Hydrogen supply system comprising at least two tanks configured to store hydrogen in liquid and supercritical states respectively

Abstract

Hydrogen supply device comprising at least two tanks configured to store hydrogen in liquid and supercritical states, respectively. The invention relates to a hydrogen supply device (18) comprising: at least one first tank (20) configured to store hydrogen in a liquid state at a pressure below 13 bar; at least one second tank (22) configured to store hydrogen in a supercritical state at a pressure greater than or equal to 13 bar; at least one upstream portion (26) comprising at least one first hydrogen flow control system (32, 32', 32'') configured to regulate the amount of hydrogen flowing from the first tank (20) to the second tank (22); at least one downstream portion (28) connecting the second tank (22) and a hydrogen-powered system (16). The invention also relates to an aircraft comprising at least one such supply device. Figure 2

Description

Title of the invention: Hydrogen supply device comprising at least two reservoirs configured to store hydrogen respectively in liquid and supercritical states

[0001] The present application relates to a hydrogen supply device comprising at least two tanks configured to store hydrogen respectively in liquid and supercritical states and to an aircraft comprising at least one such hydrogen supply device.

[0002] According to an embodiment of the prior art, an aircraft hydrogen supply device comprises at least one hydrogen tank and at least one distribution circuit connecting the hydrogen tank and at least one hydrogen-operating system such as a hydrogen engine or a fuel cell.

[0003] Each distribution circuit includes conduits as well as various equipment, such as pumps, sensors, valves or exchangers for example, connected to each other by the conduits.

[0004] According to a first embodiment, the hydrogen is stored in the hydrogen tank in liquid form, at a cryogenic temperature, and the distribution circuit includes a high-pressure pump to pressurize the hydrogen and a heat exchanger configured to heat the hydrogen, the hydrogen passing from the liquid state to the gaseous state.

[0005] Although this first embodiment significantly reduces the tank volume compared to a tank storing hydrogen in gaseous form, it is not entirely satisfactory because the distribution circuit is much more complex and includes a greater number of components. For example, some components are designed to adjust the amount of hydrogen supplied to the engine(s) according to the desired engine speed, while others are designed to provide backup for certain components in case of failure, thus ensuring a high level of safety.

[0006] According to a second embodiment, hydrogen is stored in a hydrogen tank in liquid form, at a cryogenic temperature and at a pressure higher than the operating pressure of the hydrogen system.

[0007] Even though this second embodiment allows the mass of the tank to be reduced compared to a tank storing hydrogen in a gaseous state, the tank of the second embodiment nevertheless has a greater mass than that of the tank of the first embodiment, the tank having to withstand a higher pressure.

[0008] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0009] To this end, the invention relates to a hydrogen supply device comprising at least a first reservoir configured to store hydrogen in a liquid state and at a pressure of less than 13 bar, preferably less than 6 bar, and at least one inlet line which has a first end connected to the first reservoir and at least a second end configured to be connected to an inlet of a hydrogen system operating at an operating pressure and temperature.

[0010] According to the invention, the inlet line comprises: a. at least one second tank configured to store hydrogen in a supercritical state and at a pressure greater than or equal to 13 bar, b. at least one upstream section comprising at least one feed section which connects the first and second tanks and includes at least one first hydrogen flow control system configured to regulate a quantity of hydrogen flowing from the first tank to the second tank, c. at least one downstream portion connecting the second tank and the second end of the intake line.

[0011] This solution makes it possible to retain the advantages of the first and second embodiments of the prior art while limiting the increase in the mass carried due to the reduced volume of the second tank.

[0012] According to another feature, the second tank is configured to store hydrogen at a pressure higher than the operating pressure of the hydrogen system. Thus, the hydrogen supply device can supply the hydrogen system even in the event of a malfunction of the first hydrogen flow control system.

[0013] According to another feature, the second tank has a volume at least five times smaller than that of the first tank.

[0014] According to another feature, the first hydrogen flow control system includes at least one first pump, at least one first control valve and at least one check valve.

