Device for secure actuation of a container for provision of pressurized gas in an aircraft

Abstract

The invention relates to a device for secure actuation of a container for provision of gaseous oxygen in an aircraft, in order to distribute this oxygen to a user, said container (1) being intended to store the pressurized oxygen at a first oxygen pressure and having an opening (2) sealed by a seal (9); the device comprising a manifold (4) fluidically connected to said seal (9) and configured to receive an oxygen flow from said opening (2) when the seal (9) is pierced, said manifold (4) comprising an oxygen flow circuit (11) fluidically connected to said seal (10) and having an outlet (14) at a second oxygen pressure, lower than the first pressure, and an expansion valve (13) having means (12, 15, 16) for oxygen pressure regulation between the opening (2) and said outlet (14) during a flow; and an actuator (7) provided in the opening (2) and configured to pierce said seal (9) when triggered, so as to enable a flow of oxygen through the opening (2) from the container (1) and towards the outlet (14), the oxygen flow circuit (11) comprising a calibrated orifice (17) provided at the outlet (14) and configured to prevent any accumulation of oxygen at a third pressure between the first and second pressures in the event of oxygen flowing to said outlet (14) in the absence of triggering of the actuator (7).

Description

[0001] DESCRIPTION

[0002] TITLE: DEVICE FOR SAFELY ACTUATING A PRESSURE GAS SUPPLY CONTAINER IN AN AIRCRAFT

[0003] Technical field

[0004] The present invention relates to emergency oxygen supply devices used in aircraft in the event of depressurization.

[0005] The present invention aims to provide a safe device for triggering the supply of oxygen which protects aircraft pilots against hypoxia and smoke thanks to a supply of gaseous oxygen coming from a cylinder regulator assembly (known by the acronym "CRA" for the Anglicism "Cylinder Regulator Assembly") which commonly supplies aircraft oxygen masks.

[0006] Previous techniques

[0007] Patent US9625102B2 describes the configuration of a sealed cylinder as used in a CRA.

[0008] US Patent 1,104,0225B2 describes the activation of such a sealed cylinder.

[0009] In the event of a CRA failure, it is known to use a second CRA as a backup solution to prevent pilots from being without respiratory protection in the event of a drop in cabin pressure, as described for example in patent EP2916917B 1 which includes a redundancy of the CRA, namely two CRA assemblies, including a standard unsealed CRA, called primary, and a sealed backup CRA, which are connected in parallel and isolated from each other by non-return valves.

[0010] To activate the sealed CRA, a spring-loaded piercing pin pierces a rupture disc located at the top of the cylinder.

[0011] In the case of an unsealed CRA, each cylinder must be subject to maintenance with periodic revisions of the regulator, every five to six years, as well as periodic cylinder resistance tests, also every five years, with regular checks of the quantity of oxygen and leak locations.

[0012] Such maintenance is costly and intrusive, especially since it is likely to destructively activate the CRAs under test.

[0013] These solutions are only activated in the rare cases where necessary, which would reduce the need and cost of maintaining pressurized oxygen container regulator assemblies over the life of the aircraft.

[0014] In particular, the sealed pressurized oxygen container may have slow leaks, affecting the perforation of the rupture disc, so a leak from the check valve can block the regulator by filling the low pressure circuit.

[0015] Additionally, activation of the CRA releases a high pressure oxygen shock, creating a fire hazard from heating caused by adiabatic compression of the released oxygen under pressure against certain parts of these prior art systems.

[0016] Statement of the invention

[0017] The invention aims to overcome at least some of the aforementioned drawbacks and to propose a device for the secure actuation of a gaseous oxygen supply container in an aircraft to distribute this oxygen to be breathed by a user, in particular using an oxygen mask, said device being capable of combining the advantages of speed, simplicity and reliability for its implementation, while minimizing the risks of sudden rise in temperature and fire outbreaks.

