Device for safely actuating pressurized gas supply container in aircraft

Abstract

The invention relates to a device for safely actuating a gaseous oxygen supply container in an aircraft for dispensing oxygen to a user, the container (1) being intended to store pressurized oxygen at a first oxygen pressure and having an opening (2) sealed by a seal (9). The apparatus comprises: a manifold (4) connected in fluid communication with the seal (9) and configured to receive a flow of oxygen from the opening (2) when the seal (9) is pierced, the manifold (4) comprising an oxygen flow circuit (11), an oxygen flow circuit connected in fluid communication with the seal (10) and having an outlet (14) at a second oxygen pressure lower than the first pressure and a pressure reducer (13) having means (12, 15, 16) for regulating the oxygen pressure between the opening (2) and the outlet (14) during flow; and an actuator (7) located in the opening (2), the actuator being configured to pierce the seal (9) when triggered to allow oxygen to flow from the container (1) through the opening (2) to the outlet (14), the oxygen flow circuit (11) comprising a calibration aperture (17) provided at the outlet (14), the calibration aperture is configured to prevent any accumulation of oxygen at a third pressure between the first pressure and the second pressure without triggering the actuator (7) in the event that oxygen flows to the outlet (14).

Description

Technical Field

[0001] This invention relates to an emergency oxygen supply device for use in aircraft under decompression conditions.

[0002] The present invention aims to construct a safety device for triggering oxygen supply, which protects the pilot of an aircraft from hypoxia and smoke by providing gaseous oxygen from the cylinder regulator assembly (CRA) that typically supplies oxygen masks to aircraft. Background Technology

[0003] Patent US9625102B2 describes the configuration of a sealed gas cylinder used in a CRA.

[0004] Patent US11040225B2 describes the activation of this sealed gas cylinder.

[0005] In the event of a CRA failure, it is known to use a second CRA as a backup solution to prevent the pilot from being without respiratory protection in the event of a cabin pressure drop. This is described, for example, in patent EP2916917B1, which includes CRA redundancy, namely two CRA components, including a standard unsealed CRA (referred to as the primary CRA) and a sealed backup CRA, which are connected in parallel and isolated from each other by a check valve.

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

[0007] In the case of an unsealed CRA, each cylinder must undergo a regulator overhaul every five to six years, and cylinder durability tests must also be performed every five years, with regular checks on oxygen levels and leak locations.

[0008] This maintenance is expensive and invasive, especially since it may damage the CRA being tested.

[0009] These solutions are only activated in rare, necessary circumstances, which will reduce the need and cost of maintaining pressurized oxygen container regulator components throughout the aircraft's lifespan.

[0010] In particular, sealed pressurized oxygen containers may have slow leaks that can affect rupture disc perforation, so a leak in the check valve may block the regulator by filling the low-pressure circuit.

[0011] Furthermore, the activation of CRA releases a high-pressure oxygen surge, which can create a fire hazard due to the heating caused by the adiabatic compression of certain components of these existing technology systems by the oxygen released under pressure. Summary of the Invention

[0012] The present invention aims to overcome at least some of the disadvantages mentioned above and to provide a device for safely actuating a gaseous oxygen supply container in an aircraft to distribute oxygen (particularly via an oxygen mask) for the user to breathe, the device being able to combine the advantages of speed, simplicity and reliability in its implementation, which is achieved by minimizing the risk of sudden temperature rise and fire.

[0013] In view of the foregoing, the object of the present invention is a device for safely actuating a gaseous oxygen supply container in an aircraft to distribute oxygen to a user, the container being designed to store pressurized oxygen at a first oxygen pressure and having an opening sealed by a seal. The device has: - A manifold fluidly connected to the seal and configured to receive an oxygen flow from the opening when the seal is punctured, the manifold including an oxygen flow loop fluidly connected to the seal, and having an outlet at a second oxygen pressure below the first pressure and a pressure regulator adapted to perform oxygen pressure regulation between the opening and the outlet during flow; and - An actuator located in the opening, configured to puncture the seal when triggered to allow oxygen to flow from the container through the opening to the outlet, the oxygen flow circuit including a calibration orifice disposed at the outlet, the calibration orifice being configured to prevent any accumulation of oxygen at a third pressure between the first pressure and the second pressure when oxygen flows to the outlet without triggering the actuator.

