Fuel supply system comprising at least two tanks of hydrogen in liquid form and at different pressures

Abstract

Fuel supply device comprising at least two hydrogen tanks in liquid form and at different pressures. The invention relates to a fuel supply device (18) configured to supply hydrogen to at least one hydrogen system (16) operating at an operating pressure, said fuel supply device (18) comprising: at least one first tank (20) configured to store hydrogen in a liquid state and at a pressure lower than the operating pressure; at least one main line (24) connecting the first tank (20) and the hydrogen system (16); at least one second tank (22) configured to store hydrogen in a liquid state and at a pressure higher than the operating pressure, supplying hydrogen to the main line (24). The invention also relates to an aircraft comprising at least one such fuel supply device. Figure 2

Description

Title of the invention: Fuel supply device comprising at least two tanks of hydrogen in liquid form and at different pressures

[0001] The present application relates to a fuel supply device comprising at least two tanks of hydrogen in liquid form and at different pressures and to an aircraft comprising at least one such supply device.

[0002] According to one embodiment, an aircraft powering device includes at least one hydrogen tank and at least one distribution circuit connecting the hydrogen tank and at least one hydrogen-powered 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 must withstand a lower pressure), the tank remains bulky (the density of hydrogen is lower compared to the first embodiment) and its mass is greater than that of the tank of the first embodiment (the tank must 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 supply device configured to supply hydrogen to at least one hydrogen system operating at an operating pressure, said supply device comprising: a. at least one first tank configured to store hydrogen in a liquid state and at a pressure lower than the operating pressure, said first tank having at least one outlet port, b. at least one main line extending from an upstream end connected to the outlet of the first tank to at least one downstream end configured to be connected to a hydrogen system, c. at least one pump located on the main line and configured to compress the hydrogen exiting the first tank to a pressure greater than or equal to the operating pressure, d. at least one main thermal control system located upstream of the downstream end of the main line.

[0010] According to the invention, the supply device includes at least one second tank configured to store hydrogen in a liquid state and at a pressure higher than the operating pressure, this second tank supplying hydrogen to the main line between the pump and the main thermal control system.

[0011] This solution combines the advantages of the first and second embodiments of the prior art. The first reservoir provides a supply similar to prior art devices that store hydrogen in liquid form, thus helping to limit the volume and mass of the reservoir for an equivalent amount of energy. The second reservoir helps to simplify the supply device. The invention also reduces the number of components in the supply device.

[0012] According to another feature, the main line comprises a bifurcation point located at the upstream and downstream ends, an upstream section extending from the upstream end of the main line to the bifurcation point, and at least one downstream section extending from the bifurcation point to the downstream end of the main line. The first reservoir comprises at least one inlet port through which hydrogen is introduced into the first reservoir. In addition, the supply device comprises at least one return line connecting the bifurcation point to the inlet port of the first reservoir, as well as a system for controlling the hydrogen flow in the upstream and downstream sections and in the return line.

[0013] According to another feature, the hydrogen flow control system includes at least one first valve at the upstream section, at least one second valve at the return line and at least one third valve at the downstream section, each of the first, second and third valves being configured to adjust the flow of hydrogen passing through it.

[0014] According to another feature, the power supply device includes at least one first thermal regulation system located at the return line.

[0015] According to another feature, the second reservoir is located at the return line and includes at least one outlet port connected to the inlet port of the first reservoir as well as at least one combined port connected to the bifurcation point.

[0016] According to another feature, the second reservoir is located between the bifurcation point and the first thermal regulation system.

[0017] According to another feature, the second reservoir is located at the downstream section and includes at least one outlet connected to the downstream end of the main line and at least one inlet connected to the bifurcation point.

[0018] According to another feature, the third valve is interposed between the second tank and the bifurcation point, the supply device comprising a fourth valve located between the second tank and the main thermal control system.

[0019] According to another feature, the feeding device includes at least one second regulating system located in the second tank.

[0020] According to another feature, the main line comprises several downstream ends as well as several distinct branches, one for each downstream end, each branch comprising a main thermal regulation system.

[0021] The invention also relates to an aircraft comprising at least one power supply device according to one of the preceding characteristics and at least one hydrogen system supplied with hydrogen by the power supply device.

