the pressure sensor, and the electric pump to acquire temperature and pressure data, and to control the operation of the electric pump based on the pressure and temperature data.

7. The system according to claim 6, characterized in that, The integrated controller is connected to the temperature sensor and the pressure sensor to acquire temperature and pressure data, determine the physical properties of hydrogen based on the pressure and temperature data, and control the opening and closing of the bypass valve based on the physical properties of hydrogen.

8. The system according to claim 7, characterized in that, The second liquid hydrogen vaporization device is a gas heat exchanger; If the physical state of the hydrogen is hydrogen gas, then the bypass valve is closed so that the hydrogen gas output from the liquid-cooled heat exchanger is supplied to the hydrogen engine. If the hydrogen is in liquid state, the bypass valve is opened, allowing the liquid hydrogen output from the liquid-cooled heat exchanger to flow into the gas heat exchanger through the opened bypass valve. The gas heat exchanger heats the flowing liquid hydrogen to produce hydrogen gas, which is then input into the hydrogen engine through the output end of the gas heat exchanger.

9. The system according to claim 2, characterized in that, The system further includes: a total flow control valve; one end of the integrated controller is connected to the electric heater for controlling the operation of the electric heater; one end of the integrated controller is connected to the total flow control valve for controlling the opening and closing of the total flow control valve to regulate the flow rate of liquid hydrogen into the electric heater.

10. The system according to claim 2, characterized in that, The integrated controller is also used to control the opening degree of the bypass valve and the heating power of the electric heater based on the gas temperature of the hydrogen engine.

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