Aircraft lavatory oxygen source

0001Cross-reference of related applications This application is the priority of provisional application 61 / 724,772 filed November 9, 2012 and non-provisional application 14 / 073,590 filed November 6, 2013, which are incorporated herein by reference. Claim profit.

0002The present invention generally relates to an emergency oxygen supply system mounted on a commercial aircraft as prescribed so that it can be deployed when cabin pressure drops. In particular, the present invention relates to an aircraft washroom oxygen source that should be used during decompression to prevent a result known as hypoxia.

0003Emergency oxygen supply systems are typically installed on aircraft to supply oxygen to passengers during low cabin pressure at altitudes above about 10,000 feet. Such systems generally include face masks that are released from the overhead storage compartment when needed to cover the mouth and nose. The supplemental oxygen supplied by the mask increases blood oxygen saturation levels in the mask user beyond the levels that would be experienced when inhaling ambient air at widespread room pressure altitude conditions. The oxygen flow provided by this is calculated to be sufficient to keep all passengers until the cabin pressure is restored or until a lower and safer altitude can be reached.

0004In general, passenger aircraft have been equipped with oxygen sources in the cabin area and passenger washrooms with an emergency oxygen mask that falls to supply oxygen to the passengers during decompression of the aircraft at high altitudes. It was. One conventional system for supplying oxygen to the cabin of an aircraft is known, which includes multiple chemical oxygen generators with an igniter and a sequencer to activate the igniter in sequence, and oxygen. Including the mask, the chemical generator distributes the generated oxygen to the oxygen mask. The pressure sensor, which forms part of the distribution system, controls the sequencer to sequentially activate the igniters of the next chemical generator whenever the pressure drops below the threshold. Other conventional systems for supplying emergency oxygen to passengers in the aircraft are known, and this system houses at least one breathing mask and an exothermic chemical oxygen generator connected to the breathing mask. Includes mounting container.

0005However, for aircraft in certain passenger transport categories with a passenger capacity of 20 or more, the Federal Aviation Administration (FAA) has recently been working to eliminate possible hazards from the placement of chemical oxygen generators in aircraft washrooms. Operate all chemical oxygen generators in the washroom until the oxygen source of the generator is exhausted, or remove the oxygen generator and oxygen after the generator is exhausted or removed. Requested that the mask be removed or re-stored to close the mask distribution door in the washroom. Flight attendants should now check to see if the washroom is blocked when cabin decompression occurs in an attempt to provide assistance to any passenger in the washroom with regard to obtaining emergency oxygen quickly. You are instructed. However, in the event of a washroom occupant locking the washroom door and collapsing the washroom occupant during such a cabin decompression situation, the flight attendant may provide assistance to the washroom occupant in obtaining emergency oxygen. At least prevent that.

<p num="0006"> However, more recently, with a further review, the FAA has called for an alternative oxygenation system to be installed within each washroom. Therefore, in order to comply with current FAA requirements, it is desirable to provide a washroom oxygen system to provide an aircraft washroom oxygen source for such oxygen supply systems in order to deliver gaseous oxygen through the calibration flow port. .. The present invention meets these and other needs.</p>