[0022] 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:

[0023] [Fig-1] is a side view of an aircraft,

[0024] [Fig.2] is a schematic representation of a power supply device hydrogen from an aircraft illustrating a first embodiment of the invention according to a normal operating mode,

[0025] [Fig.3] is a schematic representation of the power supply device visible in [Fig.2] according to an operating mode in the presence of a fault,

[0026] [Fig.4] is a schematic representation of the power supply device visible in [Fig.2] according to an operating mode adapted to a ground rolling phase,

[0027] [Fig.5] is a schematic representation of the power supply device visible in [Fig.2] according to a first operating mode adapted to a takeoff phase,

[0028] [Fig.6] is a schematic representation of the power supply device visible in [Fig.2] according to a second operating mode adapted to a takeoff phase,

[0029] [Fig.7] is a schematic representation of an aircraft hydrogen supply device illustrating a second embodiment of the invention according to a normal operating mode,

[0030] [Fig.8] is a schematic representation of the power supply device visible in [Fig.7] according to an operating mode in the presence of a fault,

[0031] [Fig.9] is a schematic representation of the power supply device visible in [Fig.7] according to an operating mode adapted to a ground rolling phase,

[0032] [Fig. 10] is a schematic representation of the power supply device visible on [Fig.7] according to a first operating mode adapted to a takeoff phase,

[0033] [Fig. 11] is a schematic representation of the power supply device visible on [Fig.7] according to a second operating mode adapted to a takeoff phase,

[0034] [Fig. 12] is a schematic representation of two hydrogen supply devices of an aircraft intended to supply four hydrogen systems.

[0035] As illustrated in [Fig.1], an aircraft 10 comprises several propulsion units 12 located under the wings 14 and connected to them.

[0036] According to one configuration, at least one of the propulsion assemblies 12 includes an electric motor powered by electrical energy from at least one fuel cell.

[0037] According to another configuration, at least one of the propulsion assemblies 12 comprises a hydrogen-powered turbojet or turboprop.

[0038] Regardless of the embodiment, the aircraft 10 comprises at least one hydrogen system 16 (visible in Figures 2 to 12) consuming hydrogen and at least one hydrogen supply device 18 configured to supply the hydrogen system(s) 16. According to one embodiment visible in [Fig. 12], the aircraft comprises two supply devices 18 each connected to two hydrogen systems 16.

[0039] Each hydrogen system 16 includes at least one inlet 16.1 and operates at a given operating pressure.

[0040] The supply device 18 comprises at least a first tank 20 configured to store hydrogen in liquid form and at low pressure and at least a second tank 22 configured to store hydrogen in liquid form and at medium pressure.

[0041] By low pressure, we mean a pressure between 1 and 6 bars, preferably in the order of 4 bars.

[0042] By average pressure, we mean a pressure higher than the low pressure and greater than or equal to the operating pressure of the hydrogen system(s). The average pressure is between 6 and 10 bar, preferably equal to about 8 bar.

[0043] In the first and second tanks 20, 22, hydrogen is stored at a cryogenic temperature of approximately -253°C. Storing hydrogen in liquid form allows for a reduction in the dimensions of each of the first and second tanks 20, 22, which contributes to reducing the onboard mass.

[0044] 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.

[0045] According to one embodiment, the first reservoir 20 comprises at least one outlet 20.1 through which hydrogen exits in liquid form. According to one configuration, the first reservoir 20 comprises at least one inlet 20.2 through which hydrogen is introduced into the first reservoir 20.

[0046] The supply device 18 includes a main line 24 connecting the first tank 20 and at least one hydrogen system 16. According to one embodiment, the main line 24 includes an upstream end 24.1 connected to the outlet port 20.1 of the first tank 20 and a downstream end 24.2 connected to the inlet 16.1 of the hydrogen system 16.

[0047] The supply device 18 includes at least one return line 26 connecting the first tank 20 and the main line 24 at a branch point 28 located away from the first tank 20 and the hydrogen system 16. In one embodiment, the return line 26 includes a first end 26.1 connected to the branch point 28 and a second end 26.2 connected to the inlet 20.2 of the first tank 20. The main line 24 includes an upstream section 28.1 extending from the first tank 20 (or the upstream end 24.1 of the main line 24) to the branch point 28 and at least one downstream section 28.2 extending from the branch point 28 to the hydrogen system(s) 16 (or the downstream end 24.2 of the main line). 24).