[0014] In one embodiment, the actuator and the manifold are configured to place the actuator in a deactivated position and an activated position, in the deactivated position the actuator does not puncture the seal and allows flow from the inlet into the oxygen flow circuit, and in the activated position the actuator punctures the seal and prevents flow from the inlet into the oxygen flow circuit.

[0015] For example, the device also includes the gaseous oxygen supply container, and the seal includes a rupture element configured to puncture the seal when the seal is subjected to pressure from the actuator when the actuator is triggered.

[0016] According to one embodiment, the actuator forms an impact rod that terminates with a hollow needle.

[0017] Preferably, the pressure reducer includes a valve seat, an elastic element, and a blocking element. The valve seat is made of a non-flammable material, and the blocking element is elastically connected between a blocked position and a flow position. In the blocked position, the blocking element blocks the valve seat, and in the flow position, the blocking element does not block the valve seat. The elastic element is configured to push the blocking element toward the open position, and to place the blocking element in the blocked position when a first pressure is reached on a first side of the valve seat and a second pressure is reached on a second side of the valve seat opposite to the first side.

[0018] Advantageously, heat dissipation equipment is also installed in this oxygen flow circuit.

[0019] The device may also provide: these heat dissipation devices include a hot gas discharge device formed by the valve seat and / or a filter disposed in the heat retention zone of the oxygen flow circuit.

[0020] Preferably, the calibration orifice is coupled to a pressure relief valve configured to be activated manually or automatically to release oxygen contained in the oxygen flow circuit when the actuator is not triggered.

[0021] The present invention also relates to a method in which a pressure relief valve is activated for less than ten seconds before the actuator is triggered, until the seal ruptures. Attached Figure Description

[0022] A better understanding of the invention will come from a detailed study of one embodiment, which is considered a non-limiting example and is illustrated by the accompanying drawings, in which: [ Figure 1 This illustrates a device for safely actuating an oxygen supply container in an aircraft, based on existing technology.

[0023] [ Figure 2 ]to[ Figure 4 The image shows a device according to the prior art for piercing the seal of an oxygen storage container by means of an actuator.

[0024] [ Figure 5 This illustrates a situation that leads to the puncture device being erroneously activated.

[0025] [ Figure 6 The actuation device according to the present invention is shown.

[0026] [ Figure 7 The image shows a cross-section of a seal that had been bulging into a dome shape due to oxygen overpressure before being punctured by the actuator.

[0027] [ Figure 8 The image shows an actuation device with a pressure relief valve.

[0028] [ Figure 9This illustrates the overall architecture in which actuation devices can be integrated into an aircraft.

[0029] [ Figure 10 This shows the location of the opening in the manifold leading to the oxygen flow circuit on a device where the actuator is not triggered.

[0030] [ Figure 11 This shows the location of the opening in the manifold leading to the oxygen flow circuit on the device where the actuator is triggered.

[0031] [ Figure 12 This illustrates a device with a radiator in an oxygen flow circuit.

[0032] [ Figure 13 ]、[ Figure 14 ]and[ Figure 15 The device shown has a heat-resistant hot gas discharge device coupled to a pressure regulating regulator. Detailed Implementation

[0033] Figures 1 to 5 An apparatus for actuating an oxygen supply container in an aircraft, according to the prior art, is shown. The apparatus includes an oxygen supply container located in the aircraft for distributing oxygen to a user, particularly to an oxygen mask intended for use by a pilot.

[0034] The prior art device includes: a container 1A designed to store pressurized oxygen, the container including an opening 2A sealed by a seal 9A at the inlet of a manifold 4A, the opening receiving oxygen from the container when the seal 2A is punctured by an actuator, and the container generating a low-pressure line 3A via a pressure reducer; and an isolation valve 5A, the assembly enabling oxygen to be supplied to another system using oxygen 6A or an oxygen distribution network.

