SECURE ACTUATION DEVICE FOR A PRESSURIZED GAS SUPPLY CONTAINER IN AN AIRCRAFT

Abstract

Title: SECURE ACTUATION DEVICE FOR A PRESSURIZED GAS SUPPLY CONTAINER IN AN AIRCRAFT This secure actuation device for a gaseous oxygen supply container in an aircraft to distribute this oxygen to a user, said container (1) being intended to store pressurized oxygen at a first oxygen pressure and having an opening (2) sealed by a sealing gasket (9);the device comprising a manifold (4) connected in fluidic communication with said sealing joint (9) and configured to receive an oxygen flow from said opening (2) when the sealing joint (9) is pierced, said manifold (4) comprising an oxygen flow circuit (11) connected in fluidic communication with said sealing joint (10) and having an outlet (14) at a second oxygen pressure lower than the first pressure and a regulator (13) having oxygen pressure regulation means (12,15,16) between the opening (2) and said outlet (14) during a flow;and an actuator (7) in the opening (2) configured to pierce said sealing joint (9) when triggered so as to permit oxygen flow through the opening (2) from the container (1) and to the outlet (14), the oxygen flow circuit (11) comprising a calibrated orifice (17) provided at the outlet (14) 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). Figure for the abstract: [Fig 8];

Description

Title of the invention: SECURE ACTUATION DEVICE FOR A SUPPLY CONTAINER Pressurized gas in an aircraft technical field

[0001] The present invention relates to emergency oxygen supply devices used in aircraft in the event of depressurization.

[0002] The present invention aims to provide a safe device for triggering the oxygen supply that protects aircraft pilots against hypoxia and smoke by means of a supply of gaseous oxygen from a cylinder regulator assembly (known by the acronym "CRA") which commonly supplies aircraft oxygen masks. Prior Techniques

[0003] US patent 9625102B2 describes the configuration of a sealed cylinder as used in a detention center.

[0004] US patent 11040225B2 describes the activation of such a sealed cylinder.

[0005] In the event of failure of the CRA, 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 EP2916917B1 which includes a redundancy of the CRA, namely two CRA sets, including a standard unsealed CRA, called primary, and a sealed backup CRA, which are connected in parallel and isolated from each other by check valves.

[0006] To activate the sealed CRA, a perforating spring pin pierces a rupture disc located at the top of the cylinder.

[0007] In the case of an unsealed CRA, each cylinder must be maintained with periodic regulator overhauls every five to six years, as well as periodic cylinder strength tests every five years, with regular checks of oxygen quantity and leak locations.

[0008] Such maintenance is costly and intrusive, especially since it is likely to destructively activate the tested CRAs.

[0009] These solutions are activated only in the rare cases where it is necessary, which would reduce the need and cost of maintenance of pressurized oxygen container regulator assemblies during the aircraft's lifetime.

[0010] In particular, the sealed pressurized oxygen container may exhibit slow leaks, affecting the perforation of the rupture disc, a leak from the check valve therefore being able to block the regulator by filling the low pressure circuit.

[0011] Furthermore, the activation of the CRA releases a high-pressure oxygen shock, creating a risk of fire by heating caused by the adiabatic compression of the oxygen released under pressure against certain parts of these prior art systems. Description of the invention

[0012] The invention aims to overcome at least some of the aforementioned drawbacks and to provide a safe actuation device for a gaseous oxygen supply container in an aircraft to distribute this oxygen to be breathed by a user, in particular by means of an oxygen mask, said device being capable of combining advantages of speed, simplicity and reliability for its implementation, and this while minimizing the risks of sudden temperature rise and fire.

[0013] In view of the foregoing, the invention relates to a secure actuation device for a gaseous oxygen supply container 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 sealing gasket; the device comprising:

[0014] - a manifold connected in fluidic communication with said sealing joint and configured to receive an oxygen flow from said opening when the sealing gasket is breached, said manifold comprising an oxygen flow circuit connected in fluidic communication with said sealing gasket and having an outlet at a second oxygen pressure lower than the first pressure and a pressure regulator adapted to perform oxygen pressure regulation between the opening and said outlet during a flow; and - an actuator in the opening configured to pierce said sealing joint when triggered so as to permit oxygen flow through the opening from the container and to the outlet, the oxygen flow circuit including 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.

