Hydrogen fuel feed system

Abstract

To stabilize an engine operation which uses hydrogen fuel of a supercritical phase.SOLUTION: A hydrogen fuel feed system 10 for an aircraft equipped with an engine comprises: a fuel tank 21 that stores hydrogen fuel in a liquid phase; a fuel feed path 22 through which the fuel tank 21 is connected to the engine; a pressure pump 26 provided on the fuel feed path 22 to pressure the hydrogen fuel equal to or higher than critical pressure; and a sensor 29 provided downstream of the pressure pump 26 on the fuel feed path 22 to measure the pressure of the hydrogen fuel passed through the pressure pump 26.SELECTED DRAWING: Figure 3

Description

[Technical field]

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

[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 gas phase or supercritical phase. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] US Patent Application Publication No. 2022 / 0145801 Summary of the Invention [Problem to be solved by the invention]

[0004] When hydrogen fuel changes from a liquid phase to a gas phase in the fuel supply passage during fuel supply, it causes 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, and hydrogen fuel can be stably supplied to the engine.

[0005] Hydrogen fuel can be put into the supercritical phase by pressurizing it above its critical pressure and then heating it to a temperature above its critical temperature. This method of changing 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. [Means for solving the problem]

[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 provided in the fuel supply line that pressurizes 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 that measures the pressure of hydrogen fuel that has passed through the pressure booster pump. Effect of the Invention

[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 the pressure pump, the pressure of the hydrogen fuel can be measured by a sensor downstream of the pressure pump. Therefore, the operation of the pressure pump can be controlled according to the pressure of the hydrogen fuel, and the operation of the engine using hydrogen fuel in a supercritical phase can be stabilized. [Brief description of the drawings]

[0009] [Figure 1] FIG. 1 is a plan view of an aircraft equipped with a hydrogen fuel supply system according to a first embodiment. [Diagram 2] FIG. 2 is a phase diagram showing the relationship between the phase of hydrogen and temperature-pressure. [Diagram 3] FIG. 3 is a block diagram of the hydrogen fuel supply system of FIG. [Figure 4] FIG. 4 is a block diagram of a hydrogen fuel supply system according to the second embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0010] Hereinafter, an embodiment will be described with reference to the drawings. In this disclosure, an aircraft refers to a device that can move in the air, and is, for example, a fixed-wing aircraft, a rotorcraft, 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, a main wing 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 an occupant space therein. The main wing 3 is connected to a middle part of the fuselage 2 in the longitudinal direction, and protrudes from the fuselage 2 in the lateral direction of the aircraft 1. The horizontal stabilizer 4 protrudes from the rear of the fuselage 2 in the lateral direction of the aircraft 1. The vertical stabilizer 5 protrudes upward from the rear of the fuselage 2. The gas turbine engine 6 is connected to a pair of main wings 3. The fuselage 2, the main wing 3, and the gas turbine engine 6 are equipped with a hydrogen fuel supply system 10. The fuel tank 21 is disposed in the fuselage 2, but may be disposed in the main wing 3. That is, all or a part of the fuel tank 21 is disposed in the fuselage 2 or the main wing 3.

[0012] FIG. 2 is a phase diagram showing the relationship between the phase of hydrogen and temperature-pressure. As shown in FIG. 2, in the hydrogen phase diagram, the solid phase and the gas phase are separated by the sublimation line L1, the solid phase and the liquid phase are separated by the melting line L2, and the liquid phase and the gas phase are separated by the boiling line L3. The intersection R of the sublimation line L1, the melting line L2, and the boiling line L3 is called the triple point. Hydrogen becomes 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 of the critical pressure Pc and the critical temperature Tc is called the critical point Q. The critical pressure Pc is about 1.3 MPa, and the critical temperature Tc is about -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, whereby the hydrogen fuel transitions from the liquid phase to the supercritical phase.

[0014] In order to realize 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 passage 22 is pressurized by the pressure pump 26 to a pressure equal to or higher than the critical pressure Pc. When the hydrogen fuel flowing from the pressure pump 26 toward the gas turbine engine 6 is heated by the 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 boiling phenomenon in which the hydrogen fuel in the fuel supply passage 22 transitions from the liquid phase to the gas phase.