[0035] The device according to the prior art includes an oxygen storage container 1A, which includes a neck with an opening 2A and a manifold 4A, which is mounted on the neck and connected to a supply line 3A.

[0036] Manifold 4A is connected to supply line 3A equipped with isolation valve 5A, and consumption system 6A is connected to this supply line.

[0037] The device also includes a seal 9A placed between the neck and the manifold 4A and an actuator 7A designed to puncture the seal so that the pressure reducer reduces the high pressure to a low pressure, thereby creating a low-pressure oxygen flow in the supply line and thus supplying the consumption system 6A.

[0038] The device may leak from container 1A to isolation valve 5A, rendering the device inoperable.

[0039] Figure 2 It shows that according to Figure 1 The existing technology of puncture devices in a discontinued position.

[0040] The puncture device includes an actuator 7A, which is provided with a tip 8A and is mounted in a translational manner in a manifold 4A so as to be able to puncture the seal 9A of the oxygen storage container, for example, at a weak point 10A provided for this purpose.

[0041] Figure 3 A diagram showing the method of piercing Figure 1 The device of the prior art equipment moves from the deactivated position to the activated position.

[0042] During this movement, the needle is pushed toward the seal 9A.

[0043] Figure 4 The diagram shows a puncture device in the activated position according to the prior art, wherein the seal 9A has been punctured by a needle and oxygen in the container escapes through the opening 2A into the manifold 4A.

[0044] Figure 5 The diagram illustrates that in the event of an oxygen leak in manifold 4A, the prior art equipment does not allow the discharge of the overpressure generated in manifold 4A, which produces a compressive force opposite to the displacement of actuator 7A toward seal 9A. This prevents actuator 7A from puncturing and activating the system to deliver oxygen to outlet 6A.

[0045] Figure 6 An actuation device according to the invention is shown, which enables this disadvantage to be overcome.

[0046] This actuation device is specifically designed to be installed on aircraft and to safely actuate containers used to supply gaseous oxygen, particularly for supplying oxygen masks during aircraft decompression.

[0047] Therefore, the device may include a gaseous oxygen supply container 1, which is designed to store pressurized oxygen at a first oxygen pressure, which is a high storage pressure, such as about two hundred bar.

[0048] Container 1 includes an opening 2 sealed by a seal 9.

[0049] The device includes a manifold 4 which is fluidly connected to the seal 9 and is configured to receive an oxygen flow from the opening 2 when the seal 9 is punctured.

[0050] The manifold 4 includes an oxygen flow circuit 11 that is fluidly connected to the seal 9.

[0051] Manifold 4 leads to low-pressure distribution circuit 14 via pressure reducer 13. Low-pressure distribution circuit 14 forms a low-pressure outlet 14 at a second oxygen pressure below the first pressure. The second oxygen pressure is, for example, within the range of local ambient pressure when out of service, such as local atmospheric pressure, cabin pressure, or pressure intended to supply oxygen, for example, to the interior of a vehicle, equipment, or oxygen masks for aircraft pilots or passengers.

[0052] Manifold 4 includes pressure regulator 13, which is adapted to perform oxygen pressure regulation between opening 2 and outlet 14 during oxygen flow, for example by means of oxygen pressure regulating devices 12, 15, 16.

[0053] The device includes an actuator 7 that is inserted into the opening 2.

[0054] Actuator 7 is configured to puncture seal 9 when triggered, thereby allowing oxygen to flow from container 1 through opening 2 to low-pressure circuit 14.

[0055] The oxygen flow circuit 11 also includes a calibration port 17 located at the outlet 14, which is configured to prevent any accumulation of oxygen at a third pressure between the first and second pressures when oxygen flows into the low-pressure circuit 14 without triggering the actuator 7.

