Hydrogen fuel supply system

Abstract

This hydrogen fuel supply system is for an aircraft equipped with an engine and comprises: a fuel tank that stores hydrogen fuel in a liquid phase; a fuel supply path that connects the fuel tank to the engine; a pressure pump that is provided in the fuel supply path and that pressurizes the hydrogen fuel to a pressure equal to or higher than a critical pressure; and a sensor that is provided downstream of the pressure pump in the fuel supply path and that measures the pressure of the hydrogen fuel that has passed through the pressure pump.

Description

Hydrogen Fuel Supply System

[0001] The present disclosure relates to a hydrogen fuel supply system for an aircraft equipped with an engine.

[0002] Patent Document 1 discloses a hydrogen fuel supply system for aircraft, in which liquid hydrogen in a fuel tank is pressurized by a pump, heated by a heat exchanger, and supplied to the engine in a gaseous or supercritical phase.

[0003] US Patent Application Publication No. 2022 / 0145801

[0004] When hydrogen fuel changes from a liquid phase to a gas phase in the fuel supply passage during fuel supply, it experiences effects such as a large change in volume. If the hydrogen fuel is in a supercritical phase, the phase change from liquid to gas can be avoided, allowing hydrogen fuel to be supplied to the engine stably.

[0005] Hydrogen fuel can be put into the supercritical phase by pressurizing it above its critical pressure and then heating it above its critical temperature. This method of converting hydrogen fuel into the supercritical phase requires that the hydrogen fuel first be pressurized above its critical pressure.

[0006] One aspect of the present disclosure is directed to stabilizing the operation of an engine using hydrogen fuel in the supercritical phase.

[0007] A hydrogen fuel supply system according to one aspect of the present disclosure is a hydrogen fuel supply system for an aircraft equipped with an engine, and includes a fuel tank that stores hydrogen fuel in a liquid phase, a fuel supply line that connects the fuel tank to the engine, a pressure booster pump that is provided in the fuel supply line and pressurizes the hydrogen fuel to a pressure equal to or higher than the critical pressure, and a sensor that is provided in the fuel supply line downstream of the pressure booster pump and measures the pressure of the hydrogen fuel that has passed through the pressure booster pump.

[0008] According to one aspect of the present disclosure, when hydrogen fuel is pressurized to a pressure equal to or higher than the critical pressure by a pressure pump, the pressure of the hydrogen fuel can be measured by a sensor downstream of the pressure pump. This makes it possible to control the operation of the pressure pump according to the pressure of the hydrogen fuel, thereby stabilizing the operation of an engine that uses hydrogen fuel in a supercritical phase.

[0009] Fig. 1 is a plan view of an aircraft equipped with a hydrogen fuel supply system according to a first embodiment. Fig. 2 is a phase diagram showing the relationship between hydrogen phases and temperature-pressure. Fig. 3 is a block diagram of the hydrogen fuel supply system of Fig. 1. Fig. 4 is a block diagram of a hydrogen fuel supply system according to a second embodiment.

[0010] Hereinafter, embodiments will be described with reference to the drawings. In this disclosure, an aircraft refers to a device that can move in the air, such as a fixed-wing aircraft, a rotary-wing aircraft, or an unmanned flying object.

[0011] First Embodiment FIG. 1 is a plan view of an aircraft 1 equipped with a hydrogen fuel supply system 10 according to a first embodiment. As shown in FIG. 1 , the aircraft 1 includes, for example, a fuselage 2, main wings 3, a horizontal stabilizer 4, a vertical stabilizer 5, and a gas turbine engine 6. The fuselage 2 extends in the longitudinal direction of the aircraft 1 and defines a passenger space therein. The main wings 3 are connected to a central portion of the fuselage 2 in the longitudinal direction and protrude from the fuselage 2 in the lateral directions of the aircraft 1. The horizontal stabilizers 4 protrude from the rear of the fuselage 2 in the lateral directions of the aircraft 1. The vertical stabilizer 5 protrudes upward from the rear of the fuselage 2. The gas turbine engines 6 are connected to the pair of main wings 3. The fuselage 2, the main wings 3, and the gas turbine engine 6 are equipped with a hydrogen fuel supply system 10. A fuel tank 21 is disposed in the fuselage 2, but may also be disposed in the main wings 3. That is, all or part of the fuel tank 21 is disposed in the fuselage 2 or the main wings 3.