[0015] According to another feature, at least a first hydrogen flow control system includes a recirculation section extending from a branch, provided between the first pump and the check valve, to the first tank, the first control valve being located at the recirculation section or between the branch and the check valve.

[0016] According to another feature, the upstream part includes at least one return section, connecting the first and second tanks, in which hydrogen flows from the second tank to the first tank in operation.

[0017] According to another feature, the return section includes at least one second hydrogen flow control system configured to regulate a quantity of hydrogen flowing from the second tank to the first tank and / or at least one first thermal control system configured to regulate the temperature of the hydrogen returning to the first tank.

[0018] According to another feature, the second tank includes at least one second thermal regulation system configured to regulate the temperature and / or pressure of the hydrogen present in the second tank.

[0019] According to another feature, the downstream part includes at least one thermal regulation system configured to bring the hydrogen exiting the second tank to an inlet temperature suitable for the operating temperature of the hydrogen system and / or at least one hydrogen flow regulation system configured to regulate a quantity of hydrogen supplied to the hydrogen system.

[0020] The invention also relates to an aircraft comprising at least one hydrogen supply device according to one of the preceding characteristics and a method of operating a hydrogen supply device which supplies at least one hydrogen system of an aircraft and comprises at least one first tank configured to store hydrogen in a liquid state and at a pressure of less than 13 bar, preferably less than 6 bar, and at least one inlet line connecting the first tank and the hydrogen system.

[0021] According to the invention, the inlet line comprises: a. at least one second tank configured to store hydrogen in a supercritical state and at a pressure greater than or equal to 13 bar, b. several supply sections, each connecting the first and second tanks, and each comprising at least one first hydrogen flow control system configured to regulate a quantity of hydrogen flowing from the first tank to the second tank.

[0022] The operating method consists of operating said first hydrogen flow regulation systems according to the flight phases of the aircraft.

[0023] According to another feature, for at least one first phase of aircraft flight, at least one first hydrogen flow control system among the various hydrogen flow control systems operates continuously to maintain a constant pressure in the second tank and, for at least one second phase of flight different from the first phase of flight, at least one second hydrogen flow control system among the various systems hydrogen flow regulation operates discontinuously in order to maintain a pressure between minimum and maximum pressures in the second tank.

[0024] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which:

[0025] [Fig-1] is a side view of an aircraft,

[0026] [Fig.2] is a schematic representation of an aircraft hydrogen supply system illustrating one embodiment of the invention,

[0027] [Fig.3] is a representation of the evolution of pressure in a tank storing hydrogen in a supercritical state during a first phase of flight,

[0028] [Fig.4] is a representation of the evolution of pressure in a tank storing hydrogen in a supercritical state during a second phase of flight,

[0029] [Fig.5] is a schematic representation of an aircraft hydrogen supply device illustrating another embodiment of the invention,

[0030] [Fig.6] is a schematic representation of an aircraft hydrogen supply device illustrating another embodiment of the invention.

[0031] As illustrated in [Fig.1], an aircraft 10 comprises several propulsion units 12 located under the wings 14 and connected to them.

[0032] According to one configuration, at least one of the propulsion assemblies 12 includes a turbojet or turboprop operating on hydrogen, at an operating pressure greater than 13 bar, on the order of 40 bar.

[0033] Regardless of the embodiment, the aircraft 10 includes at least one hydrogen system 16 (visible in Figures 2, 5 and 6) consuming hydrogen and at least one hydrogen supply device 18 configured to supply the hydrogen system(s) 16.

[0034] Each hydrogen system 16 includes at least one inlet 16.1 and operates at a given operating pressure greater than or equal to 13 bar, preferably greater than or equal to 40 bar.

[0035] A hydrogen supply device 18 configured to supply at least one hydrogen system 16 comprises at least a first tank 20 configured to store hydrogen in a liquid state and at low pressure and at least a second tank 22 configured to store hydrogen in a supercritical state, at a high pressure greater than or equal to the operating pressure of the hydrogen system(s) 16. In this supercritical state, hydrogen has a high density, as in the liquid state.

[0036] By low pressure, we mean a pressure less than 13 bars, preferably less than 6 bars, on the order of 4 bars.

