Aviation device for distributing gas

Abstract

Aviation device 1 for distributing gas between at least one liquefied gas source 2 and at least one gas consuming member 3 in an aircraft, comprising: at least one first controlled all-or all-no valve 11 located at the output of each liquefied gas source 2; a low-temperature distributor (5) which is connected to each first controlled valve (11) and supplies a liquid; a second controlled all-or all-no valve 12 connected in parallel to the cryogenic distributor 5; two-phase buffer vessels 7, each buffer vessel 7 supplying liquid and gas through one of the second controlled valves; a third controlled valve 13 for supplying gas, the third controlled valve 13 being mounted at the output end of each buffer container 7; the pressure reducing valve 9 is mounted at the output end of the third controlled valve 13; a collector 10 supplied with liquid by the pressure relief valve 9 to supply at least one consumable member 3.

Description

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

[0002] Since the beginning of aviation, it has 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 than gasoline and is less flammable. These fuels are stored in reservoirs in the wings, fuselage-wing joints, or in the tail.

[0003] The trend towards reducing CO2 gas emissions results in engines that consume less. However, as certain technologies mature, especially increasing blade tip speeds, the gains in CO2 gas emissions are diminishing. Introducing breakthroughs seems increasingly desirable.

[0004] Hence, the gas aircraft project emerged. Gases with shorter or non-existent carbon chains produce little or no pollution when burned with oxygen. On the other hand, storage of H2, O2 or C1 or C2 gases is difficult due to the small size of gas molecules and there is a risk of leakage.

[0005] On the ground, hydrogen, methane, ethane, ethylene, acetylene or oxygen is usually stored in overpressure containers that are too large and contain too much potential pressure energy to be loaded onto an aircraft or in welded and / or bonded cryogenic containers. Cryogenic storage time is limited in proportion to the amount stored.

[0006] Furthermore, gas stored in a liquid state cannot be used by internal or external combustion engines or fuel cells. Final consumption requires the gas to be within the temperature range and pressure range specified by the manufacturer of the consumer component.

[0007] The gas needs to be stored in the aircraft for consumption on board the aircraft.

[0008] The invention proposes an aviation device for distributing gas between at least one liquefied gas source and at least one gas consuming component in an aircraft. The device comprises 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 and supplied with gas through one of the second controlled valves, 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 consuming component. According to the invention, the aviation gas distribution device can provide the aircraft with the necessary autonomy through the volume contained in the buffer container, without being affected by 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 consuming component.

[0009] Unlike in the aerospace field, where cryogenic valves do not need to be closed again after one use, here a closable valve, such as a solenoid valve, is provided.

[0010] In one embodiment, the arrangement comprises a fourth controlled valve mounted at the output of each pressure reducing valve for supplying gas to a consumer, such as an engine or auxiliary equipment for generating electrical energy on board, whichever may be supplied from a single buffer container.

[0011] In one embodiment, the device comprises 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 fully emptied to increase the amount of gas available for the consumable components and to make the pressure of 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 valve is 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. Eliminating the cryogenic pump can save quality and reduce the risk of accidents.

[0012] In one embodiment, the device comprises a control unit which controls at least one first controlled valve for sequentially filling the buffer container and sequentially emptying the buffer container by 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 process of being emptied and the other is in the process of being filled or gasified by means of heating gas.

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

[0015] During the gasification process, if the respective buffer container exceeds the maximum pressure, the control unit can request a switch to discharge the overpressured buffer container and temporarily interrupt the emptying of the other 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 the gas flow by the 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 existing in the cryogenic distributor. The operation of the compressor is limited in time, thereby saving energy.

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

[0018] In one embodiment, the device comprises a flow meter arranged at the output of each liquefied gas source. Measuring the liquid flow enables managing the opening time of the first and second valves and the dosing device to supply the required amount.

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

[0020] In one embodiment, an assembly includes the above-described device and at least one single source of cryogenic liquefied gas. One of the cryogenic vessels can be in the process of being emptied to fill the buffer vessel while the other cryogenic vessel or vessels are inactive. In the event of overpressure in the cryogenic vessel, priority emptying can be provided to the dispensing device.