[0018] In view of the above, the subject of the invention is a device for securely actuating a container for supplying gaseous oxygen in an aircraft to distribute this oxygen to a user, said container being intended to store oxygen under pressure at a first oxygen pressure and having an opening sealed by a seal; the device comprising:

[0019] - a manifold connected in fluid communication with said seal and configured to receive a flow of oxygen from said opening when the seal is pierced, said manifold comprising an oxygen flow circuit connected in fluid communication with said seal and having an outlet at a second oxygen pressure lower than the first pressure and a pressure regulator adapted to carry out an oxygen pressure regulation, between the opening and said outlet during a flow; and

[0020] - an actuator in the opening configured to pierce said seal when triggered so as to allow a flow of oxygen through the opening from the container and towards the outlet, the oxygen flow circuit comprising a calibrated orifice provided at the outlet and configured to prevent any accumulation of oxygen at a third pressure between the first and second pressures in the event of oxygen flow to said outlet in the absence of triggering of the actuator.

[0021] In one embodiment, the actuator and manifold are configured such that the actuator has a deactivated position in which it does not pierce the seal and allows flow into the oxygen flow path from the inlet, and an activated position in which it pierces the seal and prevents flow into the oxygen flow path from the inlet.

[0022] For example, the device further comprises said gaseous oxygen supply container, and the seal comprises a rupture element configured to facilitate the piercing of said seal when it is subjected to pressure by the actuator during its triggering.

[0023] According to one embodiment, the actuator forms a striking rod ending in a hollow needle.

[0024] Preferably, the regulator comprises a valve seat made of non-flammable material, an elastic element and an obstruction element mounted in elastic connection between an obstruction position in which it blocks the valve seat and a passage position in which it does not block the valve seat, said elastic element being configured to push said obstruction element towards said opening position and to be in the obstruction position when the first pressure is reached on a first side of the valve seat while the second pressure is reached on a second side of the valve seat opposite the first side of the valve seat.

[0025] Advantageously, heat dissipation devices are also placed in the oxygen flow circuit.

[0026] The device may further provide that the heat dissipation devices comprise a hot gas escape formed by the valve seat and / or filters arranged in the thermal retention zones of the oxygen flow circuit.

[0027] Preferably, the calibrated orifice is coupled to a pressure relief valve configured to be manually or automatically activated to vent oxygen included in the oxygen flow circuit while the actuator is not triggered.

[0028] The invention also relates to a method in which the pressure relief valve is activated for less than ten seconds before triggering the actuator until the seal ruptures.

[0029] Brief description of the drawings

[0030] The invention will be better understood from a detailed study of an embodiment taken as a non-limiting example and illustrated by the appended drawings, in which:

[0031] [Fig 1] represents a device for safely actuating an oxygen supply container in an aircraft, according to the state of the art.

[0032] [Fig 2] to [Fig 4] represent the means of piercing the seal of the oxygen storage container by the actuator, according to the state of the art.

[0033] [Fig 5] represents a situation leading to a faulty activation of the drilling means.

[0034] [Fig 6] represents the actuating device according to the invention. [Fig 7] represents a section of the sealing gasket bulged by the oxygen overpressure before it is pierced by the actuator.

[0035] [Fig 8] shows the actuating device with a pressure relief valve.

[0036] [Fig 9] represents the overall architecture into which the actuation device can be integrated in an aircraft.

[0037] [Fig 10] shows the location of the opening in the manifold to the oxygen flow path, on a device whose actuator is not triggered.

[0038] [Fig 1 1 ] shows the location of the opening in the manifold to the oxygen flow circuit, on a device whose actuator is triggered.

[0039] [Fig 12] shows the device with heat sinks in the oxygen flow circuit.

[0040] [Fig 13], [Fig 14] and [Fig 15] represent the device with an anti-heat hot gas escape coupled to the pressure regulating valve.

[0041] Detailed description

[0042] Figures 1 to 5 illustrate a device for actuating an oxygen supply container in an aircraft according to the prior art, comprising an oxygen supply container in an aircraft for distributing this oxygen to a user, in particular, to an oxygen mask intended to be used by a pilot.

