Aviation device for distributing gas

Abstract

An aviation device for distributing gas between at least one liquefied gas source and at least one gas-consuming component in an aircraft, comprising: at least one first controlled all-or-nothing valve located at the output of each liquefied gas source; a cryogenic distributor connected to each first controlled valve and supplied with liquid; a second controlled all-or-nothing valve connected in parallel to the cryogenic distributor; a two-phase buffer vessel, each buffer vessel being supplied with liquid and gas through one of the second controlled valves; a third controlled valve installed at the output of each buffer vessel for supplying gas; a pressure reducing valve installed at the output of the third controlled valve; and a collector supplied with liquid by the pressure reducing valve to supply at least one consuming component.

Description

[0001] The present invention relates to the field of aviation.

[0002] Since the birth of the aviation industry, it has always used high-octane gasoline engines. After 1945, the development of jet engines and turbines led to the use of kerosene, which has a higher molecular weight and lower flammability than gasoline. These fuels are stored in fuel tanks in the wings, wing-fuselage joints, or tails.

[0003] The trend of reducing carbon dioxide gas emissions has led to less engine consumption. However, as certain technologies mature, especially the increase in blade tip speed, the benefits of carbon dioxide gas emissions are decreasing. The introduction of a breakthrough seems increasingly desirable.

[0004] Therefore, the gas aircraft project has emerged. Gases with short or no carbon chains produce little or no pollution when burned with oxygen. On the other hand, due to the small size of gas molecules, it is difficult to store H 2 、O 2 or C1 or C2 gases, and there is a risk of leakage.

[0005] On the ground, hydrogen, methane, ethane, ethylene, acetylene, or oxygen are usually stored in containers with too high pressure, which are too large in volume and contain too much potential pressure energy to be loaded onto an aircraft or in cryogenic containers that are welded and / or glued. The cryogenic storage time is limited and proportional to the storage volume.

[0006] In addition, gases stored in liquid form cannot be used by internal combustion engines, external combustion engines, or fuel cells. The final consumption requires the gas to be within the temperature range and pressure range specified by the consumer component manufacturer.

[0007] It is necessary to store gases in an aircraft for consumption on the aircraft.

[0008] The present invention proposes an aviation device for distributing gases between at least one liquefied gas source and at least one gas consumption member in an aircraft. The device includes at least one first controlled all-or-nothing valve located at the outlet of each liquefied gas source, a cryogenic distributor connected to each first controlled valve and supplied with liquid, a second controlled all-or-nothing valve connected in parallel with the cryogenic distributor, a two-phase buffer container supplied with liquid through one of the second controlled valves and supplied with gas, a third controlled valve installed at the output end of each buffer container for supplying gas, a pressure reducing valve installed at the output end of the third controlled valve, and a collector supplied by the pressure reducing valve to supply the at least one consumption member. According to the present invention, the aviation gas distribution device can provide the necessary autonomy for the aircraft through the volume contained in the buffer container, regardless of the state of the liquefied gas source. The buffer container can be designed for a gas pressure of several hundred bars, but the selected gas pressure is still supplied to the consumption member.

[0009] Different from the space field, where cryogenic valves are not required to be closed again after one use, a closable valve, such as a solenoid valve, is provided here.

[0010] In one embodiment, the device includes a fourth controlled valve installed at the output of each pressure reducing valve for supplying gas. A consuming member, such as an engine supplied from a single buffer container or an auxiliary device for generating electrical energy on board, whichever.

[0011] In one embodiment, the device includes at least one compressor supplied by at least one buffer container, and at least one fifth controlled valve installed between the compressor and the buffer container. The buffer container can be emptied sufficiently to increase the amount of gas available for the consuming member and to make the pressure in the buffer container at the end of the emptying lower than the normal pressure in the cryogenic container designated for filling at this time. When the corresponding first valve is opened and the other first valves are closed, the normal pressure in the cryogenic container is equal to the pressure in the distributor. Then, under the action of the pressure difference, the buffer container is filled with gas by operating the cryogenic valve. Omitting the cryogenic pump can save mass and reduce the risk of accidents.