[0021] In one embodiment, an aeronautical method for distributing gas between at least one liquefied gas source and at least one gas consuming component in an aircraft comprises: a step of filling a buffer container with liquefied gas through at least one of at least one first controlled all-or-nothing valve located at the output of each liquefied gas source, one of a second controlled all-or-nothing valve connected in parallel with a cryogenic distributor; a cryogenic distributor connected to each first controlled valve and supplied with liquid by the cryogenic distributor; the buffer container is connected to the second opened controlled valve, while another second controlled valve or multiple second controlled valves are closed, 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 is closed, the third controlled valve is opened, and the gas flows through a pressure reducing valve installed at the output of the third controlled valve to supply the at least one consuming component. The use of an all-or-nothing valve allows the amount of liquid passing through the valve to be controlled by the duration of the opening.

[0022] In one embodiment, in normal operation, the first buffer container is filled with liquid by pressure balance through at least one of a first opened valve and a second valve corresponding to the opened first buffer container, the third valve corresponding to the first buffer container is closed, and the second buffer container is being supplied with pressurized gas, the second valve corresponding to the closed second buffer container, the third valve corresponding to the first buffer container is opened. This mode is applicable to both buffer containers.

[0023] In one embodiment, the third buffer container is being gasified, 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 is applicable 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 consumable components, and then a sub-step of emptying with the assistance of a pump to bring the gas pressure to the pressure required by the consumable components and to make the pressure in the buffer container lower than the pressure existing in the cryogenic distributor at the end of emptying, thereby achieving a more complete emptying of the buffer container.

[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 energy reserves, in particular on one buffer container if there are two buffer containers and on two buffer containers if there are three buffer containers.

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

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

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

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

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

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

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

[0033] Aviation gas distribution units are designed to be carried by aircraft: airplanes, drones, helicopters, etc. Aviation gas distribution units are supplied by liquid and supply gas at a selected pressure. In other words, the fuel or oxidant is stored in liquid form in cryogenic containers at extremely low temperatures. As an example, gaseous hydrogen at 0°C and 1 atmosphere has a density about 800 times lower than liquid hydrogen at -253°C, and therefore has a volume about 800 times larger. Cryogenic containers are not suitable for withstanding high pressures, in particular pressures above 10 bar.

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

[0035] Furthermore, maintenance rules require the ability to dismantle and repair or replace most parts of an aircraft. Thus, an aircraft is able to land anywhere suitable for its weight and landing requirements - an airport for airplanes and a helipad for helicopters - but not equipped with maintenance equipment specific to the aircraft type. In case of detected damage, the aircraft is repaired permanently or temporarily, or dismantled to replace or repair the defective part, in accordance with the manufacturer's manuals and documents approved by the aviation safety authorities. It is desirable that the maintenance operator be able to access the part easily. In the case of replacement, it is desirable that the part be as small as possible to be easy to handle and transport. In the case of repair, it is desirable that the part be repairable by conventional tools and methods tried and tested in the aviation field.

[0036] Aircraft are subject to daily, weekly and other inspections, with the frequency of inspections being inversely proportional to the time the aircraft has been grounded.

[0037] Therefore, aviation gas distribution devices also need to meet such requirements.

[0038] Applicants have identified a need for dispensing gases from aircraft cryogenic containers, whether they are structurally connected to the aircraft structure, installed in the aircraft, or carried by the aircraft.

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

[0040] In order to ensure a high level of safety and a sense of security for the users, the applicant has determined that it is necessary to fly even in the event that the cryogenic container is damaged and the contained gas needs to be released into the atmosphere.

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

[0042] like Figure 1As shown, an aviation gas distribution device 1 installed on an aircraft is supplied by a liquefied gas source 2 to supply gas to one or more consumer components 3. Here, two consumer components 3 are shown, such as two engines, an electric energy 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 is composed 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 vessel is isolated to contain refined gas, such as liquid hydrogen at -253° C. Each cryogenic vessel is capable of withstanding a maximum operating pressure of 6 to 10 bar.