[0043] The device according to the prior art comprises a container IA intended to store oxygen under pressure, this container comprising an opening 2A sealed by a seal 9A at the inlet of a collector 4A receiving the oxygen from the container when the seal 2A is pierced by an actuator and generating a low pressure line 3A via a pressure reducer, and an isolation valve 5A, the assembly making it possible to supply oxygen to another system using oxygen 6A or an oxygen distribution network.

[0044] The device according to the state of the art comprises an oxygen storage container IA comprising a neck provided with an opening 2A and a collector 4A which is mounted on the neck and which is connected to a supply line 3A.

[0045] The 4A collector is connected to the 3A supply line equipped with a 5A isolation valve and to which a 6A consumer system is connected.

[0046] The device further comprises a seal 9A interposed between the neck and the manifold 4A and an actuator 7A intended to pierce the seal to cause the regulator to reduce the high pressure to low pressure so as to generate a flow of oxygen at low pressure in the supply line and thus supply the consumer system 6A.

[0047] This device is likely to generate leaks from the IA container to the 5A isolation valve, rendering it inoperative.

[0048] Figure 2 illustrates the piercing means of the device according to the prior art of Figure 1, in the deactivated position.

[0049] They comprise an actuator 7A provided with a tip 8A and mounted in translation in the collector 4A so as to be able to pierce the sealing gasket 9A of the oxygen storage container, for example at the level of a zone of fragility 10A provided for this purpose.

[0050] Figure 3 illustrates the piercing means of the prior art device of Figure 1 moving from the deactivated position to the activated position.

[0051] During this movement the needle is pushed towards the seal 9A.

[0052] Figure 4 illustrates the piercing means of the device according to the state of the art in the activated position, in which the seal 9A has been pierced by the needle, and the oxygen from the container escapes through the opening 2A into the collector 4A.

[0053] Figure 5 shows that in the event of an oxygen leak in the manifold 4A, the device according to the prior art does not allow the evacuation of the excess pressure generated in the manifold 4A, which generates a compression force against the movement of the actuator 7A towards the seal 9A, which prevents its piercing and the activation of the device to deliver oxygen to an outlet system 6A.

[0054] Figure 6 illustrates the actuating device according to the invention making it possible to overcome this drawback.

[0055] This actuating device is intended in particular to be carried on board an aircraft and to safely actuate a gaseous oxygen supply container, in particular for supplying an oxygen mask in the event of depressurization of the aircraft.

[0056] The device may therefore comprise a gaseous oxygen supply container 1 intended to store the oxygen under pressure at a first oxygen pressure, which is a high storage pressure, for example of the order of two hundred bars.

[0057] The container 1 has an opening 2 sealed by a seal 9.

[0058] The device comprises a manifold 4 connected in fluid communication with said seal 9 and configured to receive a flow of oxygen from said opening 2 when the seal 9 is pierced.

[0059] The manifold 4 comprises an oxygen flow circuit 11 connected in fluid communication with said seal 9.

[0060] The manifold 4 leads, via the regulator 13, to a low pressure distribution circuit 14 forming a low pressure outlet 14 at a second oxygen pressure lower than the first pressure, for example of the order of the local ambient pressure in the deactivated state, for example a local atmospheric pressure, a cabin pressure or a pressure intended for example for the supply of oxygen to a passenger compartment, a device, an oxygen mask of an aircraft pilot or passenger, etc.

[0061] The manifold 4 comprises a regulator 13 adapted to carry out an oxygen pressure regulation between the opening 2 and the outlet 14 during an oxygen flow, for example using oxygen pressure regulation means 12, 15, 16. The device comprises an actuator 7 inserted in the opening

[0062] 2.

[0063] The actuator 7 is configured to pierce the seal 9 when triggered, so as to allow a flow of oxygen through the opening 2 from the container 1 and towards the low pressure circuit 14.

[0064] The oxygen flow circuit 11 further comprises a calibrated orifice 17 provided at the outlet 14, this calibrated orifice 17 being configured to prevent any accumulation of oxygen at a third pressure between the first and second pressures in the event of oxygen flow to said low pressure circuit 14 in the absence of triggering of the actuator 7.