[0056] In the event of a leak or activation of actuator 7, puncture of seal 9 causes the third pressure to increase to the first pressure. In the off-state and normal operation, i.e., when there is no leak in seal 9, the third pressure must remain substantially equal to the second pressure.

[0057] The calibration port 17 is provided, for example, in the low-pressure section of the system, such as in the outlet 14 downstream of the pressure reducer 13.

[0058] The calibration hole 17 allows pressure to be released in the circuit, thereby improving the reliability of activation and providing protection against adiabatic compression.

[0059] To prevent contamination, a pressure relief valve can be added to the calibration port 17.

[0060] Therefore, the calibration hole 17 allows for improved reliability of actuator 7 activation and prevents fire by preventing pressure buildup in the oxygen flow circuit 11, particularly in the pressure reducer 13 and at the outlet 14, as well as preventing the pressure reducer 13 from closing. This allows hot gas that may have accumulated on and around the seat 16 of the pressure reducer 13 during the adiabatic compression that occurs when the seal 9 is punctured to be discharged into the low-pressure (LP) circuit.

[0061] According to one embodiment, the actuator 7 forms an impact rod terminating at a needle 8 (e.g., a hollow needle), which allows high-pressure oxygen to be released through the needle once the needle pierces the seal 9, thereby ensuring effective activation of the system by guiding the oxygen from the container 1 to the outlet 14 and the oxygen supply unit.

[0062] Preferably, the pressure reducer 13 includes a valve seat 16, an elastic element 15, and a blocking element 12. The valve seat is made of a non-flammable material, and the blocking element is installed in an elastic connection between a blocked position and a flow position. In the blocked position, the blocking element blocks the valve seat 16, and in the flow position, the blocking element does not block the valve seat 16. The elastic element 15 pushes the blocking element 12 toward the open position, and the blocking element is in the blocked position when the first side of the valve seat 16 reaches a first pressure and the second side of the valve seat 16 opposite to the first side reaches a second pressure.

[0063] like Figure 7 As shown, the seals 9 and 9A may include weak areas 10 and 10A, which are adapted to form dome-shaped areas under overpressure or by the shape obtained during the manufacturing process, for example, forming a dome-shaped area at the center of the seals 9 and 9A under oxygen overpressure before being punctured by the actuator 7.

[0064] For example, weak areas 10, 10A include a rupture element configured to bend according to overpressure on one side and to facilitate puncturing seals 9, 9a when the actuator 7 is subjected to pressure from the actuator.

[0065] Advantageously, the rupture element 10A forms a resilient disc to engage with the first pressure and the second or third pressure.

[0066] The rupture element may include a surface adapted to bend toward the actuator 7 under the action of a first pressure.

[0067] A fracture element may include a rigid surface that has a curved shape.

[0068] In reality, when the seal 9 is subjected to considerable pressure on each side, for example, if the seal is subjected to equivalent pressure on one side of the manifold 4 due to oxygen leakage in the direction toward the manifold, there is usually not enough tensile stress in the seal 9 to cause the seal to rupture when the actuator 7 attempts to puncture the seal 9. This is like a deflated balloon that does not burst, unlike an inflated balloon that bursts completely when it comes into contact with a needle.

[0069] Figure 8 The calibration port 17 is shown to also be coupled (e.g., in series) to a pressure relief valve 19, which can be activated manually or automatically to discharge oxygen contained in the oxygen flow circuit 11 when the actuator 7 is not triggered.

[0070] "Automatically" should be understood as the operation being passive, requiring no additional intervention from the operator, and not involving control or servo control of the pressure relief valve 19.

[0071] The pressure relief valve 19 coupled to the calibration port 17 and its method of use have the effect of preventing excessive pressure buildup in the system, particularly at the seal 9, and / or between the low-pressure side of the high-pressure manifold 2 in the container 1 and the oxygen flow circuit 11 in the event of a slight leak, while enabling the system to operate normally when triggered by the activation of the actuator 7.

[0072] As the aircraft cycles through flight, cabin pressure changes, causing the low-pressure circuit to breathe through calibration port 17 and, if necessary, through pressure relief valve 19.