[0012] FIG. 2 is a phase diagram showing the relationship between hydrogen phases and temperature-pressure. As shown in FIG. 2, in the hydrogen phase diagram, the solid phase and gas phase are separated by a sublimation line L1, the solid phase and liquid phase are separated by a melting line L2, and the liquid phase and gas phase are separated by a boiling line L3. The intersection R of the sublimation line L1, melting line L2, and boiling line L3 is called the triple point. Hydrogen enters a supercritical phase when the pressure is higher than the critical pressure Pc and the temperature is higher than the critical temperature Tc. In the phase diagram, the point at the critical pressure Pc and critical temperature Tc is called the critical point Q. The critical pressure Pc is approximately 1.3 MPa, and the critical temperature Tc is approximately -240°C.

[0013] In this embodiment, the hydrogen fuel is prevented from changing from the liquid phase to the gas phase across the boiling line L3 in the phase diagram of Fig. 2. That is, the hydrogen fuel is pressurized so that the pressure of the hydrogen fuel in the liquid phase is equal to or higher than the critical pressure Pc, and then the hydrogen fuel is heated to a temperature equal to or higher than the critical temperature Tc, causing the hydrogen fuel to transition from the liquid phase to the supercritical phase.

[0014] To achieve the transition from the liquid phase to the supercritical phase, as shown in Fig. 3 (described later), the liquid phase hydrogen fuel flowing from the fuel tank 21 to the fuel supply line 22 is pressurized by the pressure pump 26 to a pressure equal to or higher than the critical pressure Pc. When the temperature of the hydrogen fuel flowing from the pressure pump 26 toward the gas turbine engine 6 is increased by a heat exchanger 28 or the like and reaches a temperature equal to or higher than the critical temperature Tc, the hydrogen fuel transitions from the liquid phase to the supercritical phase. This prevents the hydrogen fuel in the fuel supply line 22 from transitioning from the liquid phase to the gas phase, i.e., boiling.

[0015] Figure 3 is a block diagram of the hydrogen fuel supply system 10 of Figure 1. As shown in Figure 3, the hydrogen fuel supply system 10 includes a fuel tank 21. The fuel tank 21 stores hydrogen fuel in a liquid phase. The fuel tank 21 is connected to the gas turbine engine 6 by a fuel supply line 22. When the fuel tank 21 is disposed in the fuselage 2, the fuel supply line 22 extends from the fuselage 2 through the main wing 3 to the gas turbine engine 6. When the fuel tank 21 is disposed in the main wing 3, the fuel supply line 22 extends from the main wing 3 to the gas turbine engine 6. The gas turbine engine 6 includes a compressor 11, a combustor 12, and a turbine 13. The fuel supply line 22 is connected to the combustor 12.

[0016] A feed pump 23 is provided in the fuel supply path 22 to send hydrogen fuel from the fuel tank 21 to the fuel supply path 22. A shutoff valve 24 is provided in the fuel supply path 22 between the fuel tank 21 and the feed pump 23. A check valve 25 is provided in the fuel supply path 22 downstream of the feed pump 23.

[0017] A pressure booster pump 26 is provided in the fuel supply line 22 downstream of the check valve 25. The pressure booster pump 26 pressurizes the hydrogen fuel in the fuel supply line 22 to a pressure equal to or greater than the critical pressure Pc of hydrogen. For example, the pressure booster pump 26 pressurizes liquid-phase hydrogen fuel supplied from the fuel tank 21 so that the hydrogen fuel flowing through the fuel supply line 22 reaches a control valve 30 (described below) at a pressure equal to or greater than the critical pressure Pc of hydrogen. Note that when the pressure booster pump 26 pressurizes the hydrogen fuel to a pressure equal to or greater than the critical pressure Pc, the hydrogen fuel is at a temperature below the critical temperature Tc. A shutoff valve 27 is provided in the fuel supply line 22 between the check valve 25 and the pressure booster pump 26.

[0018] A heat exchanger 28 is provided in the fuel supply path 22 downstream of the pressure pump 26. The heat exchanger 28 heats the hydrogen fuel flowing through the fuel supply path 22 to a temperature equal to or higher than the critical temperature Tc of hydrogen. The heat exchanger 28 is thermally connected to the gas turbine engine 6. That is, the heat exchanger 28 heats the hydrogen fuel in the fuel supply path 22 by utilizing the heat of the gas turbine engine 6.