[0065] During a leak or activation of the actuator 7, the piercing of the seal 9 causes an increase in the third pressure up to the first pressure, whereas in the deactivated state and in normal operation, namely without leakage of the seal 9, the third pressure must remain substantially equal to the second pressure.

[0066] The calibrated orifice 17 is for example provided in the low pressure part of the system, for example in the outlet 14 downstream of the regulator

[0067] 13.

[0068] The calibrated orifice 17 allows the pressure to be relieved from the circuit, thus improving the reliability of activation and ensuring protection against adiabatic compression.

[0069] To protect against pollution, a pressure relief valve may be added to said calibrated orifice 17.

[0070] The calibrated orifice 17 therefore makes it possible to improve the reliability of the activation of the actuator 7 and to prevent fires, by having the effect of preventing the accumulation of pressure in the oxygen flow circuit 11 and in particular in the regulator 13 and at the outlet.

[0071] 14, and to prevent the closure of said regulator 13, which makes it possible to evacuate to the LP circuit the hot gases which can accumulate on the seat 16 of said regulator 13 and around it during the adiabatic compression which takes place when the seal 9 is pierced. According to one embodiment, the actuator 7 forms a striking rod ending in a needle 8, for example a hollow needle, which allows the high pressure oxygen to be released through the needle once it has pierced the seal 9, channeling the oxygen from the container 1 towards the outlet 14 and the oxygen supply, thus ensuring efficient activation of the system.

[0072] Preferably, the pressure reducer 13 comprises a valve seat 16 made of non-flammable material, an elastic element 15 and an obstruction element 12 mounted in elastic connection between an obstruction position in which it blocks the valve seat 16 and a passage position in which it does not block the valve seat 16, said elastic element 15 pushing said obstruction element 12 towards said opening position and being in the obstruction position when the first pressure is reached on a first side of the valve seat 16 while the second pressure is reached on a second side of the valve seat 16 opposite the first side of the valve seat 16.

[0073] As illustrated by Figure 7, the seal 9,9A may comprise a zone of weakness 10,1 OA adapted to form a curved zone, under the effect of the overpressure or by its shape obtained during its manufacture, for example centrally, in said seal 9,9A under the effect of the oxygen overpressure before its piercing by the actuator 7.

[0074] For example, the fragile zone 10, 10A comprises a rupture element configured to bulge depending on an overpressure on one side and to facilitate the piercing of the sealing gasket 9, 9A when it is subjected to pressure by the actuator 7 during its triggering.

[0075] Advantageously, the rupture element 10A forms a disc, elastic to interface the first pressure and the second or third pressure.

[0076] It may include a surface adapted to be curved towards the actuator 7 under the effect of the first pressure.

[0077] It may comprise a surface which is rigid and of a domed shape. Indeed, when said seal 9 is subjected to comparable pressures on each side, for example if it is subjected to an equivalent pressure on the side of the manifold 4 due to an oxygen leak towards it, it is common for there to be insufficient tensile stress in the seal 9 to promote its rupture when the actuator 7 tries to pierce it, in the manner of a deflated balloon which does not burst unlike an inflated balloon which undergoes a complete rupture in the event of contact with a needle.

[0078] Figure 8 illustrates that the calibrated orifice 17 can further be coupled, for example in series, to a pressure relief valve 19 which can be activated manually or automatically to discharge oxygen included in the oxygen flow circuit 11 while the actuator 7 is not triggered.

[0079] By "automatically" is meant that the operation is carried out passively, without additional intervention by an operator, without necessarily involving control or servo-control of the pressure relief valve 19.

[0080] The pressure relief valve 19 coupled to the calibrated orifice 17, as well as their method of use, have the effect of preventing the accumulation of excessive pressure in the event of a minor leak in the system, in particular at the seal 9, and / or between the high pressure in the container 1 to the low pressure in the manifold 2 and the oxygen flow circuit 1 1 , while allowing normal operation of the system when triggered by the activation of the actuator 7.