[0012] In one embodiment, the device includes a control unit that controls at least one first controlled valve to sequentially fill and empty the buffer container by means of a pressure difference. The sequential operation enables the number of cryogenic containers and the number of buffer containers to be independent. At least one cryogenic container is provided. At least two, preferably three, buffer containers are provided.

[0013] In the case of two buffer containers, one is in the emptying process, while the other is in the filling or gasification process by heating the gas.

[0014] In the case of three or more buffer containers, one is in the emptying process, the second is in the filling process, and the third is in the gasification process by heating the gas or has been filled with gas at a set pressure. The time required for gasification depends on the amount of liquid brought into the buffer container, the external temperature (which may range from -55 °C at high altitude to +60 °C on the ground), and especially the speed of the aircraft. The duration of gasification and the amount of liquid entering the buffer container can be the subject of estimated prediction.

[0015] During the gasification process, if the corresponding buffer container exceeds the maximum pressure, the control unit can request a switch to discharge the overpressurized buffer container and temporarily interrupt the emptying of another buffer container, and then resume the previous operation at the detected overpressure.

[0016] In one embodiment, to empty one of the buffer containers, the control unit first controls the third controlled valve for gas flow by means of a pressure difference and then controls the third controlled valve by starting the compressor until the pressure obtained in the buffer container is lower than the pressure present in the cryogenic distributor. The operation of the compressor is time-limited, thus saving energy.

[0017] In one embodiment, at least one of the first and second valves is cryogenic. The other valves allow the gas to pass through them at a lower temperature, for example about -55 °C at high altitudes.

[0018] In one embodiment, the device includes flow meters arranged at the output of each liquefied gas source. Measuring the liquid flow enables the management of the opening times of the first and second valves and of the distribution device to supply the required amounts.

[0019] In one embodiment, an additional flow meter is advantageously arranged at the input of the buffer container.

[0020] In one embodiment, a component includes the above-described device and at least one single cryogenic liquefied gas source. One of the cryogenic containers can be in the process of being emptied to fill the buffer container, while the other cryogenic container or containers are inactive. In the case of overpressure in the cryogenic container, priority emptying can be provided to the distribution device.

[0021] In one embodiment, an aviation method for distributing gas in an aircraft between at least one liquefied gas source and at least one gas-consuming member includes: a step of filling a buffer container with liquefied gas by means of at least one of at least one first controlled all-or-nothing valve located at the output of each liquefied gas source and one of second controlled all-or-nothing valves connected in parallel with the cryogenic distributor; a cryogenic distributor connected to each first controlled valve and supplied with liquid by the cryogenic distributor; the buffer container connected to the second open controlled valve, while the other second controlled valve or valves are closed, and a third controlled valve installed at the output of the buffer container is closed; and a step of emptying the buffer container, the second controlled valve being closed and the third controlled valve being open, and the gas flowing through a pressure-reducing valve installed at the output of the third controlled valve to supply the at least one consuming member. Using all-or-nothing valves enables the control of the amount of liquid passing through the valves by the duration of the opening.

[0022] In one embodiment, during normal operation, the first buffer container is filled with liquid by pressure equalization through at least one first open valve and one of the second valves corresponding to the open first buffer container. The third valve corresponding to the first buffer container is closed, while the second buffer container is supplying pressurized gas. The second valve corresponding to the closed second buffer container and the third valve corresponding to the first buffer container are opened. This mode applies to two buffer containers.

[0023] In one embodiment, the third buffer container is vaporizing. The second valve corresponding to the third buffer container is closed, and the third valve corresponding to the third buffer container is closed. This mode applies to three or more buffer containers.

[0024] In one embodiment, the step of emptying the buffer container includes a sub-step of emptying through a pressure reducing valve to reduce the gas pressure to the pressure required by the consumption member, and then a sub-step of emptying assisted by a pump to bring the gas pressure to the pressure required by the consumption member and make the pressure in the buffer container at the end of emptying lower than the pressure present in the cryogenic distributor. Thus, a more complete emptying of the buffer container is achieved.

[0025] In one embodiment, the capacity of the buffer container is calculated according to current standards to ensure the flight distance of the aircraft in the event of an accident affecting the energy reserve, especially if there are two buffer containers, on one buffer container, and if there are three buffer containers, on two buffer containers.