[0045] The aviation gas distribution device 1 comprises a first valve 11 for each cryogenic container 2. The first valve 11 is mounted on the outlet pipe 4. The first valve 11 is controlled in 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 an all-or-nothing type. The first valve 11 may be arranged downstream of the flow meter 22. Optionally, the flow meter 22 is located downstream of the first valve 11.

[0046] The first valve 11 is present in the cryogenic distributor 5. The cryogenic distributor 5 may comprise a common conduit 6 connecting the outputs of the first valve 11. The distributor is cryogenic because it passes liquefied gas.

[0047] The cryogenic distributor 5 comprises a plurality of output ends, three in this case. A second valve 12 is mounted on each of the 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 an all-or-nothing type. The number of the second valves 12 is three here.

[0048] A central buffer container 7 is installed downstream of each second valve 12. Three buffer containers 7 are provided in the present embodiment. Each temporary storage container 7 also serves as a gasifier. Insulation can be avoided. Each buffer container 7 receives liquid and supplies gas downstream. Between filling and emptying, a pressure increase or a gasification step occurs in each buffer container 7. Each buffer container 7 is capable of withstanding a maximum operating pressure of 300 to 1000 bar. Each buffer container 7 is designed for an operating temperature range of -253°C to +60°C. The buffer container 7 is two-phase in some operating steps and a gaseous single phase in other operating steps. Each buffer container 7 can be equipped with a heating element 8.

[0049] The third valve 13 installed downstream of each buffer container 7 is used to supply gas, and the 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 works, otherwise it does not work. 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 an all-or-nothing type.

[0050] Downstream of each pressure reducing valve 9, a controlled fourth valve 14 may be provided. The fourth valve 14 is of the all-or-nothing type.

[0051] 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 connected to 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 a conduit 23 supplied to the consumable member 3. Typically, a supply conduit 23 is provided for each consumable member 3. Each supply conduit 23 can be equipped with a controlled supply valve 24. The supply valve 24 has a variable flow rate.

[0052] The gas distribution device 1 comprises at least one compressor 20 connected to the collector 10. Typically, for redundancy, two compressors 20 are arranged in parallel. The compressor 20 is electric. The compressor 20 may be equipped with a controlled upstream valve. The compressor 20 discharges the gas into the collector 10. Specifically, in the case of a single consumable component 3, the collector 10 consists of a conduit.

[0053] 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 isolation of the buffer container 7 and the compressor 20. The fifth valve 15 is controlled. The fifth valve 15 is of an all-or-nothing type.

[0054] The compressor 20 increases the pressure to supply gas equal to the consumption pressure set by the manufacturer of the consumable member 3. The consumption pressure is lower than the maximum pressure in the buffer container 7. The compressor 20 can take out gas from the buffer container 7 at a pressure lower than the consumption pressure to supply the collector 10 and the consumable member 3. 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.

[0055] 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, so that during the filling process after the emptying, liquid can be transferred from the cryogenic container to the buffer container 7 by the pressure difference. Therefore, 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.

[0056] The aviation gas distribution device 1 provides a combination of individual states of each cryogenic container, each buffer container 7 and each consumable member 3. Multiple consumable members 3 can be active at the same time. In normal mode, one cryogenic container is being emptied, while the other cryogenic containers are inactive and therefore closed. However, in some cases, for example in order 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.

[0057] 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 consumable components 3 is being supplied, the corresponding supply valve 24 is opened.

[0058] When one of the buffer containers 7 is in a filling state, the second valve 12 connected to the buffer container 7 is opened, and at least one first valve 11 is opened. Except for the case of filling two buffer containers 7 at the same time, the other second valves 12 are closed, the third valve 13 connected to the buffer container 7 is closed, and the fifth valve connected to the buffer container 7 is closed.

[0059] 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 lasts for a short time, especially in the case of hot ambient atmosphere and / or buffer container 7 heating.

[0060] When one of the buffer containers 7 is in 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 members 3.