[0081] With the flight cycles of the aircraft, the cabin pressure varies, causing the low pressure circuit to breathe through the calibrated orifice 17, if necessary via the pressure relief valve 19.

[0082] This breathing, or cyclical entry of cabin air, can introduce pollutants that cannot be filtered by a simple mechanical filter, such as humidity which can cause degradation of seals and corrosion of components.

[0083] The pressure relief valve 19 makes it possible to effectively close the system to external pollutants and to maintain the third pressure, or internal pressure, above the second pressure, or cabin pressure, but below the first pressure, or blocking pressure of the regulator 13, provided that said pressure relief valve 19 is set below the pressure range of said regulator 13, for example one to three bars.

[0084] The pressure relief valve 19 could be placed upstream, downstream of, or within the calibrated orifice 17 with similar performance, as illustrated in Figure 8.

[0085] According to another embodiment, the valve 19 is capable of opening briefly and periodically to relieve any pressure accumulated in the low pressure circuit.

[0086] Such a valve 19 can for example be activated remotely and automatically, or manually during periodic maintenance, or even briefly just before the activation of the actuator 7 and the release of oxygen into the oxygen flow circuit 11.

[0087] The invention also relates to a method in which the pressure relief valve 19 is activated for a predetermined period, for example less than ten seconds before triggering the actuator 7 until the seal 9 ruptures.

[0088] Figures 9 and 10 illustrate that the actuator 7 and the manifold 4 may be configured, in particular by the location of a passage 20 in the manifold 4, so that the actuator 7 has a deactivated position in which it does not pierce the seal 9 and allows flow into the oxygen flow circuit 11 from the passage 20, and an activated position in which it pierces the seal 9 and prevents any flow into the oxygen flow circuit 11 from the passage 20.

[0089] Figure 9 illustrates a possible architecture for implementing the invention in an aircraft.

[0090] This architecture includes, for example, two copies of container 1, one sealed and one unsealed.

[0091] The unsealed container is, for example, configured to store oxygen at approximately 1,800 psi (pounds per square inch) or 127 bars. It is coupled to a pressure regulator 13 adapted to reduce the pressure to a few bars, for example approximately 5 bars.

[0092] A low pressure switch 22 detects if the pressure is above a minimum operating pressure, for example three bars, and sends a signal to avionics equipment included in an on-board electronic system 24 of the aircraft to allow low pressure oxygen to be distributed via non-return valves 19 to the masks 25 of the pilots of the aircraft for use in an emergency.

[0093] To further increase capacity and / or provide redundancy in case of failure of the first container, the second, sealed cylinder is added in parallel with the first.

[0094] The two containers 1 are isolated from each other by the non-return valves 19 so that, in the event of a major leak in one of the containers 1, the contents of the other container do not empty through the same leak.

[0095] The second container 1 in the known solutions of the state of the art requiring regular maintenance, including for example frequent checks of quantities, functional tests, replacements of elastomer seals in the regulator, hydrostatic tests to check for cracks in the cylinder... the actuation system according to the invention makes it possible to have the second container as a backup sealed container which is only activated in the event of failure of the main container, the detection of said failure being done via an additional low pressure switch 22 located before the non-return valve 19 of the first container 1.

[0096] The sealed container 1 can thus be electrically activated by control means 23 coupled to a computer of the on-board system 24.

[0097] Furthermore, the calibrated orifice 4 prevents pressure build-up in the low pressure circuit, thus ensuring proper activation by the actuator 7.

[0098] The pressure relief valve 13 in line with the calibrated orifice 17, set below the operating pressure of the low pressure circuit at the second pressure, prevents contamination of the downstream pipes by maintaining a positive pressure.

[0099] Thus, the calibrated orifice 17 is open (Figure 10) when the actuator 7 is deactivated, namely in the raised position revealing the oxygen flow circuit 11 at the passage 20, and closed (Figure 11) when the actuator 7 is activated, namely in the lowered, depressed position, obstructing the oxygen flow circuit 11 at the passage 20.