[0015] In one embodiment, the actuator and the manifold are configured so that the actuator has a deactivated position in which it does not pierce the sealing gasket and allows flow into the oxygen flow circuit from the inlet, and an activated position in which it pierces the sealing gasket and prevents any flow into the oxygen flow circuit from the inlet.

[0016] For example, the device further comprises said supply container gaseous oxygen, and the seal includes a rupture element configured to facilitate the piercing of said seal when it is subjected to pressure by the actuator upon triggering.

[0017] According to one embodiment, the actuator forms a striking rod ending in a hollow needle.

[0018] 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 obstruct 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 to the first side of the valve seat.

[0019] Advantageously, thermal dissipation devices are also placed in the oxygen flow circuit.

[0020] The device may further provide that the heat dissipation devices include a hot gas escape formed by the valve seat and / or filters disposed in the thermal retention areas of the oxygen flow circuit.

[0021] Preferably, the calibrated orifice is coupled to a pressure relief valve configured to be activated manually or automatically to vent oxygen included in the oxygen flow circuit when the actuator is not triggered.

[0022] 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 sealing joint breaks. Brief description of the drawings

[0023] The invention will be better understood upon detailed study of an embodiment taken by way of non-limiting example and illustrated by the accompanying drawings, in which:

[0024] [Fig-1] represents a safe actuation device for an oxygen supply container in an aircraft, according to the prior art.

[0025] [Fig.2] to [Fig.4] represent the means of drilling the sealing joint of the oxygen storage container by the actuator, according to the prior art.

[0026] [Fig.5] represents a situation leading to a faulty activation of the drilling means.

[0027] [Fig.6] represents the actuation device according to the invention.

[0028] [Fig.7] represents a section of the seal bulging due to overpressure of oxygen before it is pierced by the actuator.

[0029] [Fig.8] represents the actuation device with a discharge valve of pressure.

[0030] [Fig.9] represents the overall architecture into which the device can be integrated actuation in an aircraft.

[0031] [Fig. 10] represents the location of the opening in the collector to the circuit of oxygen flow, on a device whose actuator is not triggered.

[0032] [Fig. 11] represents the location of the opening in the collector to the circuit of oxygen flow, on a device whose actuator is triggered.

[0033] [Fig. 12] represents the device with heat sinks in the circuit of oxygen flow.

[0034] [Fig. 13], [Fig. 14] and [Fig. 15] represent the device with a gas escape hot anti-heat coupled with the pressure regulating regulator. Detailed description

[0035] Figures 1 to 5 illustrate an actuation device for 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 for use by a pilot.

[0036] The prior art device comprises a container IA for storing pressurized oxygen, this container comprising an opening 2A sealed by a sealing gasket 9A at the inlet of a manifold 4A receiving oxygen from the container when the sealing gasket 2A is pierced by an actuator and generating a low pressure line 3A via a regulator, and an isolation valve 5A, the assembly enabling the supply of oxygen to another system using oxygen 6A or an oxygen distribution network.

[0037] The device according to the prior art comprises an oxygen storage container IA having a neck with an opening 2A and a collector 4A which is mounted on the neck and which is connected to a supply line 3A.

[0038] 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.

[0039] The device further includes a sealing gasket 9A interposed between the neck and the manifold 4A and an actuator 7A intended to pierce the gasket to cause the regulator to reduce the high pressure to low pressure in order to generate a low pressure oxygen flow in the supply line and thus supply the consumer system 6A.

[0040] This device is capable of generating leaks from container 1A to the 5A isolation valve, rendering it inoperative.

[0041] Fig. 2 illustrates the means of drilling the device according to the prior art of Fig. 1, in the deactivated position.

[0042] They include an actuator 7A equipped with a tip 8A and mounted in translation in the collector 4A so as to be able to pierce the sealing joint 9A of the oxygen storage container, for example at the level of a fragile area 10A provided for this purpose.

[0043] Fig. 3 illustrates the means of drilling the prior art device of Fig. 1 in movement from the deactivated position to the activated position.

[0044] During this movement the needle is pushed towards the joint 9A.

[0045] Figure 4 illustrates the means of drilling the device according to the prior art in activated position, in which the seal 9A has been pierced by the needle, and oxygen from the container escapes through the opening 2A into the collector 4A.