[0015] 3 is a block diagram of the hydrogen fuel supply system 10 of FIG. 1. As shown in FIG. 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 that sends hydrogen fuel from the fuel tank 21 to the fuel supply path 22 is provided in 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 pump 26 is provided in the fuel supply path 22 downstream of the check valve 25. The pressure pump 26 pressurizes the hydrogen fuel in the fuel supply path 22 to a pressure equal to or higher than the critical pressure Pc of hydrogen. For example, the pressure pump 26 pressurizes liquid phase hydrogen fuel supplied from the fuel tank 21 so that the hydrogen fuel flowing through the fuel supply path 22 has a pressure equal to or higher than the critical pressure Pc of hydrogen when it reaches a control valve 30 described below. Note that when the hydrogen fuel is pressurized by the pressure pump 26 to a pressure equal to or higher than the critical pressure Pc, the hydrogen fuel is at a temperature lower than the critical temperature Tc. A shutoff valve 27 is provided in the fuel supply path 22 between the check valve 25 and the pressure 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] The fuel supply passage 22 is provided with a sensor 29 downstream of the pressure pump 26. In this embodiment, the fuel supply passage 22 is provided with the sensor 29 downstream of the pressure pump 26 and upstream of the heat exchanger 28. It is desirable that the sensor 29 be adjacent to the pressure pump 26, the heat exchanger 28, or both. In this disclosure, "adjacent" means that no other fluid device such as a valve, pump, etc. is interposed between the two devices. 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 preferable that the control valve 30 is 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 location of the shutoff valves 24, 27, 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 preferable 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. A configuration in which a program stored in the storage memory is read into the system memory and executed by the processor is an example of the processing circuit 33. The processing circuit 33 is configured to control the pressurizing pump 26 or the control valve 30 in response to a measurement signal from the sensor 29. The processing circuit 33 may be configured to control the feed pump 23. The processing circuit 33 may be configured to control the pressurizing 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 so as to pressurize the hydrogen fuel in the fuel supply passage 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 the 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 response to a 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 response to a 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 the critical temperature Tc, the processing circuit 33 may control the amount of heat input to the liquid hydrogen per unit density in the heat exchanger 28 so that the temperature measured by sensor 29 becomes equal to or higher than the critical temperature Tc. For example, in the case where the heat exchanger 28 uses the heat source of the engine 6 as a medium, a heat shield may be provided upstream of the heat exchanger 28, and the actuator of the heat shield may be controlled to change the area that the heat shield covers the heat exchanger 28.

[0027] The fuel supply passage 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 passage 22 is disposed in the fuselage 2 or the main wing 3. The second area A2 of the fuel supply passage 22 is disposed in the gas turbine engine 6. The first area A1 of the fuel supply passage 22 is covered with a heat 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 passage 22 is not covered with a heat 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 pressure pump 26, the pressure of the hydrogen fuel can be maintained within an appropriate range by the processing circuit 33 controlling the pressure pump 26 in response to a 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 that uses 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 output of the engine.

[0030] When a control valve 30 is provided downstream of the sensor 29, the flow rate of hydrogen fuel before adjustment by the control valve 30 can be measured. Also, when a control valve 30 is provided upstream of the sensor 29, the fuel supply state to the gas turbine engine 6 after adjustment by the control valve 30 can be measured.

[0031] When the sensor 29 is adjacent to at least one of the booster pump 26, the heat exchanger 28, and the control valve 30, since there is no other fluid equipment 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 any abnormalities in the booster pump 26, the heat exchanger 28, and the control valve 30 can be quickly detected.

[0032] Second embodiment 4 is a block diagram of a hydrogen fuel supply system 110 according to the second embodiment. Components common to the first embodiment are denoted by the same reference numerals and will not be described. As shown in FIG. 4, the hydrogen fuel supply system 110 of the second embodiment has a different arrangement of a sensor 29 compared to 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 similar to those of the first embodiment and will not be described.

[0033] Moreover, the control valve 30 is provided downstream of the sensor 29. Note that 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 and the like of the hydrogen fuel at a position close to the gas turbine engine 6. The processing circuit 33 controls the booster pump 26 in response to a measurement signal from the sensor 29 relating to the pressure and the like of the hydrogen fuel, thereby making it possible to maintain the pressure and the like of the hydrogen fuel within an appropriate range. This makes it possible to stabilize the operation of the engine that uses hydrogen fuel in a supercritical phase.

[0035] As described above, the above embodiment has been described as an example of the technology disclosed in this application. However, the technology in this disclosure is not limited to this, and can be applied to embodiments in which modifications, replacements, additions, omissions, etc. have been made as appropriate. In addition, it is also possible to combine the components described in the above embodiment to create a new embodiment. For example, a part of the configuration or method in one embodiment may be applied to another embodiment, and a part of the configuration in an embodiment can be separated from other configurations in that embodiment and arbitrarily extracted. In addition, the components described in the attached drawings and detailed description include not only components essential for solving the problem, but also components that are not essential for solving the problem in order to exemplify 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 circuits. 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. In the case 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 the processor.

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

[0038] [Item 1] 1. A hydrogen fuel supply system for an aircraft having 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 pump provided in the fuel supply passage and configured to pressurize the hydrogen fuel to a pressure equal to or higher than a critical pressure; a sensor that is provided in the fuel supply path downstream of the booster pump and that measures the pressure of the hydrogen fuel that has passed through the booster pump.