[0019] A sensor 29 is provided in the fuel supply path 22 downstream of the pressure pump 26. In this embodiment, the sensor 29 is provided in the fuel supply path 22 downstream of the pressure pump 26 and upstream of the heat exchanger 28. The sensor 29 is preferably adjacent to the pressure pump 26, the heat exchanger 28, or both. In this disclosure, "adjacent" means that no other fluid equipment, such as a valve or a pump, is interposed between the two pieces of equipment. The sensor 29 includes a flow meter 41, a pressure gauge 42, and a thermometer 43. That is, the sensor 29 measures the flow rate, pressure, and temperature of the hydrogen fuel that has passed through the pressure pump 26.

[0020] A control valve 30 is provided in the fuel supply path 22 downstream of the sensor 29. It is desirable that the control valve 30 be adjacent to the sensor 29. The control valve 30 adjusts the flow rate of hydrogen fuel that has passed through the sensor 29. A shutoff valve 31 is provided in the fuel supply path 22 downstream of the control valve 30. The presence or absence and placement of the shutoff valves 24, 27, and 31 are optional.

[0021] A control valve 30 may be provided in the fuel supply passage 22 upstream of the sensor 29, or upstream and downstream of the sensor 29. In either case, it is desirable that the control valve 30 be adjacent to the sensor 29.

[0022] The hydrogen fuel supply system 10 includes a controller 32. The controller 32 includes a processing circuit 33. The processing circuit 33 includes a processor, a system memory, and a storage memory. The processor is, for example, a CPU. The system memory is, for example, a RAM. The storage memory is, for example, a hard disk, a flash memory, or a combination thereof. An example of the processing circuit 33 is a configuration in which a program stored in the storage memory is read into the system memory and executed by the processor. The processing circuit 33 is configured to control the booster pump 26 or the control valve 30 in response to a measurement signal from the sensor 29. The processing circuit 33 may also be configured to control the feed pump 23. The processing circuit 33 may be configured to control the booster pump 26, the control valve 30, and the feed pump 23 individually or simultaneously. The measurement signal from the sensor 29 is, for example, the pressure or flow rate of the hydrogen fuel.

[0023] When the processing circuit 33 receives an engine start command, it drives the feed pump 23. The processing circuit 33 controls the pressure pump 26 to pressurize the hydrogen fuel in the fuel supply line 22 to a pressure equal to or higher than the critical pressure Pc. The processing circuit 33 controls the control valve 30 so that the flow rate measured by the sensor 29 becomes a target flow rate. The processing circuit 33 outputs an alert when the pressure measured by the sensor 29 is lower than the critical pressure Pc or when the flow rate measured by the sensor 29 is lower than a predetermined flow rate. The processing circuit 33 also outputs an alert when the temperature measured by the sensor 29 is lower than the critical temperature Tc.

[0024] When the pressure measured by the sensor 29 becomes lower than the critical pressure Pc, the processing circuit 33 controls the pressure pump 26 so that the pressure measured by the sensor 29 becomes equal to or higher than the critical pressure Pc. For example, the processing circuit 33 can feedback-control the pressure pump 26 in accordance with the measurement signal relating to the pressure of the hydrogen fuel measured by the sensor 29.

[0025] Furthermore, when the flow rate measured by the sensor 29 becomes lower than a predetermined flow rate, the processing circuit 33 controls the control valve 30 so that the flow rate measured by the sensor 29 becomes the predetermined flow rate. For example, the processing circuit 33 can control the opening degree of the control valve 30 in accordance with the measurement signal relating to the flow rate of hydrogen fuel measured by the sensor 29.

[0026] Furthermore, when the temperature measured by sensor 29 falls below critical temperature Tc, processing circuitry 33 may control the amount of heat input to liquid hydrogen per unit density in heat exchanger 28 so that the temperature measured by sensor 29 becomes equal to or higher than critical temperature Tc. For example, if heat exchanger 28 uses the heat source of engine 6 as a medium, a heat shield may be provided upstream of heat exchanger 28, and an actuator for the heat shield may be controlled to change the area that the heat shield covers over heat exchanger 28.

[0027] The fuel supply path 22 includes a first area A1 located upstream of the heat exchanger 28 and a second area A2 provided in the gas turbine engine 6 and located downstream of the heat exchanger 28. The first area A1 of the fuel supply path 22 is arranged in the fuselage 2 or the main wing 3. The second area A2 of the fuel supply path 22 is arranged in the gas turbine engine 6. The first area A1 of the fuel supply path 22 is covered with a thermal insulating material. This keeps the hydrogen fuel at a low temperature from the fuel tank 21 to the heat exchanger 28. On the other hand, the second area A2 of the fuel supply path 22 is not covered with a thermal insulating material. This prevents an increase in weight in the gas turbine engine 6 and suppresses a reduction in space.