<p num="0007"> Briefly, the invention includes an oxygen reservoir, a manifold connected to the oxygen reservoir, and an actuator configured to break the pressure seal of the oxygen reservoir to initiate the flow of oxygen. Provides an aircraft washroom oxygen source for use in aircraft washrooms.</p><p num="0008"> The present invention provides an aircraft washroom oxygen source used in an aircraft washroom to distribute a small amount of supplemental oxygen suitable for breathing by the user, the aircraft washroom oxygen source having a breathable purity. To start the flow of oxygen through the oxygen storage container configured to store gaseous oxygen at the oxygen pressure of 1 and the manifold connected to the opening of the oxygen storage container in a fluid communication state, and the opening of the oxygen storage container. Includes an actuator to be configured.</p><p num="0009"> In one currently preferred embodiment, the oxygen reservoir is configured to store gaseous oxygen at a first oxygen pressure with a purity suitable for respiration, and the oxygen reservoir is a first oxygen reservoir in the oxygen reservoir. It has an opening that is sealed by a pressure seal that is configured to keep oxygen pressure, and the pressure seal is configured to seal the oxygen storage vessel against the flow from the oxygen storage vessel until the pressure seal is broken. Will be done. In another currently preferred embodiment, the oxygen storage vessel is made of metal, such as a corrosion resistant stainless steel cylinder.</p><p num="0010"> The manifold is preferably connected to the pressure seal at the opening of the oxygen storage vessel in a fluid communication state and is configured to receive the flow of oxygen from the opening of the oxygen storage vessel when the pressure seal is broken. The manifold includes an oxygen flow path that includes an outlet that is connected to the pressure seal of the oxygen storage vessel in a fluid communication state. In another currently preferred embodiment, the manifold exit is through the exit to support a person's physiological life support requirements at a given aircraft altitude, time interval, and aircraft descent profile, or with sustained release characteristics. Includes one or more oxygen flow control orifices configured to control the oxygen flow rate and supply a predetermined amount of oxygen at a second oxygen pressure lower than the first oxygen pressure. In another currently preferred embodiment, the manifold also includes a pressure release port connected to the oxygen flow path in a fluid communication state.</p><p num="0011"> The actuator is configured to break the pressure seal, and the pressure seal is broken, broken, or broken by the actuator during actuation of the actuator to initiate the flow of oxygen through the opening of the oxygen reservoir. It is configured as follows. In a currently preferred embodiment, the pressure seal is formed from a fragile material that is configured to retain high pressure oxygen and can be broken or broken to open the oxygen reservoir and initiate the flow of oxygen from the oxygen reservoir. It has a vulnerable disk. In another currently preferred embodiment, the fragile disk is compressed between the manifold and the opening of the oxygen storage vessel, whereby the fragile disk provides a sealing surface and a break point for the oxygen storage vessel.</p><p num="0012"> In one currently preferred embodiment, one or more oxygen flow control orifices include a single flow control orifice. In another currently preferred embodiment, it is preferred that one or more oxygen flow control orifices include a plurality of flow control orifices, which are sequentially arranged in the flow path. In another currently preferred embodiment, one or more oxygen flow control orifices meet a person's physiological life support requirements, for example, at a given aircraft altitude, time interval, and aircraft descent profile, or with sustained release characteristics. Includes variable orifices such as decompressors configured to control the flow and pressure of oxygen through the outlet to provide a predetermined amount of oxygen to support.</p><p num="0013"> In another currently preferred embodiment, the manifold outlet is a swivel configured to be connected to one or more outlet hoses for one or more breathing masks configured for use in aircraft washrooms. Includes connector fittings. In the currently preferred embodiment, the swivel connector fitting is configured to rotate 360 degrees. In another currently preferred embodiment, the outlet of the manifold further comprises one or more oxygen distribution tubes that are detachably attached to the outlet. In another currently preferred embodiment, one or more oxygen distribution tubes include at least one detachably attachable connector, which connector can be detachably connected to the outlet for a portion of one or more oxygen distribution tubes. Can be detachably connected with, and can be detachably connected to the breathing mask. In another currently preferred embodiment, the aircraft washroom oxygen source comprises one or more breathing masks in the aircraft washroom connected to receive a flow of oxygen at a second oxygen pressure from the outlet of the manifold.</p><p num="0014"> In one currently preferred embodiment, the actuator comprises a metal wedge-shaped needle configured to mechanically break the fragile disk, and the opening of the oxygen reservoir is made of metal, in which case the actuator is a metal wedge. The shaped needle is configured to push into the metal opening of the oxygen reservoir, whereby the metal wedge-shaped needle and the opening of the oxygen reservoir guide the flow of oxygen from the oxygen reservoir through the outlet when the actuator operates. Form a metal-on-metal wedge seal configured to. In another currently preferred embodiment, the actuator comprises a spring loading mechanism configured to pierce the needle with a pressure seal, the spring loading mechanism making the needle a pressure seal to allow oxygen to flow through the flow path. Gives enough spring force to push through. In another currently preferred embodiment, the spring loading mechanism comprises a corrugated spring configured to provide an actuating force. In another currently preferred embodiment, the actuator comprises an explosive mechanism for initiating the flow of high pressure oxygen by puncturing the pressure seal, and the explosive device makes the needle into a fragile disk to allow oxygen to flow. Give enough force to push the needle through the fragile disc to allow oxygen to flow. In another currently preferred embodiment, the actuator comprises an electric solenoid configured to puncture the needle with a pressure seal, the electric solenoid having sufficient force to push the needle through a fragile disk to allow oxygen to flow. give. In another currently preferred embodiment, the actuator comprises a pneumatic starter configured to puncture the needle with a pressure seal, the pneumatic starter sufficient to push the needle through a fragile disk to allow oxygen to flow. Gives power.</p><p num="0015"> Other features and advantages of the present invention will become even more apparent from the following detailed description of preferred embodiments relating to the accompanying drawings showing the operation of the present invention as an example.</p>