[0048] According to a configuration visible in [Fig. 12], when supplying several hydrogen systems 16, the main line 24 comprises several downstream ends 24.2 as well as several distinct branches 30.1, 30.2, one for each downstream end 24.2. Thus, the main line 24 comprises, from upstream to downstream, an upstream section 28.1, a common downstream section 28.2 extending from the bifurcation point 28, and then a branch 30.1, 30.2 for each hydrogen system 16 connecting to the downstream section 28.2 common and the corresponding hydrogen system 16 (or the downstream end 24.2 of the main line 24.

[0049] The supply device 18 includes a hydrogen flow control system in the upstream and downstream sections 28.1, 28.2 and the return line 26. According to one configuration, the supply device 18 includes at least one first valve 32.1 at the upstream section 28.1, at least one second valve 32.2 at the return line 26 and at least one third valve 32.3 at the downstream section 28.2. Each of the first, second and third valves 32.1, 32.2, 32.3 is configured to adjust the flow rate of the hydrogen passing through it.

[0050] According to one arrangement, the third valve 32.3 is positioned just downstream of the bifurcation point 28. Thus, no element is interposed between the bifurcation point 28 and the third valve 32.3. According to one arrangement, in the presence of several hydrogen systems 16, the third valve 32.3 is located at the common downstream section 28.2 and not at the branches 30.1, 30.2.

[0051] According to one embodiment, the supply device 18 includes at least one pump 34 located at the upstream section 28.1, just downstream of the outlet 20.1 of the first tank 20. The supply device 18 includes at least one main thermal control system 36, such as a heat exchanger for example, located at the downstream section 28.2, just upstream of the downstream end 24.2 of the main line 24 or of the inlet 16.1 of the hydrogen system 16. According to one arrangement, in the presence of several hydrogen systems 16, the supply device 18 includes a main thermal control system 36 for each hydrogen system 16, located at each branch 30.1, 30.2.

[0052] In one configuration, the feed device 18 includes at least one first thermal control system 38, located at the return line 26, configured to regulate the temperature of the hydrogen circulating in the return line 26 and reintroduced into the first tank 20. In one operating mode, the first thermal control system 38 is configured to regulate the temperature of the hydrogen circulating in the return line 26 so as to evaporate the liquid hydrogen into gaseous hydrogen at a temperature greater than or equal to the temperature of the hydrogen in the first tank 20 in order to increase the hydrogen pressure and subcool the first tank 20 (which allows for proper operation of the pumps). In one arrangement, the first thermal control system 38 is located between the bifurcation point 28 and the second valve 32.2.

[0053] According to one embodiment, the supply device 18 comprises at least a second control system 40 located in the second tank 22 and configured to regulate the hydrogen pressure in the second tank 22, in certain operating methods, in order to trigger, by an increase in the temperature of the hydrogen (by adding heat), an evaporation of at least part of the liquid hydrogen into gaseous hydrogen in said second tank 22.

[0054] The first and second control systems 38, 40 can be of electrical or other type.

[0055] According to a first embodiment visible in Figures 2 to 6, the first and second tanks 20, 22 are positioned in parallel, the second tank 22 being located at the return line 26. In this case, the second tank 22 comprises at least one outlet 22.1 connected to the inlet 20.2 of the first tank 20 as well as at least one combined orifice 22.2, ensuring the outlet or inlet of hydrogen into the second tank 22, connected to the bifurcation point 28. According to one arrangement, the second tank 22 is located between the bifurcation point 28 and the first thermal regulation system 38.

[0056] According to a so-called normal operating mode illustrated in [Fig. 2], during flight and in the absence of any failure(s), hydrogen exits the first tank 20 at low pressure. Upon exiting, the hydrogen passes through the pump 34 to be compressed and reach a higher pressure suitable for the hydrogen system(s) 16 and the second tank 22. At the bifurcation point 28, a first portion of the hydrogen exiting the pump 34 is introduced into the second tank 22, and a second portion of the hydrogen is transferred to the hydrogen system(s) 16.