[0026] Other features and advantages of the present invention will be apparent from the following detailed description and the accompanying drawings, in which:

[0027] Figure 1 schematically shows a device having two cryogenic containers and three buffer containers according to one aspect of the present invention.

[0028] Figure 2 schematically shows a device having one cryogenic container and three buffer containers according to one aspect of the present invention.

[0029] Figure 3 schematically shows a device having one cryogenic container and three buffer containers according to one aspect of the present invention.

[0030] Figure 4 schematically shows a device having two cryogenic containers and three buffer containers according to one aspect of the present invention.

[0031] Figure 5 schematically shows a device having one cryogenic container and two buffer containers according to one aspect of the present invention. ​​​​​

[0032] The accompanying drawings can not only be used to supplement the present invention, but also help to define the present invention where applicable.

[0033] The aviation gas distribution device is designed to be carried by an aircraft: airplanes, drones, helicopters, etc. The aviation gas distribution device is supplied with liquid and supplies gas at a selected pressure. In other words, fuel or oxidizer is stored in a cryogenic container in liquid form at an extremely low temperature. As an example, the density of gaseous hydrogen at 0 °C and 1 atmosphere is about 800 times lower than that of liquid hydrogen at -253 °C, so the volume is about 800 times. Cryogenic containers are not suitable for withstanding high pressures, especially pressures above 10 bar.

[0034] The stored gas is selected from hydrogen, methane, ethane, ethylene, acetylene, and oxygen.

[0035] In addition, the maintenance rules require that most parts of the aircraft can be disassembled and repaired or replaced. Therefore, the aircraft can land anywhere suitable for its weight and landing requirements - an airport for an airplane and a helipad for a helicopter - but is not equipped with maintenance equipment specific to the aircraft model. In the event of detected damage, the aircraft is permanently or temporarily repaired, or disassembled to replace or repair defective parts, in accordance with the manufacturer's manuals and documents approved by the aviation safety authorities. It is desirable for the maintenance operator to have easy access to the part. In the case of replacement, it is desirable for the part to be as small as possible for easy handling and transportation. In the case of repair, it is desirable for the part to be repairable by conventional tools and methods that have been tested and proven in the aviation field.

[0036] The aircraft is subject to daily, weekly, etc. inspections, and the inspection frequency is inversely proportional to the aircraft's downtime.

[0037] Therefore, the aviation gas distribution device also needs to meet such requirements.

[0038] The applicant has determined the need to distribute gas from aviation cryogenic containers, whether they are structurally connected to the aircraft structure, installed in the aircraft, or carried by the aircraft.

[0039] From another perspective, according to ETOPS certification, aircraft are currently subject to a maximum distance rule from the landing runway, expressed in flight hours. This distance depends on the type of aircraft.

[0040] To ensure a high level of safety and the user's sense of security, the applicant has determined that flight is required even in the event of damage to the cryogenic container and the need to release the contained gas into the atmosphere.

[0041] The aviation storage device is designed to meet the complex requirements analyzed by the applicant.

[0042] As Figure 1As shown, the aviation gas distribution device 1 installed on the aircraft is supplied by a liquefied gas source 2 to supply gas to one or more consumption components 3. Here, two consumption components 3 are shown, such as two engines, an electric power generator or an air heater. A flow meter 22 is arranged at the output end of each liquefied gas source 2.

[0043] The liquefied gas source 2 consists of two cryogenic containers arranged in parallel. Each cryogenic container is provided with an output pipeline 4. The terms upstream and downstream refer to the flow direction of fluids, liquids and gases during normal operation.

[0044] Each cryogenic container is isolated to contain refined gas, such as liquid hydrogen at -253 °C. Each cryogenic container can withstand a maximum working pressure of 6 to 10 bar.

[0045] The aviation gas distribution device 1 includes a first valve 11 for each cryogenic container 2. The first valve 11 is installed on the output pipeline 4. The first valve 11 is controlled between an open position and a closed position. The intermediate position of the first valve 11 is dynamic because the first valve 11 is in motion when passing through the intermediate position. In other words, the first valve 11 is of the all-or-nothing type.