[0037] High pressure means a pressure greater than or equal to 13 bars.

[0038] In the first and second tanks 20, 22, hydrogen is stored at a cryogenic temperature of around -253°C. Storing hydrogen in liquid or supercritical form allows for a reduction in the dimensions of each of the first and second tanks 20, 22, which helps to reduce the overall size of said first and second tanks 20, 22.

[0039] The first and second tanks 20, 22 are thermally insulated to reduce heat loss. These first and second tanks 20, 22 are not described further because they may be identical to prior art tanks configured for storing liquefied hydrogen.

[0040] According to one configuration, the first tank 20 has a capacity of approximately 12 m3. According to one operating mode, the first tank 20 stores hydrogen at a pressure between 2 and 4 bars.

[0041] According to one configuration, the second tank 22 has a capacity of approximately 250 L. According to one operating mode, the second tank 22 stores hydrogen at a pressure between 40 and 50 bar.

[0042] According to a preferred embodiment, the second tank 22 has a volume at least five times, preferably ten times, less than that of the first tank 20 so that the majority of the hydrogen is stored at low pressure in the first tank 20. Therefore, even if the second tank 22 is more reinforced than the first tank 20, the increase in the onboard mass is limited because this second tank 22 has a small volume.

[0043] The hydrogen supply device 18 includes at least one intake line 24 connecting the first tank 20 and at least one hydrogen system 16. The second tank 22 is part of this supply line 24.

[0044] Each inlet line 24 includes a first end connected to the first tank 20 and at least a second end configured to be connected to the inlet 16.1 of at least one hydrogen system 16.

[0045] Each inlet line 24 comprises at least an upstream portion 26 connecting the first and second tanks 20, 22 and at least a downstream portion 28 connecting the second tank 22 and at least one hydrogen system 16.

[0046] According to a preferred arrangement, to limit heat losses and the number of conduits and equipment in contact with hydrogen in liquid form and at a cryogenic temperature, the second tank 22 is as close as possible to the first tank 20.

[0047] According to an embodiment visible in figures 2, 5 and 6, the hydrogen supply device 18 comprises a single inlet line 24.

[0048] According to other embodiments, the hydrogen supply device 18 comprises several inlet lines 24 for supplying the same (or the same) hydrogen system(s) 16 or different hydrogen systems 16. In one configuration, the various inlet lines 24 comprise separate upstream portions 26 and a common downstream portion 28. Alternatively, the various inlet lines 24 comprise a common upstream portion 26 and separate downstream portions 28.

[0049] The upstream part 26 includes at least one supply section 30, 30', 30" which has a first end 30.1, 30.1', 30.1" opening into the first reservoir 20 and a second end 30.2, 30.2', 30.2" opening into the second reservoir 22.

[0050] According to a configuration visible in [Fig.2], the upstream part 26 comprises a single supply section 30. According to other configurations visible in Figures 5 and 6, the upstream part 26 comprises several supply sections 30, 30', 30" which may be identical or different.

[0051] According to one embodiment, each supply section 30, 30', 30" includes at least one first hydrogen flow control system 32, 32', 32" configured to regulate a quantity of hydrogen flowing from the first tank 20 to the second tank 22. This quantity of hydrogen is regulated by controlling, for example, the mass or volumetric flow rate.

[0052] According to one embodiment, the first hydrogen flow control system 32, 32', 32" includes at least one first pump 34, 34', 34" at the outlet of the first tank 20 and at least one check valve 32.1, 32.1', 32.1" downstream of the second tank 22.

[0053] According to a configuration visible in Figures 2 and 5, at least a first hydrogen flow control system 32, 32' comprises: a. a recirculation section 36, 36' extending from a branch 30.3, 30.3', provided between the first pump 34, 34' and the non-return valve 32.1, 32.1', to the first reservoir 20, b. at least one first control valve 32.2, 32.2' located at the level of the recirculation section 36, 36'.