[0057] The second control system 40 is not necessarily activated. It allows, if necessary, the hydrogen in the second tank 22 to be heated and its pressure to be regulated within this second tank 22. The pressure of the hydrogen in the second tank 22 can also be regulated by adjusting the amount of hydrogen entering the second tank 22 using the first and third valves 32.1, 32.3, as well as the amount of hydrogen leaving the second tank 22 using the second valve 32.2. According to this normal operating mode, each hydrogen system 16 is supplied with hydrogen solely by the first tank 20, the hydrogen leaving the first tank 20 being compressed by the pump 34 to increase its pressure to a pressure greater than or equal to the operating pressure of the hydrogen system(s) 16.

[0058] According to a degraded operating mode illustrated in [Fig. 3], in the event of a failure, when at least one element of the pump 34 and the first thermal control system 38 is faulty, the first tank 22 is isolated by closing the first and second valves 32.1, 32.2. In this case, the second control system 40 can be activated. The hydrogen pressure in the second tank 22 being greater than or equal to the operating pressure of the system(s) at hydrogen 16, the second tank 22 supplies, without a pump, the hydrogen 16 system(s).

[0059] According to an operating mode adapted to a ground taxiing phase and illustrated in [Fig. 4], the first tank 22 is isolated by closing the first and second valves 32.1, 32.2 after landing. In addition, the pump 38 and the first thermal control system 38 are shut down. Since the hydrogen pressure in the second tank 22 is greater than or equal to the operating pressure of the hydrogen system(s) 16, the second tank 22 supplies the hydrogen system(s) 16 without a pump. Thus, the majority of the hydrogen in the second tank 22 is consumed prior to a ground refueling phase before the next flight. This solution optimizes the amount of hydrogen stored in the first and second tanks 20, 22 for a flight.

[0060] According to a first operating mode adapted to a takeoff phase illustrated in [Fig. 5], the hydrogen exiting the first tank 20 is compressed by the pump 34 to a pressure suitable for the hydrogen system(s) 16 and the second tank 22, as in the normal operating mode. The hydrogen in the second tank 22 flows towards the first tank 20 and / or the hydrogen system(s) 16. The second control system 40 may not be activated. According to this first operating mode adapted to a takeoff phase, each hydrogen system 16 can be simultaneously supplied with hydrogen from the first and second tanks 20, 22.

[0061] According to a second operating mode adapted to a takeoff phase illustrated in [Fig. 6], each hydrogen system 16 is supplied with hydrogen only from the second tank 22 and not from the first tank 20. The pump 34 is therefore off and the first valve 32.1 is closed. In this case, the second control system 40 is activated to heat the hydrogen present in the second tank 22.

[0062] As illustrated in [Fig.6], the second tank 22 can also be used to supply the first tank 20 by opening the second valve 32.2. This mode of operation can be extended until the pressure in the second tank 22 is no longer sufficient to supply the hydrogen system(s) 16.

[0063] According to a second embodiment shown in Figures 7 to 12, the first and second reservoirs 20, 22 are positioned in series, the second reservoir 22 being located at the downstream section 28.2, more particularly at the common trunk of the downstream section 28.2 located upstream of branches 30.1, 30.2. In this case, the second reservoir 22 includes at least one outlet 22.1' connected to the downstream end 24.2 of the main line 24 as well as at least one inlet port 22.2' connected to the bifurcation point 28.

[0064] According to this second embodiment, the third valve 32.3 is interposed between the second reservoir 22 and the bifurcation point 28. In addition, the supply device 18 includes a fourth valve 32.4 located at the outlet of the second reservoir 22, more particularly between the second reservoir 22 and the main thermal regulation system(s).

[0065] According to a so-called normal operating mode illustrated in [Fig. 7], during flight and in the absence of any failure(s), hydrogen exits the first tank 20 at low pressure. Upon exiting, the hydrogen passes through the pump 34 to reach a higher pressure suitable for the hydrogen system(s) 16 and the second tank 22.

[0066] The hydrogen exiting the pump 34 feeds in cascade the second tank 22 which itself feeds the hydrogen system(s) 16. The second regulation system 40 is not necessarily activated.

[0067] Depending on the circumstances, part of the hydrogen exiting the pump 34 is reintroduced into the first tank 20 via the return line 26 by adjusting the flow of the second and third valves 32.2, 32.3.