[0046] Fig. 5 shows that in the event of an oxygen leak in the manifold 4A, the prior art device does not allow the evacuation of the overpressure generated in the manifold 4A, which generates a compression force against the movement of the actuator 7A towards the seal 9A, which prevents its perforation and the activation of the device to deliver oxygen to an outlet system 6A.

[0047] Figure 6 illustrates the actuation device according to the invention which makes it possible to overcome this drawback.

[0048] This actuation device is intended in particular to be carried on board an aircraft and to safely operate a gaseous oxygen supply container, in particular to supply an oxygen mask in the event of aircraft depressurization.

[0049] The device may therefore include a gaseous oxygen supply container 1 intended to store oxygen under pressure at a first oxygen pressure, which is a high storage pressure, for example on the order of two hundred bars.

[0050] The container 1 has an opening 2 sealed by a sealing gasket 9.

[0051] The device includes a manifold 4 connected in fluidic communication with said sealing joint 9 and configured to receive a flow of oxygen from said opening 2 when the sealing joint 9 is pierced.

[0052] The manifold 4 includes an oxygen flow circuit 11 connected in fluidic communication with said sealing joint 9.

[0053] The manifold 4 leads, via the pressure 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 on the order of the local ambient pressure in the deactivated state, for example local atmospheric pressure, cabin pressure or a pressure intended for example for the oxygen supply of a passenger compartment, of a device, of an oxygen mask of a pilot or passenger of an aircraft...

[0054] The manifold 4 includes a regulator 13 adapted to perform oxygen pressure regulation between the opening 2 and the outlet 14 during an oxygen flow, for example by means of oxygen pressure regulation means 12,15,16.

[0055] The device includes an actuator 7 inserted into the opening 2.

[0056] The actuator 7 is configured to pierce the sealing gasket 9 when triggered, so as to allow oxygen to flow through the opening 2 from the container 1 and into the low-pressure circuit 14.

[0057] The oxygen flow circuit 11 further includes 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.

[0058] During a leak or activation of the actuator 7, the perforation 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, i.e. without leakage of the seal 9, the third pressure should remain substantially equal to the second pressure.

[0059] 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 13.

[0060] The calibrated orifice 17 allows the pressure in the circuit to be relieved, thus improving the reliability of the activation and ensuring protection against adiabatic compression.

[0061] To protect against pollution, a pressure relief valve can be added to said calibrated orifice 17.

[0062] 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 14, and of preventing 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 sealing gasket 9 is pierced.

[0063] According to one embodiment, the actuator 7 forms a striking rod ending in a needle 8, for example a hollow needle, which allows high-pressure oxygen to be released through the needle once it has pierced the seal 9, channeling oxygen from the container 1 to the outlet 14 and the oxygen supply, thus ensuring efficient activation of the system.

[0064] Preferably, the regulator 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 obstruct the valve seat 16, said elastic element 15 pushing said obstruction element 12 towards said opening position and being in 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 to the first side of the valve seat 16.

[0065] As illustrated by [Fig.7], the sealing gasket 9,9A may have a zone of weakness 10,10A adapted to form a domed zone, under the effect of overpressure or by its shape obtained during its manufacture, for example centrally, in said sealing gasket 9,9A under the effect of overpressure of oxygen before its drilling by the actuator 7.

[0066] For example, the area of ​​weakness 10,10A has a breaking element configured to bulge according to 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 when it is triggered.

[0067] Advantageously, the rupture element 10A forms a disc, elastic to interface the first pressure and the second or third pressure.

[0068] It may include a surface adapted to be convex towards the actuator 7 under the effect of the first pressure.

[0069] It may include a surface that is rigid and convex in shape.

[0070] 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 that there is not enough tensile stress in the sealing joint 9 to promote its rupture when the actuator 7 tries to pierce it, in the manner of a deflated balloon that does not burst unlike an inflated balloon that suffers a complete rupture in the event of contact with a needle.

[0071] Fig. 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 evacuate oxygen included in the oxygen flow circuit 11 when the actuator 7 is not triggered.

[0072] By "automatically", we mean that the operation is carried out passively, without additional intervention by an operator, without necessarily involving piloting or controlling the pressure relief valve 19.