[0046] The first valve 11 can be arranged downstream of the flow meter 22. Optionally, the flow meter 22 is located downstream of the first valve 11.

[0047] The first valve 11 is present in the cryogenic distributor 5. The cryogenic distributor 5 may include a common pipeline 6 connecting the output of the first valve 11. The distributor is cryogenic because it passes through liquefied gas.

[0048] The cryogenic distributor 5 includes a plurality of output ends, here three. A second valve 12 is installed on each of the said output ends. The second valve 12 is controlled to have an open position and a closed position. The intermediate position of the second valve 12 is dynamic because the second valve 12 is in motion when entering the intermediate position. In other words, the second valve 12 is of the all-or-nothing type. The number of second valves 12 is three here.

[0049] A central buffer container 7 is installed downstream of each second valve 12. Three buffer containers 7 are provided in this embodiment. Each buffer container 7 also serves as a vaporizer. Insulation can be avoided. Each buffer container 7 receives liquid and supplies gas downstream. Between filling and emptying, a pressure rise or vaporization step occurs in each buffer container 7. Each buffer container 7 can withstand a maximum working pressure of 300 to 1000 bar. The designed working temperature range of each buffer container 7 is from -253 °C to +60 °C. The buffer container 7 is in a two-phase state during some operating steps and in a gaseous single-phase state during other operating steps. Each buffer container 7 can be equipped with a heating element 8.

[0050] A third valve 13 installed downstream of each buffer container 7 is used to supply gas, and a pressure reducing valve 9 is installed downstream of the third valve 13. The pressure reducing valve 9 limits the pressure to supply gas at the consumption pressure specified by the manufacturer of the consumption member 3. When the pressure in the buffer container 7 is higher than the consumption pressure, the pressure reducing valve 9 functions, otherwise it does not. The consumption pressure is lower than the maximum pressure of the buffer container 7. The consumption pressure is independent of the maximum pressure of the cryogenic container. The third valve 18 is of the all-or-nothing type.

[0051] Downstream of each pressure reducing valve 9, a controlled fourth valve 14 can be provided. The fourth valve 14 belongs to the all-or-nothing type.

[0052] Depending on the selected option, the fourth valve 14 or the pressure reducing valve 9 is formed in the collector 10. The collector 10 may include a conduit connecting the output of the fourth valve 14 or the pressure reducing valve 9. The collector 10 conveys gas. The collector 10 is connected downstream to the conduit 23 supplied to the consumption member 3. Generally, one supply conduit 23 is provided for each consumption member 3. Each supply conduit 23 can be equipped with a controlled supply valve 24. The supply valve 24 has a variable flow rate.

[0053] The gas distribution device 1 includes at least one compressor 20 connected to the collector 10. Generally, for redundancy, two compressors 20 are provided in parallel. The compressor 20 is electric. The compressor 20 can be equipped with a controlled upstream valve. The compressor 20 discharges gas into the collector 10. Specifically, in the case of a single consumption member 3, the collector 10 consists of a conduit.

[0054] A fifth valve 15 is installed downstream of each buffer container 7 to supply gas, and a second collector is installed downstream of the fifth valve 15. The second collector is connected to the compressor 20. The fifth valve 15 enables the isolation of the buffer container 7 and the compressor 20.

[0055] The fifth valve 15 is controlled. The fifth valve 15 is of the all-or-nothing type.

[0056] The compressor 20 increases the pressure to supply gas equal to the consumption pressure set by the manufacturer of the consumption member 3. The consumption pressure is lower than the maximum pressure in the buffer container 7. The compressor 20 can take gas from the buffer container 7 with a pressure lower than the consumption pressure to supply the collector 10 and the consumption member 3. A more thorough emptying of the buffer container 7 can increase the supply range of the gas contained in the buffer container 7 or reduce the volume of the buffer container 7.

[0057] The buffer container 7 is emptied sufficiently so that the internal pressure of the buffer container 7 is lower than the pressure in one of the cryogenic containers, such that during the filling process after emptying, liquid can be transferred from the cryogenic container to the buffer container 7 through the pressure difference. Thus, the liquid in the cryogenic container is sucked into the buffer container 7 to achieve pressure balance. The cryogenic pump can be omitted, thereby saving mass and energy consumption.