[0054] According to this configuration, each supply section 30, 30' comprises a first conduit connecting the first reservoir 20 and the first pump 34, 34', a second conduit connecting the first pump 34, 34' and the branch 30.3, 30.3', a third conduit connecting the branch 30.3, 30.3' and the check valve 32.1, 32.1', a fourth conduit connecting the check valve 32.1, 32.1' and the second reservoir 22, a fifth conduit connecting the branch 30.3, 30.3' and the first regulating valve 32.2, 32.2' and a sixth conduit connecting the first regulating valve 32.2, 32.2' and the first reservoir 20.

[0055] Alternatively, the first regulating valve 32.2, 32.2' could be provided between the branch 30.3, 30.3' and the check valve 32.1, 32.1'.

[0056] According to another configuration visible in [Fig. 6], each supply section 30, 30', 30" comprises, from upstream to downstream, at least one first pump 34, 34', 34", a first regulating valve 32.2, 32.2', 32.2" and a non-return valve 32.1, 32.1', 32.1". According to this configuration, each supply section 30, 30', 30" comprises a first conduit connecting the first tank 20 and at least one first pump 34, 34', 34", a second conduit connecting said at least one pump 34, 34', 34" and the first regulating valve 32.2, 32.2', 32.2", a third conduit connecting the first regulating valve 32.2, 32.2', 32.2" and the check valve 32.1, 32.1', 32.1" and a fourth conduit connecting the check valve 32.1, 32.1', 32.1" and the second tank 22.

[0057] According to embodiments visible in Figures 2 and 5, at least one supply section 30, 30' comprises a single first pump 34. Alternatively, as illustrated in [Fig.6], at least one supply section 30, 30' comprises two first pumps 34 to form two compression stages.

[0058] According to one embodiment, the upstream part 26 comprises at least one return section 38, 38' which extends from a first end 38.1 connected to the second tank 22 to a second end 38.2 connected to the first tank 20. In the return section 38, 38', hydrogen flows from the second tank 22 to the first tank 20.

[0059] Each return section 38, 38' includes at least one second hydrogen flow control system 40, 40' configured to regulate the amount of hydrogen flowing from the second tank 22 to the first tank 24, the amount of hydrogen being regulated by controlling the mass or volumetric flow rate, for example. In one configuration, each second hydrogen flow control system 40, 40' includes at least one second regulating valve 40.1, 40.1'. It is not necessary to provide a pump at the return section 38, 38', as the hydrogen flows naturally from the second tank 22 to the first tank 20 due to the pressure difference between the two tanks 20, 22.

[0060] According to one configuration, at least one return section 38, 38' comprises at least one first thermal regulation system 42 configured to regulate the temperature of the hydrogen returning to the first tank 20. By way of example, this first thermal regulation system 42 is a heat exchanger.

[0061] According to an embodiment visible in [Fig. 2], each return section 38, 38' comprises a first conduit connecting the second reservoir 22 and the second valve of regulation 40.1, a second conduit connecting the second control valve 40.1 and the first thermal control system 42 and a third conduit connecting the first thermal control system 42 and the first tank 20.

[0062] Each return section 38, 38' allows the pressure and temperature of the hydrogen present in the first tank to be managed by introducing hydrogen from the second tank 22.

[0063] Providing at least one return section 38, 38' allows the first tank 20 to be returned to an optimal operating state after a particular event such as a pressure loss during a fuel sloshing event in the first tank 20 for example, the second tank 22 supplying hydrogen to the first tank 20.

[0064] According to one embodiment, the second tank 22 comprises at least one second thermal control system 44 configured to regulate the temperature and / or pressure of the hydrogen present in the second tank 22. According to a configuration shown in Figures 2 and 5, the second tank 22 comprises a single second thermal control system 44. According to another configuration shown in [Fig. 6], the second tank 22 comprises two second thermal control systems 44, 44'. By way of example, each second thermal control system 44, 44' is a heat exchanger.

[0065] This second thermal regulation system 44, when activated, maintains the hydrogen pressure in the second tank 22 even if the latter is not supplied with hydrogen by the first tank 20 and supplies hydrogen to the hydrogen system 16.