[0100] The calibrated orifice 17 can thus be positioned openly allowing breathable ventilation as described previously as long as the actuator 7 has not yet been activated, and closed once the latter has been activated.

[0101] Upon activation of the actuator 7, ambient pressure gas accumulates in the manifold 4 and in the expander 13, which causes rapid and substantially adiabatic compression of the gas in a dead-end zone in which it is compressed.

[0102] This is calculated using the following ideal gas law equation in a reversible adiabatic process: p^-Y pv = constant in which:

[0103] P represents the initial pressure of the gas, y is the adiabatic coefficient, namely the ratio of the heat capacities at constant pressure and constant volume, and

[0104] T is the absolute temperature of the gas.

[0105] Using the example of a gas under a pressure of one bar at twenty degrees Celsius in the expander 13, which is then compressed to two hundred bars, the final temperature of the adiabatically compressed gas is one thousand fifty-eight degrees, where gamma equals one point four.

[0106] At such temperatures in pure oxygen, most elastomers ignite spontaneously, in particular that of the valve seat 16 which is often made of elastomer for its sealing properties, elasticity, ease of manufacture at low cost.

[0107] Thus, it is advantageous to leave the calibrated orifice 17 open so that the compressed gas is not confined at the valve seat 13 but pushed through the low pressure side, namely into the oxygen flow circuit 11, which requires a relatively large volume in terms of piping to slowly diffuse said flow.

[0108] Thus, in this case, the low pressure side having reached a certain pressure, for example of the order of six bars, the regulator 13 then blocks under the effect of the compressed oxygen from the activation chamber on the low pressure side.

[0109] The gas immediately next to the valve seat 16 is then compressed adiabatically from six bars to two hundred bars under the effect of oxygen from the container 1 cooled slightly during its expansion by the Joule-Thompson effect before heating up during recompression.

[0110] The invention thus makes it possible to mitigate dangerous high temperatures during its activation.

[0111] In addition, the compression ratio increases from two hundred to one to two hundred to six compared to known systems according to the state of the art, which reduces the temperature increase by about half for the same initial conditions.

[0112] This way, the mechanical shock of sudden pressurization to two hundred bars is mitigated, reducing potential damage to the device, the aircraft and the passengers.

[0113] According to the invention, the maximum instantaneous temperature can locally reach approximately five hundred degrees Celsius at the dead zones in which the gases accumulate, which is still high enough to ignite the elastomers.

[0114] Additional heat management may be required.

[0115] Thus, referring to Figure 12, it is advantageous to further place heat dissipation devices 18, 21 in the oxygen flow circuit 11.

[0116] The heat dissipation devices 18, 21 are, for example, filters and bypass devices intended to prevent the accumulation of hot compressed oxygen at the sensitive components, in particular the elastomer seals, such as that of the valve seat 16, at the time of arrival of the compressed oxygen from the container 1 after activation of the actuator 7.

[0117] These heat dissipation devices 18, 21 are placed at the level of the circulation dead zones where the hot gaseous oxygen accumulates and forms thermal retention zones, in particular in the expander 13.

[0118] These heat sink devices 18,21 are preferably made of sintered brass or the like, which has a very large surface area and excellent thermal conductivity to quickly absorb heat.

[0119] Figures 13 to 15 illustrate that some of the heat dissipation devices 18, 21 can form a hot gas escape 21, in particular an anti-heat escape, formed by the valve seat 16, as an alternative or in addition to the filters arranged in the thermal retention zones of the oxygen flow circuit 11.

[0120] Filters can therefore be placed particularly near sensitive areas to absorb heat, particularly that due to adiabatic compression.

[0121] Thus, these added elements allow gas that would otherwise be compressed in the heated retention areas to be diverted away from the elastomer valve seat 16,

[0122] The use of hot gas vents provides additional protection against adiabatic compression by diverting hot gases to low-risk areas, such as dead ends, away from sealing materials.