[0061] At a given moment, of the three buffer containers 7, one is in the filling mode, another is in the gasification and then storage mode, and the third is in the emptying mode. Due to the different durations of these modes, it is also possible to find two buffer containers 7 in the filling mode and the third in the emptying mode, or vice versa. It is also possible to find two buffer containers 7 in the storage mode and the third in the emptying mode, or vice versa.

[0062] In this embodiment, a flow meter 22 is arranged at the output of each liquefied gas source 2. The flow meter 22 enables the amount of liquid supplied to such a buffer container 7 to be known with sufficient accuracy.

[0063] In this embodiment, the aviation gas distribution device 1 comprises a control unit 25, which receives external commands (e.g. from the consumer component 3 or from the central control unit of the aircraft) and liquid flow rate data from the flow meter 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 command can be "open" or "closed". The control unit 25 manages the combination of the various states.

[0064] In a variant, the first valve 11 can be replaced by at least one multi-way valve having a plurality of inputs and one output. In this case, it is advantageous to provide the multi-way valve with mixing positions, in particular with at least one position for simultaneously emptying two or more liquefied gas sources 2 in order to reduce their pressure while avoiding losses to the atmosphere.

[0065] In a variant, the second valve 12 can be replaced by at least one multi-way valve having one input and a plurality of outputs, one multi-way valve for each buffer container 7. The multi-way valve forms a distributor.

[0066] In a variant, the plurality of pressure reducing valves 9 are replaced by a single pressure reducing valve 9 in which the third valve 13 is present. 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 inputs and one output. The plurality of fourth valves 14 are then replaced by a single fourth valve 14, which is not controlled where applicable.

[0067] In a variant, the fifth valves 15 may be replaced by at least one multi-way valve having a plurality of inputs, one for each buffer container 7 , and an output to the compressor 20 or compressors 20 . The multi-way valve forms the collector 10 .

[0068] exist Figure 2 In the embodiment shown, the device is associated with a liquefied gas source 2 for filling three buffer containers 7, thereby providing gas for two gas consuming members 3. The first valve 11 can be omitted, since the second valve 12 is sufficient to direct liquid from the liquefied gas source 2 to one of the buffer containers 7.

[0069] 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, where the number of the third valves is three, for receiving pressurized gas from the buffer container 7, and the associated third valve 13 of the buffer container 7 is in an open state. This also applies to Figure 5 The 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 consumer components 3.

[0070] The flow meter 22 is disposed between the second valve 12 and the buffer container 7. Optionally, the flow meter 22 is disposed upstream of the second valve 12.

[0071] The compressor 20 is wirelessly remotely controlled by a control unit 25 .

[0072] exist Figure 3 In the embodiment shown, the device is associated with a liquefied gas source 2 for filling three buffer containers 7 and thereby supplying gas to gas consuming components 3, such as engines. Figure 2 For the same reason, the first valve 11 can be omitted. A flow meter 22 is provided at the output of the liquefied gas source 2. The presence of three buffer containers 7 ensures that the aircraft has a great 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, since the device can operate satisfactorily with only two buffer containers 7. The cryogenic distributor 5 can include a valve having an input and three outputs, one for each buffer container 7. The supply valve 24 associated with the consumer member 3 can be omitted, in particular if the valve associated with the compressor 20 is controlled.

[0073] This embodiment is very suitable for an aircraft having two modules, each module comprising an aviation gas distribution device 1 and at least one cryogenic liquefied gas source. Each module can be symmetrically mounted in the aircraft, for example in a wing, under a wing, etc.

[0074] exist Figure 4 In the embodiment shown, the device is associated with two sources 2 of liquefied gas for filling three buffer containers 7 and thus providing gas consuming members 3 with gas.

[0075] exist Figure 5 In the embodiment shown, the device is associated with a liquefied gas source 2 for filling two buffer containers 7 and thus providing gas to the gas consuming components 3. Figure 2 For the same reason, the first valve 11 can be omitted. The operation is then adjusted. The duration of the gasification phase can be reduced, in particular by providing a heating element 8 for each buffer container 7 or multiple buffer containers 7. In addition, one of the buffer containers 7 is emptied via the third valve 13 and then emptied via the fifth valve 15, while the other buffer container 7 is filled with liquid and then in the gasification phase. The switching moment between the third valve 13 and the fifth valve 15 is independent of the closing moment of the second valve 12.