[0058] The aviation gas distribution device 1 provides a combination of the individual states of each cryogenic container, each buffer container 7, and each consumption member 3. Multiple consumption members 3 can be active simultaneously. In the normal mode, one cryogenic container is being emptied while the other cryogenic containers are in an inactive state and thus closed. However, in certain cases, such as to reduce the pressure in multiple cryogenic containers, a specific mode can be provided in which multiple cryogenic containers are being emptied. The buffer container 7 has a filling mode, a gasification mode, a gas storage mode, and an emptying mode.

[0059] When one of the cryogenic containers is being emptied, the corresponding first valve 11 is opened while the other first valves 11 are closed. When one of the consumption members 3 is being supplied, the corresponding supply valve 24 is opened.

[0060] When one of the buffer containers 7 is in the filling state, the second valve 12 connected to this buffer container 7 is opened, and at least one first valve 11 is opened. Except for the case of filling two buffer containers 7 simultaneously, the remaining second valves 12 are closed, the third valve 13 connected to this buffer container 7 is closed, and the fifth valve connected to this buffer container 7 is closed.

[0061] When one of the buffer containers 7 is in the gasification mode, the second valve 12 connected to the buffer container 7, the third valve 13 connected to the buffer container 7, and the fifth valve 15 connected to the buffer container 7 are closed. The gasification mode has a short duration, especially in a hot ambient atmosphere and / or when the buffer container 7 is heated.

[0062] When one of the buffer containers 7 is in the emptying mode, the second valve 12 connected to the buffer container 7 is closed. In the first part of the emptying, the pressure in the buffer container 7 is higher than the consumption pressure. The third valve 13 connected to the buffer container 7 is opened, the corresponding fourth valve 14 is opened, and the fifth valve connected to the buffer container 7 is closed. The gas undergoes a pressure reduction in the pressure reducing valve 9 and is supplied to the collector 10 at the consumption pressure. Next, the gas is consumed by the consumption member or multiple consumption members 3.

[0063] At a given moment, among the three buffer containers 7, one is in the filling mode, another is in the gasification - then - storage mode, and the third is in the emptying mode. Due to the different durations of these modes, it can also be found that two buffer containers 7 are in the filling mode and the third is in the emptying mode, and vice versa. It can also be found that two buffer containers 7 are in the storage mode and the third is in the emptying mode, and vice versa.

[0064] In this embodiment, the flowmeter 22 is arranged at the output of each liquefied gas source 2. The flowmeter 22 makes it possible to know with sufficient precision the quantity of liquid supplied to such a buffer container 7.

[0065] In this embodiment, the aviation gas distribution device 1 comprises a control unit 25 which receives external commands (for example from the consumption member 3 or from the central control unit of the aircraft) and liquid flow rate data from the flowmeter 22. The control unit 25 generates commands and sends them to the first, second, third, fourth and fifth controlled valves and the controlled supply valve 24. The commands can be "open" or "close". The control unit 25 manages the combination of the various states.

[0066] In a variant, the first valve 11 can be replaced by at least one multi-way valve having a plurality of input ends and one output end. In this case, it is advantageous to provide a multi-way valve having a mixing position, in particular having at least one position for emptying simultaneously two or more liquefied gas sources 2 in order to reduce their pressure while avoiding losses to the atmosphere.

[0067] In a variant, the second valve 12 can be replaced by at least one multi-way valve having one input end and a plurality of output ends, one multi-way valve per buffer container 7. The multi-way valve forms a distributor.

[0068] In a variant, the plurality of pressure reducing valves 9 are replaced by a single pressure reducing valve 9, and the third valve 13 is present in the single pressure reducing valve 9. In this case, the third valve 13 can be replaced by at least one multi-way valve of a pressure reducing valve having a plurality of input ends and one output end. Then, the plurality of fourth valves 14 are replaced by a single fourth valve 14, which is not controlled where applicable.

[0069] In a variant, the plurality of fifth valves 15 can be replaced by at least one multi-way valve having a plurality of input ends, one input end per buffer container 7, and an output end to the compressor 20 or the plurality of compressors 20. The multi-way valve forms a collector 10.