[0068] According to a degraded operating mode illustrated in [Fig. 8], in the event of a failure, when at least one element of the pump 34 and the first thermal control system 38 is faulty, the first tank 22 is isolated by closing the first and second valves 32.1, 32.2. In this case, the second control system 40 is generally activated. Since the hydrogen pressure in the second tank 22 is greater than or equal to the operating pressure of the hydrogen system(s) 16, the second tank 22 supplies the hydrogen system(s) 16 without pumping.

[0069] According to an operating mode adapted to a ground taxiing phase illustrated in [Fig. 9], the first tank 22 is isolated by closing the first and second valves 32.1, 32.2 after landing. In addition, the pump 38 and the first thermal control system 38 are shut down. Since the hydrogen pressure in the second tank 22 is greater than or equal to the operating pressure of the hydrogen system(s) 16, the second tank 22 supplies the hydrogen system(s) 16 without pumping. Thus, the majority of the hydrogen in the second tank 22 is consumed prior to a ground refueling phase before the next flight. This solution optimizes the amount of hydrogen stored in the first and second tanks 20, 22 for a flight.

[0070] According to a first operating mode adapted to a takeoff phase and illustrated in [Fig. 10], the hydrogen exiting the first tank 20 is compressed by the pump 34 to a pressure suitable for the hydrogen system(s) 16 and the second reservoir 22, as in normal operating mode. The hydrogen exiting pump 34 cascades into the second reservoir 22, which in turn supplies the hydrogen system(s) 16. The second control system 40 is not necessarily activated.

[0071] Depending on the circumstances, part of the hydrogen exiting the pump 34 is reintroduced into the first tank 20 via the return line 26 by adjusting the flow of the second and third valves 32.2, 32.3.

[0072] According to a second operating mode adapted to a takeoff phase and illustrated in [Fig. 1 1], each hydrogen system 16 is supplied with hydrogen only by the second tank 22 and not by the first tank 20. The latter is isolated from the downstream section 28.1 by closing the third valve 32.3. The first tank 20 can be subcooled by injection of gaseous hydrogen via the pump 34 and the thermal regulation system 38 (independent of the second tank 22 and the hydrogen system 16).

[0073] The hydrogen exiting the first tank 20 is compressed by the pump 34 and then reintroduced into the first tank 20 via the return line 26. The first thermal regulation system 38 can be activated and the first and second valves 32.2 are in the open state.

[0074] In this case, the second control system 40 is activated to heat the hydrogen present in the second tank 22. The operating mode can be extended until the pressure in the second tank 22 is no longer sufficient to supply the hydrogen system(s) 16.

[0075] Regardless of the embodiment, a supply device 18 configured to supply hydrogen to at least one hydrogen system 16 operating at an operating pressure comprises: a. at least one first tank 20 configured to store hydrogen in liquid form and at a pressure lower than the operating pressure, said first tank 20 having at least one outlet port 20.1, b. at least one main line 24 extending from an upstream end 24.1 connected to the outlet port 20.1 of the first tank 20 to at least one downstream end 24.2 configured to be connected to the hydrogen system 16, c. at least one pump 34 located on the main line 24 and configured to compress the hydrogen exiting the first tank 20 to a pressure greater than or equal to the operating pressure, d. at least one main thermal control system 34 located upstream of the downstream end 24.2 of the main line 24, e. at least one second tank 22 configured to store hydrogen, in liquid form and at a pressure higher than the operating pressure, supplying hydrogen to the main line between pump 34 and the main thermal control system 36.

[0076] This solution combines the advantages of the first and second prior art embodiments. The first reservoir 20 provides a supply similar to prior art devices storing hydrogen in liquid form, which helps to limit the volume and mass of the reservoir for an equivalent amount of energy. The second reservoir 22 provides a supply similar to the device in the second prior art embodiment storing hydrogen in liquid form and at a pressure higher than the operating pressure, which helps to simplify the supply device.

[0077] The invention makes it possible to reduce the number of components, some of which provide a redundancy function as well as a modulation function for the quantity of hydrogen supplied, which helps to simplify the supply system while maintaining a high level of safety. Thus, the second tank 22 allows the first tank 20 to be duplicated in the event of a malfunction of the latter and / or of the pump 34, but also to participate in regulating the quantity of hydrogen transmitted to the hydrogen system(s) 16 during specific phases of flight such as takeoff and taxiing.