[0073] This periodic intake of breathing or cabin air can introduce contaminants that cannot be filtered out by simple mechanical filters, such as moisture that can lead to seal degradation and component corrosion.

[0074] The pressure relief valve 19 allows the system to be effectively shut off from external contaminants and maintains a third pressure or internal pressure higher than the second pressure or cabin pressure, but lower than the first pressure or the shut-off pressure of the pressure regulator 13, provided that the set pressure of the pressure relief valve 19 is below the pressure range of the pressure regulator 13, for example, one to three bar.

[0075] like Figure 8 As shown, the pressure relief valve 19 can be located upstream or downstream of the calibration port 17, or located within the calibration port, and has similar performance.

[0076] According to another embodiment, valve 19 can be opened briefly and periodically to release any pressure buildup in the low-pressure circuit.

[0077] This valve 19 can be activated, for example, remotely and automatically, or manually during regular maintenance, or even briefly before activating the actuator 7 and releasing oxygen into the oxygen flow circuit 11.

[0078] The invention also relates to a method in which a pressure relief valve 19 is activated for a predetermined duration (e.g., less than 10 seconds) before triggering the actuator 7, until the seal 9 ruptures.

[0079] Figure 9 and Figure 10The actuator 7 and manifold 4 are shown to be configured, particularly due to the position of the channel 20 in the manifold 4, such that the actuator 7 has a deactivated position and an activated position, in which the actuator does not puncture the seal 9 and allows flow from the channel 20 into the oxygen flow circuit 11, and in the activated position, the actuator punctures the seal 9 and blocks any flow from the channel 20 into the oxygen flow circuit 11.

[0080] Figure 9 A possible architecture for positioning the present invention in an aircraft is shown.

[0081] This architecture includes, for example, two samples in container 1, one of which is sealed and the other is unsealed.

[0082] Unsealed containers are configured, for example, to store oxygen at a pressure of approximately 1,800 pounds per square inch (psi) or 127 bar.

[0083] The container is coupled to a pressure regulator 13, which is adapted to reduce the pressure to a few bar, for example, about five bar.

[0084] The low-pressure switch 22 detects whether the pressure is higher than the minimum operating pressure (e.g., 3 bar) and sends a signal to the avionics equipment included in the aircraft's onboard electronic system 24 to allow low-pressure oxygen to be distributed via check valve 19 to the aircraft pilot's mask 25 for use in an emergency.

[0085] To further increase capacity and / or provide redundancy in the event of failure of the first container, a sealed second gas cylinder was added to be connected in parallel with the first gas cylinder.

[0086] The two containers 1 are isolated from each other by a check valve 19, so that in the event of a serious leak in one container 1, the contents of the other container will not be emptied due to the same leak.

[0087] The second container 1 in known prior art solutions requires regular maintenance, including, for example, frequent quantity checks, functional tests, replacement of elastomeric seals in the regulator, hydrostatic tests to check for cracks in the gas cylinder, etc. The actuation system according to the invention allows the second container to be used as a sealed backup container, which is only activated in the event of a failure in the main container, the failure being detected via an additional low-pressure switch 22 located before the check valve 19 of the first container 1.

[0088] Therefore, the sealed container 1 can be activated by a control device 23 of a computer coupled to the airborne system 24.

[0089] In addition, the calibration hole 4 prevents pressure buildup in the low-pressure circuit, thereby ensuring proper activation of the actuator 7.

[0090] The pressure relief valve 13, aligned with the calibration port 17, is positioned below the operating pressure of the low-pressure circuit under the second pressure, thereby preventing contamination of the downstream pipeline by maintaining positive pressure.

[0091] Therefore, when actuator 7 is deactivated, i.e., in the raised position of oxygen flow circuit 11 at exposed channel 20, calibration port 17 is open. Figure 10 When actuator 7 is activated, i.e., in the depressed low position, calibration port 17 is closed. Figure 11 This blocks the oxygen flow loop 11 at channel 20.