[0070] In Figure 2 In the embodiment shown, the device is associated with the liquefied gas source 2 for filling three buffer containers 7 so as to supply gas to two gas consumption members 3. The first valve 11 can be omitted because the second valve 12 is sufficient to direct the liquid from the liquefied gas source 2 to one of the buffer containers 7.

[0071] Furthermore, the pressure reducing valve 9 is unique. The fourth valve 14 is unique. The pressure reducing valve 9 is connected downstream of the third valve 13, here the number of third valves being three, for receiving the pressurized gas from the buffer container 7, the associated third valve 13 of the buffer container 7 being in the open state. This also applies to Figure 5The case where there are two buffer containers 7 instead of three buffer containers 7. A single pressure reducing valve 9 is also applicable to the other embodiments shown, regardless of the number of liquefied gas sources 2 and the number of consumption members 3.

[0072] A flowmeter 22 is provided between the second valve 12 and the buffer container 7. Optionally, the flowmeter 22 is provided upstream of the second valve 12.

[0073] The compressor 20 is wirelessly remotely controlled by the control unit 25.

[0074] In Figure 3 the embodiment shown, the device is associated with a liquefied gas source 2 for filling three buffer containers 7, so as to supply gas to a gas consumption member 3 (such as an engine). For the same reason as Figure 2 above, the first valve 11 can be omitted. The flowmeter 22 is provided at the output end of the liquefied gas source 2. The presence of three buffer containers 7 ensures that the aircraft has a high degree of autonomy in the event of a failure of the liquefied gas source 2, which may require emptying the liquefied gas source 2. In addition, the three buffer containers 7 provide redundancy because the device can operate satisfactorily using only two buffer containers 7. The cryogenic distributor 5 may include a valve having one input end and three output ends, one for each buffer container 7. The supply valve 24 associated with the consumption member 3 can be omitted, especially if the valve associated with the compressor 20 is controlled.

[0075] This embodiment is very suitable for an aircraft having two components, each component including an aviation gas distribution device 1 and at least one cryogenic liquefied gas source. Each component can be symmetrically installed in the aircraft, for example, installed in the wing, under the wing, etc.

[0076] In Figure 4 the embodiment shown, the device is associated with two liquefied gas sources 2 for filling three buffer containers 7, so as to provide gas for the gas consumption member 3.

[0077] In Figure 5 the embodiment shown, the device is associated with a liquefied gas source 2 for filling two buffer containers 7, so as to provide gas for the gas consumption member 3. For the same reason as Figure 2 above, the first valve 11 can be omitted. Then the operation is adjusted. The duration of the gasification stage can be reduced, especially by providing a heating member 8 for each buffer container 7 or a plurality of buffer containers 7. In addition, one of the buffer containers 7 is emptied through the third valve 13 and then through the fifth valve 15, while the other buffer container 7 is filled with liquid and then in the gasification stage. The switching moment between the third valve 13 and the fifth valve 15 is independent of the closing moment of the second valve 12.

[0078] Generally, the number X of cryogenic containers, the number Y of buffer containers 7, and the number Z of consumption components are independent of each other, where X ≥ 1; Y ≥ 2; Z ≥ 1.

[0079] The capacity of each buffer container 7 is 10% to 20% of the capacity of each liquefied gas source 2.

[0080] The cryogenic container 2 is subject to the evaporation of liquefied gas. A gas collection circuit can be provided at the top of the cryogenic container 2. The collection circuit can operate through a calibrated pressure valve above a threshold pressure. The collection circuit includes a compressor for re-injecting the gas downstream, for example, between the fifth valve 15 and the compressor 20.

[0081] Optionally, an additional flowmeter is provided at the input of each buffer container. To ensure redundancy in liquid flow measurement.

[0082] The first valve 11 can be monostable or bistable. The first valve 11 can be controlled to open for a duration corresponding to the filling of one of the buffer containers 7, or to open in a pulse width modulation manner. The second valve 12 can be monostable or bistable. The second valve 12 can be controlled to open for a duration corresponding to the filling of one of the buffer containers 7, or to open in a pulse width modulation manner.