[0073] The pressure relief valve 19 coupled to the calibrated orifice 17, and their method of use, prevent the accumulation of excessive pressure in the event of a minor leak in the system, particularly at the seal 9, and / or between the high pressure in the vessel 1 and the low pressure in the manifold 2 and the circuit of oxygen flow 11, while allowing normal operation of the system when triggered by the activation of actuator 7.

[0074] With the aircraft's flight cycles, the cabin pressure varies, causing the low-pressure circuit to breathe through the calibrated orifice 17, if necessary via the pressure relief valve 19.

[0075] This breathing, or cyclic entry of cabin air, can introduce pollutants that cannot be filtered by a simple mechanical filter, such as humidity which can lead to the degradation of seals and corrosion of components.

[0076] 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.

[0077] The pressure relief valve 19 could be placed upstream or downstream of the calibrated orifice 17, or in it, with similar performance, as illustrated by [Fig.8].

[0078] According to another embodiment, the valve 19 is capable of opening briefly and periodically to relieve any pressure accumulated in the low-pressure circuit.

[0079] 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.

[0080] 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 sealing joint 9 breaks.

[0081] Figures 9 and 10 illustrate that the actuator 7 and the manifold 4 can be configured, in particular by means of 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 sealing gasket 9 and allows flow into the oxygen flow circuit 11 from the passage 20, and an activated position in which it pierces the sealing gasket 9 and prevents any flow into the oxygen flow circuit 11 from the passage 20.

[0082] Figure 9 illustrates a possible architecture for implementing the invention in an aircraft.

[0083] This architecture includes, for example, two examples of container 1, one of which is sealed and one unsealed.

[0084] The unsealed container is configured for example to store oxygen at about 1,800 psi (pounds per square inch) or 127 bars.

[0085] It is coupled to a pressure regulator 13 adapted to reduce the pressure to a few bars, for example about five bars.

[0086] 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 onboard electronic system 24 of the aircraft to allow low pressure oxygen to be distributed via check valves 19 to the aircraft pilots' masks 25 for use in an emergency.

[0087] To further increase capacity and / or ensure redundancy in case of failure of the first container, the second sealed cylinder is added in parallel with the first.

[0088] The two containers 1 are isolated from each other by the check 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 by the same leak.

[0089] The second container 1 in the known solutions of the prior 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 allows the second container to be used as a sealed backup container which is activated only in the event of failure of the main container, the detection of said failure being done via an additional low pressure switch 22 located upstream of the non-return valve 19 of the first container 1.

[0090] The sealed container 1 can thus be electrically activated by control means 23 coupled to a computer of the embedded system 24.

[0091] In addition, the calibrated orifice 4 prevents pressure buildup in the low-pressure circuit, thus ensuring proper activation by the actuator 7.

[0092] 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.

[0093] Thus, the calibrated orifice 17 is open ([Fig.10]) when the actuator 7 is deactivated, i.e. in the raised position revealing the oxygen flow circuit 11 at the level of the passage 20, and closed ([Fig. 11]) when the actuator 7 is activated, i.e. in the lower pressed position, obstructing the oxygen flow circuit 11 at the level of the passage 20.

[0094] The calibrated orifice 17 can thus be positioned in an open position allowing breathing ventilation as described above as long as the actuator 7 has not yet was activated, and closed once activated.

[0095] When the actuator 7 is activated, gas at ambient pressure accumulates in the manifold 4 and in the regulator 13, which causes a rapid and substantially adiabatic compression of the gas in a dead zone in which it is compressed.

[0096] This is calculated using the following ideal gas law equation in a reversible adiabatic process:

[0097] P^r.Tv = constant

[0098] in which:

[0099] P represents the initial pressure of the gas,

[0100] y is the adiabatic coefficient, namely the ratio of the heat capacities at constant pressure and constant volume, and

[0101] T is the absolute temperature of the gas.

[0102] Using the example of a gas under a pressure of one bar at twenty degrees Celsius in the regulator 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.

[0103] At such temperatures in pure oxygen, most elastomers spontaneously ignite, in particular that of the valve seat 16 which is often made of elastomer for its sealing properties, elasticity, ease of manufacture at lower cost.

[0104] 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.

[0105] 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.

[0106] The gas immediately next to the valve seat 16 is then adiabatically compressed from six bars to two hundred bars under the effect of oxygen from the container 1, which is cooled slightly during its expansion by Joule-Thompson effect before heating up during recompression.