[0028] In the configuration described above, since the sensor 29 is provided downstream of the booster pump 26, the pressure of the hydrogen fuel can be maintained within an appropriate range by the processing circuit 33 controlling the booster pump 26 in accordance with the measurement signal related to the pressure of the hydrogen fuel from the sensor 29. This makes it possible to stabilize the operation of the engine using hydrogen fuel in the supercritical phase.

[0029] Furthermore, if a control valve 30 is provided downstream of the booster pump 26 in addition to the sensor 29, the flow rate of the hydrogen fuel can be maintained within an appropriate range by the processing circuit 33 controlling the control valve 30 in response to a measurement signal relating to the flow rate of the hydrogen fuel from the sensor 29. This makes it possible to stabilize the engine output.

[0030] If a control valve 30 is provided downstream of the sensor 29, it is possible to measure the flow rate of hydrogen fuel before adjustment by the control valve 30. Furthermore, if a control valve 30 is provided upstream of the sensor 29, it is possible to measure the state of fuel supply to the gas turbine engine 6 after adjustment by the control valve 30.

[0031] When the sensor 29 is adjacent to at least one of the pressure pump 26, the heat exchanger 28, and the control valve 30, since no other fluid equipment is interposed between the adjacent equipment and the sensor 29, the pressure, temperature, and flow rate of the hydrogen fuel can be measured with high accuracy, and abnormalities in the pressure pump 26, the heat exchanger 28, and the control valve 30 can be quickly detected.

[0032] Second Embodiment Fig. 4 is a block diagram of a hydrogen fuel supply system 110 according to a second embodiment. Components common to the first embodiment are designated by the same reference numerals, and a description thereof will be omitted. As shown in Fig. 4, the hydrogen fuel supply system 110 of the second embodiment has a different arrangement of the sensor 29 than the hydrogen fuel supply system 10 of the first embodiment. In this embodiment, the sensor 29 is provided downstream of the pressure pump 26 and the heat exchanger 28. It is desirable that the sensor 29 be adjacent to the heat exchanger 28. Other components are the same as those of the first embodiment, and therefore a description thereof will be omitted.

[0033] The control valve 30 is provided downstream of the sensor 29. The control valve 30 may be provided upstream of the sensor 29, or may be provided both upstream and downstream of the sensor 29. In either case, it is desirable that the control valve 30 be adjacent to the sensor 29.

[0034] In the configuration described above, since the sensor 29 is provided downstream of the heat exchanger 28, the sensor 29 can measure the pressure of the hydrogen fuel and the like at a position close to the gas turbine engine 6. The processing circuit 33 controls the booster pump 26 in response to the measurement signal related to the pressure of the hydrogen fuel and the like from the sensor 29, thereby making it possible to maintain the pressure of the hydrogen fuel and the like within an appropriate range. This makes it possible to stabilize the operation of the engine using hydrogen fuel in a supercritical phase.

[0035] As described above, the above embodiments have been described as examples of the technology disclosed in this application. However, the technology of the present disclosure is not limited to these and can be applied to embodiments in which modifications, substitutions, additions, omissions, etc. are made as appropriate. Furthermore, the components described in the above embodiments can be combined to create new embodiments. For example, some configurations or methods in one embodiment may be applied to other embodiments, and some configurations in an embodiment can be separated and arbitrarily extracted from other configurations in that embodiment. Furthermore, the components described in the accompanying drawings and detailed description include not only components essential for solving the problem, but also components that are not essential for solving the problem, and are used to illustrate the technology.

[0036] The functions of the elements disclosed herein can be performed using circuits or processing circuits, including general-purpose processors, special-purpose processors, integrated circuits, application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), conventional circuits, and / or combinations thereof, configured or programmed to perform the disclosed functions. Processors are considered processing circuits or circuits because they include transistors and other circuitry. In this disclosure, a circuit, unit, or means is hardware that performs the recited functions or hardware that is programmed to perform the recited functions. The hardware may be hardware disclosed herein or other known hardware that is programmed or configured to perform the recited functions. Where the hardware is a processor, which is considered a type of circuit, the circuit, means, or unit is a combination of hardware and software, and the software is used to configure the hardware and / or processor.

[0037] Each of the following sections is a disclosure of a preferred embodiment.