0016<figref num="1">FIG. 5 is a perspective view of a prior art chemical oxygen source with an oxygen mask in an oxygen module container.</figref><figref num="2">It is a perspective view of the high pressure gas oxygen source with an oxygen mask in an oxygen module container which concerns on this invention.</figref><figref num="3">FIG. 2 is a perspective view of an oxygen storage vessel for a high pressure gaseous oxygen source of FIG. 2 with a rotatable swivel attachment for the outlet hose of the oxygen module according to the present invention.</figref><figref num="4">It is sectional drawing which shows the spring load actuator for breaking the pressure seal of the oxygen storage container of FIG. 3 in order to start the flow of oxygen which concerns on this invention.</figref><figref num="5A">It is sectional drawing which shows the explosive type actuator mechanism for breaking the pressure seal of the oxygen storage container of FIG. 3 in order to start the flow of oxygen which concerns on this invention.</figref><figref num="5B">It is sectional drawing which shows the electric solenoid actuator mechanism for breaking the pressure seal of the oxygen storage container of FIG. 3 in order to start the flow of oxygen which concerns on this invention.</figref><figref num="5C">It is sectional drawing which shows the pneumatic start actuator mechanism for breaking the pressure seal of the oxygen storage container of FIG. 3 in order to start the flow of oxygen which concerns on this invention.</figref><figref num="6">A pressure seal for holding high-pressure oxygen according to the present invention, which is broken or destroyed to start the flow of oxygen from the oxygen storage container by opening the oxygen storage container of FIG. 3 to start the flow of oxygen. FIG. 5 is a cross-sectional view showing a fragile disk made of a fragile material used as a pressure seal that can be broken.</figref><figref num="7">It is a perspective view of the vulnerable disk of FIG.</figref><figref num="8">FIG. 6 is a cross-sectional view showing a metal wedge-shaped needle forming a metal-on-metal wedge seal when the actuator is actuated to guide the flow of oxygen from the oxygen reservoir through the outlet and the opening of the oxygen reservoir according to the present invention. is there.</figref><figref num="9">FIG. 5 is a cross-sectional view showing a manifold including a single flow control orifice in an oxygen flow path connected to the opening of the oxygen storage container of FIG. 3 according to the present invention.</figref><figref num="10">FIG. 5 is a cross-sectional view showing an oxygen flow path in a manifold including a plurality of flow rate control orifices in the oxygen flow path connected to the opening of the oxygen storage container of FIG. 3 according to the present invention.</figref><figref num="11">FIG. 5 is a cross-sectional view showing an oxygen flow path in a manifold for one or more flow control orifices of oxygen flow activation in the oxygen flow path connected to the opening of the oxygen storage vessel of FIG. 3 according to the present invention.</figref><figref num="12">FIG. 5 is a perspective view showing an oxygen module with a breathing mask that can be released to fall from the oxygen module, wherein the oxygen distribution tube is detachably attached to the outlet of the oxygen source by a removable attachment according to the present invention.</figref><figref num="13">It is a perspective view which shows the manifold which contains the decompression variable orifice in the oxygen flow path connected to the opening of the oxygen storage container of FIG. 3 which concerns on this invention.</figref>

0017With reference to the drawings provided as an example, but not as a limitation, the present invention provides an aircraft washroom oxygen source 20 used in an aircraft washroom to distribute a small amount of supplemental oxygen suitable for breathing by the user. Aircraft washrooms generally include, or such oxygen, an oxygen module container 22 within the aircraft washroom, with one or more breathing masks 24 shown in FIG. 2, as further described below. Includes a personal service unit (PSU) that contains modules. Referring to FIGS. 2-4, the aircraft washroom oxygen source of the present invention has an oxygen storage vessel 26 configured to store first oxygen pressure gaseous oxygen having a purity suitable for respiration, and an oxygen storage vessel. Includes a manifold 28 connected to the opening 30 of the oxygen storage vessel in a fluid communication state, and an actuator 32 configured to initiate the flow of oxygen through the opening of the oxygen reservoir. The opening of the oxygen storage vessel is sealed by a pressure seal 34, which seals the oxygen in the oxygen storage vessel and keeps it at the first high pressure until the pressure seal is broken. The actuator preferably comprises a portion configured to penetrate the pressure seal, such as a hollow ported needle 35, which can be moved to break the pressure seal of the oxygen reservoir when the actuator is activated. Also, the pressure seal is correspondingly configured to be broken, broken or broken by the actuator mechanism during actuation of the actuator to initiate the flow of oxygen through the opening of the oxygen reservoir. One or more breathing masks can be provided in the aircraft washroom, the breathing masks are connected to receive the oxygen flow of the second oxygen pressure from the outlet of the manifold and, for example, in the aircraft at high altitudes. It can be released to fall from the oxygen module during decompression.