[0107] The invention thus makes it possible to mitigate the dangerous high temperatures during its activation.

[0108] Moreover, the compression ratio goes from two hundred to one to two hundred to six compared to systems known according to the prior art, which reduces the temperature increase by about half for the same initial conditions.

[0109] Thus, the mechanical shock of the sudden pressurization to two hundred bars is attenuated, This reduces potential damage to the device, the aircraft, and the passengers.

[0110] According to the invention, the maximum instantaneous temperature can locally reach approximately five hundred degrees Celsius in the dead zones where gases accumulate, which is still high enough to ignite the elastomers.

[0111] Additional heat management may be required.

[0112] Thus, referring to [Fig.12], it is advantageous to place further thermal dissipation devices 18,21 in the oxygen flow circuit 11.

[0113] The thermal 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 the arrival of compressed oxygen from the container 1 after activation of the actuator 7.

[0114] These thermal dissipation devices 18,21 are placed at the circulation dead zones where hot gaseous oxygen accumulates and forms thermal retention zones, particularly in the regulator 13.

[0115] These heat dissipation devices 18,21 are preferably made of sintered brass or similar, which has a very large surface area and excellent thermal conductivity to rapidly absorb heat.

[0116] Figures 13 to 15 illustrate that some of the thermal dissipation devices 18,21 can form a hot gas escape 21, in particular anti-heat, formed by the valve seat 16, as an alternative or in addition to the filters disposed in the thermal retention areas of the oxygen flow circuit 11.

[0117] The filters can therefore be placed in particular near sensitive areas to absorb heat, especially that due to adiabatic compression.

[0118] Thus, these added elements make it possible to divert away from the elastomer valve seat 16 the gas which would otherwise be compressed in the heated retention areas,

[0119] The use of hot gas escapes forms an additional protection against adiabatic compression consisting of diverting hot gases to low risk areas, in particular to dead ends, away from the sealing materials.

[0120] This can be achieved in various ways, as illustrated by the variants in Figures 13, 14 and 15, either by the geometry of the regulator 13 itself ([Fig. 13]), by dedicated discharge lines 26 ([Fig. 14]) or by positioning the pressure reducer along an existing line ([Fig. 15]).

[0121] These diversions are carried out using only non-flammable materials, such as brass.

[0122] A secure actuation system is thus provided for actuating its gaseous oxygen supply container to distribute this oxygen within of an aircraft, in particular to the pilot through a gas mask, in which possible leaks of oxygen 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, preventing pressurization of the activation circuit, ensuring correct activation of the pressure vessel 1, even in the event of slow or rapid leakage of oxygen from the vessel, in particular through the sealing joint 9.

Claims

Demands

1. A secure actuation device for a gaseous oxygen supply container in an aircraft to distribute such 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 sealing gasket (9); the device comprising: - a manifold (4) connected in fluidic communication with said sealing gasket (9) and configured to receive an oxygen flow from said opening (2) when the sealing gasket (9) is punctured, said manifold (4) comprising an oxygen flow circuit (11) connected in fluidic communication with said sealing gasket (9) and having an outlet (14) at a second oxygen pressure lower than the first pressure and a regulator (13) adapted to perform 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 sealing joint (9) when triggered so as to permit a flow of oxygen through the opening (2) from the container (1) and to the outlet (14), said device being characterized in that the oxygen flow circuit (11) includes 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 puncture the sealing gasket (9) and allows flow into the oxygen flow circuit (11) from the inlet (2), and an activated position in which it punctures the sealing gasket (9) and prevents any flow into the oxygen flow circuit (11) from the inlet (2).

3. A device according to any one of claims 1 and 2, further comprising said gaseous oxygen supply container (1), in which the sealing gasket (9) comprises a rupture element (10) configured to facilitate piercing said sealing gasket (9) when it is subjected to pressure by the actuator (7) when it is triggered.

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

5. A device according to any one of claims 1 to 4, wherein the regulator (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 obstruct 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 to the first side of the valve seat (16).

6. Device according to any one of claims 1 to 5, further comprising thermal 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 disposed in the heat 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 actuated to vent oxygen included in the oxygen flow circuit (11) when 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 sealing gasket (9) breaks.

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