[0123] This can be achieved in various ways, as illustrated by the variations of Figures 13, 14 and 15, whether by the geometry of the pressure reducer 13 itself (Figure 13), by dedicated discharge lines 26 (Figure 14) or by positioning the pressure reducer along an existing line (Figure 15).

[0124] These diversions are made using only non-flammable materials, such as brass.

[0125] A secure actuation system is thus produced for actuating its gaseous oxygen supply container to distribute this oxygen within an aircraft, in particular to the pilot through a gas mask, in which any possible oxygen leaks are controlled, thus maintaining the pressure at a safe level, while allowing the temperature to be maintained at a level below the risks of ignition and / or deterioration of the elastomers, by preventing pressurization of the activation circuit, guaranteeing correct activation of the pressure container 1, even in the event of a slow or rapid leak of oxygen from the container, in particular through the seal 9.

Claims

CLAIMS 1. Device for safely actuating a gaseous oxygen supply container in an aircraft for distributing this oxygen to a user, said container (1) being intended to store oxygen under pressure at a first oxygen pressure and having an opening (2) sealed by a seal (9); the device comprising: - a manifold (4) connected in fluid communication with said seal (9) and configured to receive an oxygen flow from said opening (2) when the seal (9) is pierced, said manifold (4) comprising an oxygen flow circuit (11) connected in fluid communication with said seal (9) and having an outlet (14) at a second oxygen pressure lower than the first pressure and a pressure reducer (13) adapted to carry out an oxygen pressure regulation between the opening (2) and said outlet (14) during a flow; and - an actuator (7) in the opening (2) configured to pierce said seal (9) when triggered so as to allow a flow of oxygen through the opening (2) from the container (1) and towards the outlet (14), said device being characterized in that the oxygen flow circuit (11) comprises a calibrated orifice (17) provided at the outlet (14) and configured to prevent any accumulation of oxygen at a third pressure between the first and second pressures in the event of oxygen flow to said outlet (14) in the absence of triggering of the actuator (7).

2. Device according to claim 1, wherein the actuator (7) and the manifold (4) are configured so that the actuator (7) has a deactivated position in which it does not pierce the seal (9) and allows flow into the oxygen flow circuit (11) from the inlet (2), and an activated position in which it pierces the seal sealing (9) and prevents any flow into the oxygen flow circuit (11) from the inlet (2).

3. Device according to any one of claims 1 and 2, further comprising said gaseous oxygen supply container (1), wherein the seal (9) comprises a rupture element (10) configured to facilitate the piercing of said seal (9) when it is subjected to pressure by the actuator (7) during its triggering.

4. Device according to any one of claims 1 to 3, in which the actuator (7) forms a striking rod ending in a hollow needle (8).

5. Device according to any one of claims 1 to 4, wherein the pressure reducer (13) comprises a valve seat (16) made of non-flammable material, an elastic element (15) and an obstruction element (12) mounted in elastic connection between an obstruction position in which it blocks the valve seat (16) and a passage position in which it does not block the valve seat (16), said elastic element (15) pushing said obstruction element (12) towards said opening position and being in the obstruction position when the first pressure is reached on a first side of the valve seat (16) while the second pressure is reached on a second side of the valve seat (16) opposite the first side of the valve seat (16).

6. Device according to any one of claims 1 to 5, further comprising heat dissipation devices (18, 21) placed in the oxygen flow circuit (11).

7. Device according to claim 6, wherein the heat dissipation devices (18,21) comprise a hot gas escape (21) formed by the valve seat (16) and / or filters arranged in the thermal retention zones of the oxygen flow circuit (11).

8. Device according to any one of claims 1 to 7, wherein the calibrated orifice (17) is coupled to a pressure relief valve (19) configured to be manually or automatically to discharge oxygen included in the oxygen flow circuit (11) while the actuator (7) is not triggered.

9. A method of using a device according to claim 8, wherein the pressure relief valve (19) is activated for less than ten seconds before triggering the actuator (7) until the seal (9) breaks.

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