[0066] Each downstream part 28 has a first end 28.1 opening into the second tank 22 and a second end 28.2 connected to the inlet 16.1 of the hydrogen system 16. According to one embodiment, each downstream part 28 comprises at least one thermal control system 46 configured to bring the hydrogen exiting the second tank 22 to an inlet temperature adapted to the operating temperature of the hydrogen system 16 and / or at least one hydrogen flow control system 48, such as a valve for example, configured to regulate a quantity of hydrogen supplied to the hydrogen system 16. By way of example, the thermal control system 46 is a heat exchanger.

[0067] According to embodiments visible in figures 2 and 5, the downstream part 28 comprises a first conduit connecting the second reservoir 22 and the thermal regulation system 46, a second conduit connecting the thermal regulation system 46 and the hydrogen flow regulation system 48, and a third conduit connecting the hydrogen flow regulation system 48 and the hydrogen system 16.

[0068] According to another embodiment visible in [Fig. 6], the hydrogen flow control system 48 is located upstream of the thermal control system 46. The downstream part 28 comprises a first conduit connecting the second tank 22 and the hydrogen flow control system 48, a second conduit connecting the hydrogen flow control system 48 and the thermal control system 46, and a third conduit connecting the thermal control system 46 and the hydrogen system 16. By way of example, the downstream part 28 comprises a heating circuit 50 passing through the thermal control system 46 in which a heat transfer fluid circulates, the heating circuit comprising a pump 50.1 and at least one heat exchanger 50.2 positioned, for example, in an airflow exiting an aircraft engine.

[0069] Given the temperature of hydrogen and its gaseous state in the downstream part 28, the conduits and equipment in this downstream part 28 are simplified and do not need to be insulated like conduits or equipment in contact with liquid hydrogen and at a cryogenic temperature.

[0070] Regardless of the embodiment, the upstream portion 26 includes at least one supply section 30, 30', 30”, connecting the first and second tanks 20, 22, which includes at least one first hydrogen flow control system 32, 32', 32” configured to regulate a quantity of hydrogen flowing from the first tank 20 to the second tank 22, the quantity of hydrogen being regulated by controlling the mass or volumetric flow rate of the hydrogen flow between the first and second tanks 20, 22.

[0071] Thus, the majority of the hydrogen is stored in liquid form in the first tank 20.

[0072] When the hydrogen system 16 needs to be supplied with hydrogen, the first hydrogen flow control system 32, 32', 32", more particularly its first pump 34, 34', 34", compresses the hydrogen at the outlet of the first tank 20 to a pressure equal to that of the supercritical hydrogen stored in the second tank 22, the first control valve 32.2, 32.2', 32.2" being closed or nearly closed. When the first pump 34, 34', 34" is no longer supplying hydrogen to the second tank 22, it is possible to maintain the temperature of the first pump 34, 34', 34" by means of a small recirculation of hydrogen through the first pump 34, 34', 34'' which returns to the first tank 20 via the recirculation section 36, 36', the first regulating valve 32.2, 32.2', 32.2” being open.

[0073] According to a preferred configuration, hydrogen is stored in the second tank 22 at a high pressure greater than or equal to the operating pressure of the hydrogen system(s) 16. Thus, the latter are supplied with hydrogen even in the event of a malfunction of the first hydrogen flow regulation system 32, 32', 32”.

[0074] This privileged configuration allows you to: a. to complete a maneuver, takeoff or mission after the loss of the first tank 20 or the first hydrogen flow control system 32, 32', 32”, or b. allow time for the first hydrogen flow control system 32, 32', 32" to reconfigure itself in the event of a failure of one of these components.

[0075] In the presence of a return section 38, if the pressure of the hydrogen in the first tank 20 needs to be increased or its temperature adjusted, it is possible to use the hydrogen in the second tank 22 to supply the first tank 20. Thus, the second tank 22 and the return section 38 allow the first tank 20 to be returned to an optimal operating state.

[0076] According to a configuration visible in [Fig.2], the upstream part 26 comprises a single supply section 30 which includes a single first hydrogen flow regulation system 32.

[0077] According to other configurations, the upstream part 26 comprises several supply sections 30, 30', 30", each of them being adapted to at least one phase of flight of an aircraft and comprising different or identical hydrogen flow control systems 32, 32', 32'' and / or operating differently.