[0039] According to this configuration, when the pressure of hydrogen fuel is pressurized 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. Therefore, the operation of the pressure pump can be controlled according to the pressure of the hydrogen fuel, and the operation of the engine using hydrogen fuel in the supercritical phase can be stabilized.

[0040] [Item 2] 2. The hydrogen fuel supply system according to item 1, further comprising a heat exchanger provided in the fuel supply passage 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 equal to or higher than the critical pressure by the pressure pump, and then the hydrogen fuel can be heated to a temperature equal to or higher than the critical temperature by the heat exchanger, so that the hydrogen fuel can be smoothly brought into a supercritical phase.

[0042] [Item 3] 3. The hydrogen fuel supply system according to claim 1, further comprising a control valve provided downstream of the booster pump in the fuel supply passage, the control valve controlling a 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] 4. The hydrogen fuel supply system according to claim 2, 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.

[0045] According to this configuration, the pressure and temperature of the hydrogen fuel that has passed through the booster pump can be measured by the sensors, and therefore the operation of the booster pump can be controlled according to the pressure and temperature of the hydrogen fuel downstream of the booster pump, making it possible to stabilize the operation of the engine that uses hydrogen fuel in a supercritical phase.

[0046] [Item 5] 4. The hydrogen fuel supply system according to claim 2, 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] According to this configuration, the pressure and temperature of the hydrogen fuel that has passed through the pressure pump and the heat exchanger can be measured by the sensors, so that the operation of the pressure pump can be controlled according to the pressure and temperature of the hydrogen fuel downstream of the heat exchanger, and the operation of the engine that uses supercritical hydrogen fuel can be stabilized.

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

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

[0050] [Item 7] 6. 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.

[0051] 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 and the heat exchanger.

[0052] [Item 8] 6. 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] According to this configuration, the pressure and temperature of the hydrogen fuel directly related to at least one of the pressure pump, the heat exchanger, and the control valve can be measured with greater accuracy.

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

[0055] According to this configuration, the flow rate of hydrogen fuel can be measured with high accuracy, and therefore the engine output can be controlled with high accuracy.

[0056] [Item 10] 10. The 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.

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

[0058] [Item 11] 10. The hydrogen fuel supply system of item 9, further comprising a processing circuit configured to control the opening degree of the control valve in response to a flow rate measurement signal of 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 aircraft comprises a fuselage, a wing connected to the fuselage, and the engine connected to the wing; The fuel tank is disposed in the fuselage or the main wing, The heat exchanger is disposed in the engine, the fuel supply passage includes a first region provided in the fuselage or the main wing and located upstream of the heat exchanger, and a second region provided in the engine and located downstream of the heat exchanger; 12. The hydrogen fuel supply system according to any one of claims 1 to 11, wherein the first region is covered with a thermal insulation material, and the second region is not covered with a thermal insulation material.

[0061] According to this configuration, while hydrogen fuel is kept at a low temperature up to the heat exchanger, heat insulation material can be omitted around the engine, preventing an increase in weight and a reduction in space around the engine. [Explanation of symbols]

[0062] 1 aircraft 2. Torso 3. Main Wing 6. Gas Turbine Engine 10 Hydrogen Fuel Supply System 21 Fuel Tank 22 Fuel supply path 26 Pressure Pump 28 Heat exchanger 29 Sensors 30 Control valve 33 Processing circuit 41 Flowmeter 42 Pressure gauge 43 Thermometer A1 1st area A2 2nd area

Claims

1. 1. A hydrogen fuel supply system for an aircraft having 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 pump provided in the fuel supply passage and configured to pressurize the hydrogen fuel to a pressure equal to or higher than a critical pressure; a sensor that is provided in the fuel supply path downstream of the booster pump and that measures a pressure of the hydrogen fuel that has passed through the booster pump.

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

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

4. 3. The hydrogen fuel supply system according to claim 2, 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. 3. The hydrogen fuel supply system according to claim 2, 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. The hydrogen fuel supply system of claim 1 , wherein the sensor is adjacent to the boost pump.

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

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

9. 7. The hydrogen fuel supply system of claim 1, wherein the sensor further measures a flow rate of hydrogen fuel passing through the booster pump.

10. 7. The hydrogen fuel supply system according to claim 1, further comprising a processing circuit configured to control the booster pump in response to a pressure measurement signal of the sensor.

11. 10. 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. The aircraft comprises a fuselage, a wing connected to the fuselage, and the engine connected to the wing; The fuel tank is disposed in the fuselage or the main wing, The heat exchanger is disposed in the engine, the fuel supply passage includes a first region provided in the fuselage or the main wing and located upstream of the heat exchanger, and a second region provided in the engine and located downstream of the heat exchanger; 7. The hydrogen fuel supply system according to claim 1, wherein the first region is covered with a thermal insulation material, and the second region is not covered with a thermal insulation material.

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