[0092] Therefore, as long as the actuator 7 is not activated, the calibration port 17 can be positioned in an open manner that allows breathing (as described above), and once the actuator 7 is activated, the calibration port 17 is closed.

[0093] When actuator 7 is activated, gas at ambient pressure accumulates in manifold 4 and pressure reducer 13, which results in rapid and substantially adiabatic compression of the gas in the dead-end region (where the gas is compressed).

[0094] This is calculated using the ideal gas law equations for a reversible adiabatic process, as shown below:

[0095] in: P represents the initial gas pressure. γ is the adiabatic coefficient, which is the ratio of heat capacity at constant pressure to that at constant volume, and t is the absolute gas temperature.

[0096] Taking a gas at a pressure of one bar and a temperature of twenty degrees Celsius in pressure regulator 13 (which is subsequently compressed to two hundred bar) as an example, the final temperature of the adiabatic compressed gas is one thousand fifty-eight degrees, where γ equals 1.4.

[0097] At such a pure oxygen temperature, most elastomer materials will spontaneously combust, especially the material of valve seat 16. Due to the sealing performance, elasticity, and ease of low-cost manufacturing of elastomer materials, valve seat 16 is usually made of elastomer materials.

[0098] Therefore, it is advantageous to keep the calibration port 17 open so that the compressed gas is not confined at the valve seat 13, but is pushed through the low-pressure side, i.e., into the oxygen flow circuit 11, which requires a relatively large volume in the pipeline to slowly diffuse the flow.

[0099] Therefore, in this situation, the low-pressure side has reached a specific pressure, for example, within the range of six bar, and thus the pressure reducer 13 is blocked by the compressed oxygen in the activation chamber on the low-pressure side.

[0100] The gas adjacent to valve seat 16 is adiabatically compressed from six bar to two hundred bar by the Joule-Thompson effect under the influence of oxygen from slightly cooled container 1 during its expansion, and is subsequently heated during recompression.

[0101] Therefore, the present invention can mitigate dangerous high temperatures when it is activated.

[0102] Furthermore, compared to known systems based on existing technology, the compression ratio changes from 200:1 to 200:6, which reduces the temperature increase by about half under the same initial conditions.

[0103] Therefore, the mechanical impact of suddenly increasing the pressure to 200 bar is reduced, thereby minimizing potential damage to equipment, aircraft, and passengers.

[0104] According to the present invention, in the dead zone where gas accumulates, the instantaneous maximum temperature can locally reach about 500 degrees Celsius, which is still high enough to ignite the elastomer material.

[0105] Additional heat management may be required.

[0106] Therefore, refer to Figure 12 It is advantageous to further install heat dissipation devices 18 and 21 in the oxygen flow circuit 11.

[0107] The heat dissipation devices 18 and 21 are, for example, filters and bypass devices, designed to prevent hot compressed oxygen from accumulating on sensitive parts, particularly elastomeric seals (e.g., the elastomeric seal of valve seat 16), when compressed oxygen arrives from container 1 after actuator 7 is activated.

[0108] These heat dissipation devices 18 and 21 are located in the circulation dead zone, where hot gaseous oxygen accumulates and forms a heat retention zone, especially in the pressure reducer 13.

[0109] These heat dissipation devices 18 and 21 are preferably made of sintered brass or the like, which have a very large surface area and excellent thermal conductivity to quickly absorb heat.

[0110] Figures 13 to 15 Some of the heat dissipation devices 18 and 21 are shown as hot gas discharge devices 21 formed by valve seats 16, and in particular heat protection devices, as alternatives to or supplements to filters provided in the heat retention zone of the oxygen flow circuit 11.

[0111] Therefore, filters can be placed near sensitive areas to absorb heat, especially heat generated by adiabatic compression.

[0112] Therefore, these added elements allow the gas, which would otherwise be compressed in the heated holding zone, to be diverted away from the elastomer seat 16.