[0038] [Item 1] A hydrogen fuel supply system for an aircraft equipped with an engine, comprising: a fuel tank that stores hydrogen fuel in a liquid phase; a fuel supply line that connects the fuel tank to the engine; a pressure pump that is provided in the fuel supply line and pressurizes the hydrogen fuel to a pressure equal to or higher than the critical pressure; and a sensor that is provided in the fuel supply line downstream of the pressure pump and measures the pressure of the hydrogen fuel that has passed through the pressure pump.

[0039] With this configuration, when the pressure of hydrogen fuel is increased to a pressure equal to or higher than the critical pressure by the pressure pump, the pressure of the hydrogen fuel can be measured by a sensor downstream of the pressure pump. This makes it possible to control the operation of the pressure pump in accordance with the pressure of the hydrogen fuel, thereby stabilizing the operation of an engine that uses hydrogen fuel in a supercritical phase.

[0040] [Item 2] The hydrogen fuel supply system according to item 1, further comprising a heat exchanger provided in the fuel supply line downstream of the booster pump, for heating the hydrogen fuel to a temperature equal to or higher than a critical temperature.

[0041] According to this configuration, the hydrogen fuel can be pressurized to a pressure above the critical pressure by the pressure pump, and then heated to a temperature above the critical temperature by the heat exchanger, so that the hydrogen fuel can be smoothly brought into a supercritical phase.

[0042] [Item 3] The hydrogen fuel supply system according to item 1 or 2, further comprising a control valve provided in the fuel supply passage downstream of the booster pump, for controlling the flow rate of the hydrogen fuel that has passed through the booster pump.

[0043] According to this configuration, the flow rate of hydrogen fuel supplied to the engine can be adjusted by the control valve.

[0044] [Item 4] The hydrogen fuel supply system according to item 2 or 3, wherein the sensor is provided upstream of the heat exchanger in the fuel supply path and measures the pressure and temperature of the hydrogen fuel that has passed through the pressure pump.

[0045] With this configuration, the pressure and temperature of the hydrogen fuel that has passed through the booster pump can be measured by the sensors, making it possible to control the operation of the booster pump in accordance with the pressure and temperature of the hydrogen fuel downstream of the booster pump, thereby stabilizing the operation of the engine that uses supercritical hydrogen fuel.

[0046] [Item 5] The hydrogen fuel supply system according to item 2 or 3, wherein the sensor is provided downstream of the heat exchanger in the fuel supply path and measures the pressure and temperature of the hydrogen fuel that has passed through the heat exchanger.

[0047] With this configuration, the pressure and temperature of the hydrogen fuel that has passed through the booster pump and the heat exchanger can be measured by sensors, making it possible to control the operation of the booster pump in accordance with the pressure and temperature of the hydrogen fuel downstream of the heat exchanger, thereby stabilizing the operation of the engine that uses supercritical hydrogen fuel.

[0048] [Item 6] The hydrogen fuel supply system according to any one of items 1 to 5, wherein the sensor is adjacent to the booster pump.

[0049] According to this configuration, since the sensor is located adjacent to the pressure pump, the pressure and temperature of the hydrogen fuel discharged by the pressure pump can be measured with even greater accuracy.

[0050] [Item 7] The hydrogen fuel supply system according to any one of items 1 to 5, wherein the sensor is adjacent to at least one of the booster pump and the heat exchanger.

[0051] This configuration allows for more accurate measurement of the pressure and temperature of the hydrogen fuel, which are directly related to at least one of the pressure pump and the heat exchanger.

[0052] [Item 8] The hydrogen fuel supply system according to any one of items 3 to 5, wherein the sensor is adjacent to at least one of the booster pump, the heat exchanger, and the control valve.

[0053] This configuration allows for more accurate measurement of the pressure and temperature of the hydrogen fuel that are directly related to at least one of the pressure pump, the heat exchanger, and the control valve.

[0054] [Item 9] The hydrogen fuel supply system according to any one of items 1 to 8, wherein the sensor further measures the flow rate of the hydrogen fuel that has passed through the booster pump.

[0055] This configuration allows the flow rate of hydrogen fuel to be measured with high precision, thereby enabling the engine output to be controlled with high precision.

[0056] [Item 10] The hydrogen fuel supply system according to any one of items 1 to 9, further comprising a processing circuit configured to control the booster pump in response to a pressure measurement signal from the sensor.