[0076] Typically, the number X of cryogenic containers, the number Y of buffer containers 7 and the number Z of consumable components are independent of each other, wherein X≥1; Y≥2; Z≥1.

[0077] The capacity of each buffer container 7 is 10% to 20% of the capacity of each liquefied gas source 2 .

[0078] The cryogenic container 2 is subjected to evaporation of the liquefied gas, and a gas collection circuit can be provided at the top of the cryogenic container 2. The collection circuit can function 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.

[0079] Optionally, an additional flow meter is provided at the input of each buffer vessel to ensure redundancy of the liquid flow measurement.

[0080] The first valve 11 may be monostable or bistable. The first valve 11 may 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 modulated manner. The second valve 12 may be monostable or bistable. The second valve 12 may 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 modulated manner.

Claims

1. An aircraft 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 said output end of each liquefied gas source (2); a low temperature distributor (5) connected to each first controlled valve (11) and supplied with liquid; a second controlled all-or-nothing valve (12) connected in parallel with the cryogenic distributor (5); two-phase buffer containers (7), each buffer container being supplied with liquid by one of the second controlled valves (12) and with gas; a third controlled valve (13) mounted at the output end of each buffer container (7) for supplying gas; a pressure reducing valve (9) installed at the output end of the third controlled valve (13); A collector (10) supplied by said pressure reducing valve (9) for supplying said at least one consumable member (3).

2. The device according to claim 1, comprising a fourth controlled valve (40) installed at the output end of each pressure reducing valve (9) for supplying gas.

3. The device according to one of the preceding claims, 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 one of the preceding claims, comprising a control unit for controlling the at least one first controlled valve (11) to successively fill the buffer container (7) and to successively empty the buffer container (7) by means of a pressure difference.

5. The device according to claim 3 or 4, wherein: In order to empty one of the buffer containers (7), the control unit controls the third controlled valve to allow gas flow, first by pressure difference and then by starting the compressor (20), until the pressure in the buffer container (7) is lower than the pressure prevailing in the cryogenic distributor (5).

6. The device according to any one of the preceding claims, wherein The at least one first valve (11) and the second valve (12) are cryogenic, and a flow meter (22) is provided at the output end of each liquefied gas source (2), an additional flow meter is advantageously provided at the input end of the buffer container (7).

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

8. An aeronautical method for distributing gas between at least one liquefied gas source (2) and at least one gas consuming component (3) in an aircraft, comprising: A step of filling a buffer container (7) from at least two buffer containers (7) with liquefied gas by at least one of at least one first controlled all-or-nothing valve (11) at the output end of each liquefied gas source (2), from one of the second controlled all-or-nothing valves (12) connected in parallel to the cryogenic distributor (5); the cryogenic distributor (5) is connected to each first controlled valve (11), the first controlled valve (11) is supplied with liquid by the cryogenic distributor (5), the buffer container (7) is connected to the opened second controlled valve (12), and the other second controlled valve (12) is closed, the third controlled valve (13) installed at the output end of the buffer container (7) is closed, and In the step of emptying the buffer container (7), the second controlled valve (12) is closed, the third controlled valve (13) is opened, and the gas flows through the pressure reducing valve (9) installed at the output end of the third controlled valve (13) to supply gas to the at least one consumable component (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 of the opened first valves (11) and the second valves (12) corresponding to the opened first buffer container (7), the third valve (13) corresponding to the first buffer container (7) is closed, and the second buffer container (7) is in the process of being supplied with pressurized gas, the second valve (12) corresponding to the closed second buffer container (7), and the third 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 valve (12) corresponding to the third buffer container (7) is closed, and the third 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) comprises: a sub-step of emptying through a pressure reducing valve (9) to reduce the gas pressure to the pressure required by the consumable component (3); then, a sub-step of emptying with the assistance of a pump to make the gas pressure reach the pressure required by the consumable component (3), and at the end of emptying, the pressure in the buffer container (7) is lower than the pressure existing in the low-temperature distributor (5).

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