0018Further, the manifold is preferably connected to the pressure seal of the opening of the oxygen storage container in a fluid communication state, and is configured to receive the flow of oxygen from the opening of the oxygen storage container when the pressure seal is broken. The manifold includes an oxygen flow path 36 shown in FIG. 11 and an outlet 38 connected to the pressure seal of the oxygen storage vessel in a fluid communication state. The manifold may also include a pressure release port 40 that is connected to the oxygen flow path in a fluid communication state. Also, the outlet of the manifold preferably comprises one or more oxygen flow control orifices 42, the oxygen flow control orifices controlling the oxygen flow through the outlets to be lower than the first high oxygen pressure. Provides a predetermined amount of oxygen at the pressure of, thereby configured to support a person's physiological life-sustaining requirements at a given aircraft altitude, time interval, and aircraft descent profile, or with sustained release characteristics. Will be done. With reference to FIGS. 6 and 7, in the present preferred embodiment, the pressure seal is a fragile disk 44 formed from a fragile material, the fragile disk being configured to hold high pressure oxygen and providing an oxygen storage vessel. It can be broken or broken by the needle of the actuator to open and initiate the flow of oxygen from the oxygen reservoir. The fragile disk is compressed between the manifold and the opening of the oxygen storage vessel, whereby the fragile disk provides a sealing surface and break point for the oxygen storage vessel.

0019With reference to FIGS. 8-10, in the currently preferred embodiment, one or more oxygen flow control orifices include a single flow control orifice. In another currently preferred embodiment, the one or more oxygen flow control orifices preferably include a plurality of flow control orifices 48a, 48b sequentially arranged in the flow path. In another currently preferred embodiment shown in FIG. 13, one or more oxygen flow control orifices, for example, control the flow and pressure of oxygen through the outlet to supply a predetermined amount of oxygen, thereby providing a predetermined aircraft. Variable orifices 52, such as pressure reducing valves, that are configured to support a person's physiological life support requirements at altitude, time interval, and aircraft descent profile, or with sustained release characteristics, can be included. In another currently preferred embodiment shown in FIG. 3, the manifold outlet is one or more outlet hoses or oxygen distribution tubes for one or more breathing masks configured for use in aircraft washrooms 56. Includes a swivel connector fixture 54 configured to be connected to. The swivel connector fixture is preferably configured to rotate 360 degrees. In another currently preferred embodiment, the one or more oxygen distribution tubes are detachably attached to the outlet, eg, by one or more removable attachable connectors 58, the connector 58 being one or more oxygenated. Can be detachably connected directly to the outlet in a portion of the distribution tube, and can be detachably connected to the oxygen reservoir bag 59 of the breathing mask, or directly and detachably connected to the breathing mask Can be done. In this way, one or more breathing masks can be connected so that the oxygen flow of the second oxygen pressure is received from the outlet of the manifold, and one or more breathing masks, for example, when the aircraft is depressurized at a high altitude. Can be released to fall from the oxygen module.

0020Referring to FIG. 8, in the present preferred embodiment, the oxygen storage vessel is formed of a metal such as a corrosion resistant stainless steel cylinder, the actuator includes a metal wedge-shaped needle 60, and the metal wedge-shaped needle 60 is generally hollow. Together, it typically includes one or more ports configured to be connected to the flow channel of the manifold. The metal wedge-shaped needle is configured to mechanically break the fragile disk, and the opening of the oxygen reservoir is made of metal, in which case the actuator pushes the metal wedge-shaped needle into the metal opening of the oxygen reservoir. The metal wedge-shaped needle and the opening of the oxygen reservoir are configured to guide the flow of oxygen from the oxygen reservoir through the outlet when the actuator is activated. To form.

0021With reference to FIG. 4, in one currently preferred embodiment, the actuator can include a spring loading mechanism 62 configured to pierce the needle with a pressure seal, in which case the spring loading mechanism allows oxygen to pass through the flow path. Provide sufficient spring force to push the needle through the pressure seal to allow it to flow. In another currently preferred embodiment, the spring loading mechanism comprises a corrugated spring 64 configured to provide an actuating force.

0022As shown in FIG. 5A, in another currently preferred embodiment, the actuator may be an explosive mechanism 66, which is connected to receive an operation control signal 67 and allows oxygen to flow. High pressure oxygen flow that causes the needle to puncture the pressure seal by giving enough force to push the needle through the fragile disc to allow oxygen to flow through the fragile disc so that it can. Configured to start. As shown in FIG. 5B, in another currently preferred embodiment, the actuator is electrically connected to receive an electrical control signal and has an electrical connection 69 configured to puncture the needle with a pressure seal. It may be a solenoid 68, in which case the electric solenoid provides sufficient force to push the needle through the fragile disk to allow oxygen to flow. As shown in FIG. 5C, in another currently preferred embodiment, the actuator is connected to receive a pneumatic actuation signal 71 from a pneumatic source and is configured to puncture the needle with a pressure seal 70. In this case, the pneumatic actuator provides sufficient force to push the needle through the fragile disk to allow oxygen to flow.

0023As is clear from the above, although the specific embodiment of the present invention has been illustrated and described, various modifications can be made without departing from the idea and scope of the present invention.