[0078] According to a configuration visible on [Fig.5], the upstream part 26 comprises two identical supply sections 30, 30'.

[0079] According to a first configuration, in the presence of at least one first and second supply sections 30, 30' identical, the second supply section 30' is only implemented in the event of failure of the first supply section 30.

[0080] According to a second configuration, the two supply sections are used simultaneously for all flight phases of an aircraft by adapting the quantity (volume or mass) of hydrogen flowing from the first tank 20 to the second tank 22 according to the flight phase considered.

[0081] When the hydrogen requirement of the hydrogen system(s) 16 is maximum, such as during an aircraft takeoff phase for example, the hydrogen flow control system 32, 32' of each supply section 30, 30' operates continuously at a mass flow rate adapted to maintain a constant pressure Pc in the second tank 22, as illustrated in [Fig.3].

[0082] When the hydrogen requirement of the hydrogen system(s) 16 is minimal or reduced compared to a maximum requirement, such as during a descent phase of an aircraft for example, the hydrogen flow control system 32, 32' of each section 30, 30' operates discontinuously, as illustrated in [Fig.4]. Thus, each pump 34, 34' is activated during a first phase T1 at a given mass flow rate until the pressure in the second reservoir 22 reaches a first value Psi. When this value is reached, each pump 34, 34' is stopped during a second phase T2 until the pressure in the second reservoir 22 drops to a second value Ps2. Then, each pump 34, 34' is reactivated.

[0083] Optionally, to reduce the number of cycles, the thermal regulation system 44 located in the second tank 22 is activated to increase the pressure in the second tank 22 without necessarily reactivating the first pump 34, 34'.

[0084] Furthermore, the quantity of hydrogen flowing from the second tank 22 to the first tank 20 is adjusted by controlling the mass or volumetric flow rate through the return section 38, 38' and back into the first tank 20 by means of each second regulating valve 40.1, 40.1'. The quantity of hydrogen returning to the first tank 20 is adjusted, in particular, according to the pressurization requirement of the first tank 20 so that the latter always operates under optimal conditions.

[0085] Regardless of the mode of operation, when the hydrogen supply device 18 comprises several supply sections 30, 30', 30" each comprising at least one first hydrogen flow control system 32, 32', 32", one method of operating the hydrogen supply device 18 consists of operating said first hydrogen flow control systems 32, 32', 32" according to the flight phases of the aircraft.According to one mode of operation, for at least one first flight phase, at least one first hydrogen flow control system 32 among the various hydrogen flow control systems 32, 32', 32" operates continuously to maintain a constant pressure Pc in the second tank 22 and, for at least one second flight phase different from the first flight phase, at least one second hydrogen flow control system 32' among the various hydrogen flow control systems 32, 32', 32" operates discontinuously in order to maintain a pressure between minimum and maximum pressures in the second tank 22.

[0086] Of course, the invention is not limited to this number of feed sections 30, 30', 30". Thus, the upstream portion 26 may include feed sections 30, 30', 30" which may be identical or different and / or operate in the same or different ways. The upstream portion 26 may include redundant first and second feed sections 30, 30' intended for the same flight phase(s). In this case, the hydrogen flow control system 32' the second supply section 30' only operates in the event of a malfunction of the hydrogen flow regulation system 32 of the first supply section 30.

Claims

Demands

1. Hydrogen supply device (18) comprising at least one first reservoir (20) configured to store hydrogen in a liquid state and at a pressure below 13 bar, preferably below 6 bar, and at least one inlet line (24) having a first end connected to the first reservoir (20) and at least one second end configured to be connected to an inlet (16.1) of a hydrogen system (16) operating at an operating pressure and temperature; characterized in that the inlet line (24) comprises: a. at least one second reservoir (22) configured to store hydrogen in a supercritical state and at a pressure greater than or equal to 13 bar, b.at least one upstream portion (26) comprising at least one feed section (30, 30', 30") which connects the first and second tanks (20, 22) and includes at least one first hydrogen flow control system (32, 32', 32") configured to regulate an amount of hydrogen flowing from the first tank (20) to the second tank (22), i.e. at least one downstream portion (28) connecting the second tank (22) and the second end of the inlet line (24).