[0057] With this configuration, even if pressure fluctuations occur in the fuel supply line due to changes in the opening of the control valve, the pressure fluctuations can be reduced by controlling the booster pump, thereby maintaining the pressure of the hydrogen fuel supplied to the engine within an appropriate range.

[0058] [Item 11] The hydrogen fuel supply system according to Item 9, further comprising a processing circuit configured to control the opening of the control valve in response to a flow rate measurement signal from the sensor.

[0059] According to this configuration, the control valve is controlled in accordance with the flow rate measured by the sensor, so the flow rate of hydrogen fuel supplied to the engine can be adjusted with high precision.

[0060] [Item 12] The hydrogen fuel supply system according to any one of Items 1 to 11, wherein the aircraft comprises a fuselage, a main wing connected to the fuselage, and the engine connected to the main wing, the fuel tank is disposed in the fuselage or the main wing, the heat exchanger is disposed in the engine, and the fuel supply path includes a first region provided in the fuselage or the main wing and upstream of the heat exchanger, and a second region provided in the engine and downstream of the heat exchanger, the first region being covered with a thermal insulating material, and the second region being not covered with a thermal insulating material.

[0061] With this configuration, it is possible to keep the hydrogen fuel at a low temperature up to the heat exchanger, while eliminating the need for heat insulating materials around the engine, thereby preventing an increase in weight and a reduction in space around the engine.

[0062] REFERENCE SIGNS LIST 1 aircraft 2 fuselage 3 main wing 6 gas turbine engine 10 hydrogen fuel supply system 21 fuel tank 22 fuel supply line 26 pressure pump 28 heat exchanger 29 sensor 30 control valve 33 processing circuit 41 flow meter 42 pressure gauge 43 thermometer A1 first area A2 second area

Claims

1. A hydrogen fuel supply system for an aircraft equipped with an engine, comprising: a fuel tank for storing hydrogen fuel in a liquid phase; a fuel supply line connecting the fuel tank to the engine; a pressure booster pump provided in the fuel supply line for pressurizing the hydrogen fuel to a pressure equal to or higher than the critical pressure; and a sensor provided in the fuel supply line downstream of the pressure booster pump for measuring the pressure of hydrogen fuel that has passed through the pressure booster pump.

2. The hydrogen fuel supply system according to claim 1, further comprising a heat exchanger provided in said fuel supply passage downstream of said booster pump for heating said hydrogen fuel to a temperature equal to or higher than the critical temperature.

3. The hydrogen fuel supply system according to claim 1 or 2, further comprising a control valve provided downstream of said booster pump in said fuel supply passage for controlling the flow rate of the hydrogen fuel that has passed through said booster pump.

4. A hydrogen fuel supply system according to claim 2 or 3, wherein the sensor is provided upstream of the heat exchanger in the fuel supply path and measures the pressure and temperature of the hydrogen fuel that has passed through the booster pump.

5. A hydrogen fuel supply system as described in claim 2 or 3, wherein the sensor is provided downstream of the heat exchanger in the fuel supply path and measures the pressure and temperature of the hydrogen fuel that has passed through the heat exchanger.

6. A hydrogen fuel supply system according to any one of claims 1 to 5, wherein the sensor is adjacent to the booster pump.

7. The hydrogen fuel supply system according to any one of claims 1 to 5, wherein the sensor is adjacent to at least one of the booster pump and the heat exchanger.

8. The hydrogen fuel supply system of any one of claims 3 to 5, wherein the sensor is adjacent to at least one of the booster pump, the heat exchanger, and the control valve.

9. A hydrogen fuel supply system according to any one of claims 1 to 8, wherein the sensor further measures the flow rate of hydrogen fuel passed through the booster pump.

10. A hydrogen fuel supply system according to any one of claims 1 to 9, further comprising a processing circuit configured to control the booster pump in response to a pressure measurement signal of the sensor.

11. The hydrogen fuel supply system of claim 9, further comprising a processing circuit configured to control the opening of the control valve in response to a flow measurement signal of the sensor.

12. A hydrogen fuel supply system as described in any one of claims 1 to 11, wherein the aircraft comprises a fuselage, a main wing connected to the fuselage, and the engine connected to the main wing, the fuel tank is disposed in the fuselage or the main wing, the heat exchanger is disposed in the engine, the fuel supply path includes a first region provided in the fuselage or the main wing and upstream of the heat exchanger, and a second region provided in the engine and downstream of the heat exchanger, the first region being covered with a thermal insulation material, and the second region being not covered with a thermal insulation material.

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