[0078] According to a preferred embodiment, the supply device 18 includes a return line 26 allowing a portion of the hydrogen exiting the first tank 20 to be reintroduced into the latter, which helps to simplify the regulation of the quantity of hydrogen transmitted to each hydrogen system 16, more particularly the quantity of hydrogen exiting the first tank 20 and passing through the pump 34 which can then be substantially constant.

Claims

Demands

1. A power supply device (18) configured to supply hydrogen to at least one hydrogen system (16) operating at an operating pressure, said power supply device (18) comprising: a. at least one first tank (20) configured to store hydrogen in a liquid state and at a pressure lower than the operating pressure, said first tank (20) having at least one outlet port (20.1), b. at least one main line (24) extending from an upstream end (24.1) connected to the outlet port (20.1) of the first tank (20) to at least one downstream end (24.2) configured to be connected to a hydrogen system (16), c. at least one pump (34) located on the main line (24) and configured to compress the hydrogen exiting the first tank (20) to a pressure greater than or equal to the operating pressure, d. at least one main thermal control system (36) located upstream of the downstream end (24.2) of the main line (24); e. characterized in that the supply device (18) comprises at least one second tank (22) configured to store hydrogen in a liquid state and at a pressure higher than the operating pressure, said second tank (22) supplying hydrogen to the main line (24) between the pump (34) and the main thermal control system (36).

2. A feeding device (18) according to claim 1, characterized in that the main line (24) comprises a bifurcation point (28) located at a distance from the upstream and downstream ends (24.1, 24.2), an upstream section (28.1) extending between the upstream end (24.1) of the main line (24) and the bifurcation point (28), and at least one downstream section (28.2) extending between the bifurcation point (28) and the downstream end (24.2) of the main line (24), in that the first reservoir (20) comprises at least one inlet port (20.2) through which hydrogen is introduced into the first reservoir (20), and in that the feeding device (18) comprises at least a return line (26) connecting the bifurcation point (28) and the inlet port (20.2) of the first reservoir (20) and a hydrogen flow control system in the upstream and downstream sections (28.1, 28.2) as well as in the return line (26).

3. Feeding device (18) according to the preceding claim, characterized in that the hydrogen flow control system comprises at least one first valve (32.1) at the upstream section (28.1), at least one second valve (32.2) at the return line (26) and at least one third valve (32.3) at the downstream section (28.2); each of the first, second and third valves (32.1, 32.2, 32.3) being configured to adjust the flow rate of hydrogen passing through it.

4. Power supply device (18) according to any one of claims 2 to 3, characterized in that the power supply device (18) comprises at least a first thermal regulation system (38) located at the return line (26).

5. Feeding device (18) according to any one of claims 2 to 4, characterized in that the second reservoir (22) is located at the return line (26) and includes at least one outlet port (22.1) connected to the inlet port (20.2) of the first reservoir (20) and at least one combined port (22.2) connected to the bifurcation point (28).

6. Feeding device (18) according to claims 4 and 5, characterized in that the second reservoir (22) is located between the bifurcation point (28) and the first thermal regulation system (38).

7. Feeding device (18) according to any one of claims 2 to 3, characterized in that the second reservoir (22) is located at the level of the downstream section (28.2) and includes at least one outlet port (22.1') ​​connected to the downstream end (24.2) of the main line (24) and at least one inlet port (22.2') connected to the bifurcation point (28).

8. Feeding device (18) according to the preceding claim, characterized in that the third valve (32.3) is interposed between the second reservoir (22) and the bifurcation point (28) and in that the feeding device (18) includes a fourth valve (32.4) located between the second reservoir (22) and the main thermal control system (36).

9. Feeding device (18) according to any one of the preceding claims, characterized in that the feeding device (18) comprises at least one second regulating system (40) located in the second reservoir (22).

10. Power supply device (18) according to any one of the preceding claims, characterized in that the main line (24) comprises several downstream ends (24.2) as well as several separate branches (30.1, 30.2), one for each downstream end (24.2), each branch (30.1, 30.2) comprising a main thermal regulation system (36).

11. Aircraft comprising at least one power supply device (18) according to any one of the preceding claims and at least one hydrogen system (18) supplied with hydrogen by the power supply device (18).

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