Claims

1. An aviation device (1) for distributing gas between at least one liquefied gas source (2) and at least one gas-consuming component (3) in an aircraft, comprising: at least one first controlled all-or-nothing valve (11) located at the output of each liquefied gas source (2); a cryogenic distributor (5) connected to each first controlled all-or-nothing valve (11) and supplying liquid; a second controlled all-or-nothing valve (12) connected in parallel with the cryogenic distributor (5); a two-phase buffer container (7), each buffer container being supplied with liquid by one of the second controlled all-or-nothing valves (12) and supplying gas; a third controlled valve (13) installed at the output of each buffer container (7) for supplying gas; a pressure reducing valve (9) installed at the output of the third controlled valve (13); a collector (10) supplied by the pressure reducing valve (9) to supply the at least one gas-consuming component (3).

2. The device according to claim 1, comprising a fourth controlled valve (14) installed at the output of each pressure reducing valve (9) for supplying gas.

3. The device according to claim 1, comprising at least one compressor (20) supplied by at least one of the buffer containers (7), and at least one fifth controlled valve (15) installed between the compressor (20) and the buffer container (7).

4. The device according to claim 1, comprising a control unit for controlling the at least one first controlled all-or-nothing valve (11) to sequentially fill and empty the buffer containers (7) by a pressure difference.

5. The device according to claim 4, wherein, in order to empty one of the buffer containers (7), the control unit first controls the third controlled valve by a pressure difference and then by starting the compressor (20) to allow gas flow until the pressure in the buffer container (7) is lower than the pressure present in the cryogenic distributor (5).

6. The device according to any one of the preceding claims, wherein, the at least one first controlled all-or-nothing valve (11) and the second controlled all-or-nothing valve (12) are cryogenic, and a flow meter (22) is provided at the output of each liquefied gas source (2), and an additional flow meter is advantageously provided at the input of the buffer container (7).

7. A component comprising the device according to any one of the preceding claims and at least one single cryogenic liquefied gas source.

8. An aviation method for distributing gas between at least one liquefied gas source (2) and at least one gas-consuming component (3) in an aircraft, comprising: The step of filling a buffer container (7) out of at least two buffer containers (7) with liquefied gas by means of at least one of at least one first controlled all-or-nothing valve (11) at the output of each liquefied gas source (2), one of the second controlled all-or-nothing valves (12) connected in parallel with the cryogenic distributor (5); the cryogenic distributor (5) is connected to each first controlled all-or-nothing valve (11), the first controlled all-or-nothing valve (11) is supplied with liquid by the cryogenic distributor (5), the buffer container (7) is connected to the open second controlled all-or-nothing valve (12), and the other second controlled all-or-nothing valves (12) are closed, and the third controlled valve (13) installed at the output of the buffer container (7) is closed, and The step of emptying the buffer container (7), the second controlled all-or-nothing valve (12) is closed, the third controlled valve (13) is opened, and the gas flows through a pressure reducing valve (9) installed at the output of the third controlled valve (13) for supplying gas to the at least one gas consuming member (3).

9. The method according to claim 8, wherein, In normal operation, the first buffer container (7) is in the process of being filled with liquid by pressure equalization via at least one open first controlled all-or-nothing valve (11) and one of the second controlled all-or-nothing valves (12) corresponding to the open first buffer container (7), the third controlled valve (13) corresponding to the first buffer container (7) is closed, while the second buffer container (7) is in the process of supplying pressurized gas, the second controlled all-or-nothing valve (12) corresponding to the closed second buffer container (7), and the third controlled valve (13) corresponding to the first buffer container (7) are opened, and The third buffer container (7) is in the process of gasification, the second controlled all-or-nothing valve (12) corresponding to the third buffer container (7) is closed, and the third controlled valve (13) corresponding to the third buffer container (7) is closed.

10. The method according to claim 8 or 9, wherein, The step of emptying the buffer container (7) includes: a sub-step of emptying through a pressure reducing valve (9) to reduce the gas pressure to the pressure required by the at least one gas consuming member (3); then, a sub-step of emptying assisted by a pump to bring the gas pressure to the pressure required by the at least one gas consuming member (3) and to make the pressure in the buffer container (7) lower than the pressure existing in the cryogenic distributor (5) at the end of emptying.

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