2. Hydrogen supply device (18) according to claim 1, characterized in that the second reservoir (22) is configured to store hydrogen at a pressure higher than the operating pressure of the hydrogen system (16).

3. Hydrogen supply device (18) according to any one of the preceding claims, characterized in that the second tank (22) has a volume at least five times smaller than that of the first tank (20).

4. Hydrogen supply device (18) according to any one of the preceding claims, characterized in that the first hydrogen flow control system (32, 32', 32") comprises at least one first pump (34, 34', 34"), at least one first control valve (32.2, 32.2', 32.2") and at least one check valve (32.1, 32.1', 32.1").

5. Hydrogen supply device (18) according to the preceding claim, characterized in that at least a first hydrogen flow control system (32, 32') comprises a recirculation section (36, 36') which extends from a branch (30.3, 30.3'), provided between the first pump (34, 34') and the check valve (32.1, 32.1'), to the first tank (20), the first control valve (32.2, 32.2') being located at the level of the recirculation section (36, 36') or between the branch (30.3, 30.3') and the check valve (32.1, 32.1').

6. Hydrogen supply device (18) according to any one of the preceding claims, characterized in that the upstream part (26) comprises at least one return section (38, 38') connecting the first and second tanks (20, 22) in which hydrogen flows from the second tank (22) to the first tank (20) in operation.

7. Hydrogen supply device (18) according to the preceding claim, characterized in that the return section (38, 38') comprises at least one second hydrogen flow control system (40, 40') configured to regulate a quantity of hydrogen flowing from the second tank (22) to the first tank (24) and / or at least one first thermal control system (42) configured to regulate the temperature of the hydrogen returning to the first tank (20).

8. Hydrogen supply device (18) according to any one of the preceding claims, characterized in that the second tank (22) comprises at least one second thermal control system (44) configured to regulate the temperature and / or pressure of the hydrogen present in the second tank (22).

9. Hydrogen supply device (18) according to any one of the preceding claims, characterized in that the downstream part (28) comprises at least one thermal control system (46) configured to bring the hydrogen exiting the second tank (22) to an inlet temperature suitable for the operating temperature of the hydrogen system (16) and / or at least one hydrogen flow control system (48) configured to regulate a quantity of hydrogen supplied to the hydrogen system (16).

10. Aircraft comprising at least one hydrogen supply device (18) according to any one of the preceding claims.

11. A method of operating a hydrogen supply device (18) according to any one of claims 1 to 9, said hydrogen supply device (18) supplying at least one hydrogen system (16) of an aircraft and comprising at least one first tank (20) configured to store hydrogen in a liquid state and at a pressure below 13 bar, preferably below 6 bar, and at least one inlet line (24) connecting the first tank (20) and the hydrogen system (16); characterized in that the inlet line (24) comprises: a. at least one second tank (22) configured to store hydrogen in a supercritical state and at a pressure greater than or equal to 13 bar, b.at least an upstream portion (26) comprising several supply sections (30, 30', 30") each connecting the first and second tanks (20, 22) and each comprising at least one first hydrogen flow control system (32, 32', 32") configured to regulate a quantity of hydrogen flowing from the first tank (20) to the second tank (22), c. at least a downstream portion (28) connecting the second tank (22) and the second end of the inlet line (24), d. and in that the method of operating the hydrogen supply device (18) consists of operating said first hydrogen flow control systems (32, 32', 32") according to the flight phases of the aircraft.

12. A method of operation according to the preceding claim, characterized in that, for at least one first phase of aircraft flight, at least one first hydrogen flow control system (32) among the various hydrogen flow control systems (32, 32', 32") operates continuously to maintain a constant pressure (Pc) in the second tank (22), and in that, for at least one second phase of flight different from the first phase of flight, at least one second hydrogen flow control system (32') among the various hydrogen flow control systems (32, 32', 32") operate discontinuously in order to maintain a pressure between minimum and maximum pressures in the second tank (22).

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