[0113] By redirecting hot gas to a low-risk area away from the sealing material (such as the dead end), the use of hot gas venting devices provides additional protection against adiabatic compression.

[0114] This can be achieved through various means (such as) Figure 13 , Figure 14 and Figure 15 As shown in the variation, regardless of the geometry of the pressure reducer 13 itself ( Figure 13 ), or through dedicated discharge pipeline 26 ( Figure 14 ), or by positioning the pressure reducer along the existing pipeline ( Figure 15 To achieve this.

[0115] These steering mechanisms are made using only non-combustible materials such as brass.

[0116] Therefore, a safety actuation system is implemented that allows actuation of its gaseous oxygen supply container to distribute oxygen into the aircraft, particularly to the pilot via a gas mask, wherein any oxygen leakage is controlled, thereby maintaining pressure at a safe level, while allowing temperature to be maintained below the risk of ignition and / or degradation of the elastomeric material by preventing pressurization of the actuation circuit, ensuring proper activation of the pressurized container 1 even in the event of slow or rapid oxygen leakage from the container, particularly through seal 9.

Claims

1. A device for safely actuating a gaseous oxygen supply container in an aircraft to distribute oxygen to a user, said container (1) being designed to store pressurized oxygen at a first oxygen pressure and having an opening (2) sealed by a seal (9). The device has: - A manifold (4), which is fluidly connected to the seal (9) and configured to receive an oxygen flow from the opening (2) when the seal (9) is punctured, the manifold (4) including an oxygen flow circuit (11), which is fluidly connected to the seal (9), and having an outlet (14) at a second oxygen pressure lower than the first pressure and a pressure regulator (13) adapted to perform oxygen pressure regulation between the opening (2) and the outlet (14) during flow; and - An actuator (7) located in the opening (2) is configured to puncture the seal (9) when triggered to allow oxygen to flow from the container (1) through the opening (2) to the outlet (14). The device is characterized in that the oxygen flow circuit (11) includes a calibration hole (17) disposed at the outlet (14), the calibration hole being configured to prevent any accumulation of oxygen at a third pressure between the first pressure and the second pressure when oxygen flows to the outlet (14) without triggering the actuator (7).

2. The device according to claim 1, wherein, The actuator (7) and the manifold (4) are configured to place the actuator (7) in a deactivated position and an activated position, in the deactivated position, the actuator does not puncture the seal (9) and allows flow from the inlet (2) into the oxygen flow circuit (11), and in the activated position, the actuator punctures the seal (9) and blocks any flow from the inlet (2) into the oxygen flow circuit (11).

3. The apparatus according to any one of claims 1 and 2, further comprising the gaseous oxygen supply container (1), wherein, The seal (9) includes a rupture element (10) configured to puncture the seal (9) when the seal (9) is subjected to pressure from the actuator (7) when the actuator (7) is triggered.

4. The device according to any one of claims 1 to 3, wherein, The actuator (7) forms an impact rod terminated by a hollow needle (8).

5. The device according to any one of claims 1 to 4, wherein, The pressure reducer (13) includes a valve seat (16), an elastic element (15), and a blocking element (12). The valve seat is made of a non-flammable material. The blocking element is installed in an elastic connection between a blocked position and a flow position. In the blocked position, the blocking element blocks the valve seat (16). In the flow position, the blocking element does not block the valve seat (16). The elastic element (15) pushes the blocking element (12) toward the open position. When the first pressure is reached on the first side of the valve seat (16) and the second pressure is reached on the second side of the valve seat (16) opposite to the first side, the blocking element is placed in the blocked position.

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

7. The device according to claim 6, wherein, The heat dissipation device (18, 21) includes a hot gas discharge device (21) formed by the valve seat (16) and / or a filter disposed in the heat retention zone of the oxygen flow circuit (11).

8. The device according to any one of claims 1 to 7, wherein, The calibration port (17) is coupled to a pressure relief valve (19), which is configured to be activated manually or automatically to discharge oxygen contained in the oxygen flow circuit (11) when the actuator (7) is not triggered.

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

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