초록 ▼

Compressed Air from an aircraft/rocket engine's compressed air line to its air-conditioning system, or an Auxiliary Air Compressor out-put is used, for energizing a high-speed gas turbine. The very high-speed convoluting air discharge into a vortex cone causes a first separation of the Air gas compo

Compressed Air from an aircraft/rocket engine's compressed air line to its air-conditioning system, or an Auxiliary Air Compressor out-put is used, for energizing a high-speed gas turbine. The very high-speed convoluting air discharge into a vortex cone causes a first separation of the Air gas components, by stratifying into heavier (Argon), medium (Oxygen) and lighter (Nitrogen) components, where in the heavier and lighter components are non-combustible, inert gases and the medium is a combustible gas. The lighter non-combustible component (Nitrogen) exits from the turbine in one direction for storage in the Inert gas tank. The heavier (Argon) and medium (Oxygen) components together move in the opposite direction for having a second stratifying separation downstream in the vortex tube, to separate non-combustible, heavier (Argon) gas from combustible medium (Oxygen) gas components. The combustible, medium (Oxygen) component exits the vortex tube open end, to flow into an Oxygenating storage tank; whereas, the heavier, non-combustible(Argon) gas is piped into the Inert gas storage tank. Both gas storage tank in-flow lines are fitted with non-return valves. The out flow lines from the Inert tank to either Fuel Tank “Ullage” or “OBGIS” areas are fitted with electronic control valves, operated by signals received from fiber-optic Temperature/Pressure/Oxygen concentration Sensors in the Fuel tank “Ullage” or “OBGIS: areas. Likewise, the outflow lines from the Oxygenating tank are fitted with electronc control valves activated by engine “takeoff” or Passenger cabin low oxygen signals, respectively.

대표청구항 ▼

What is claimed is: 1. A method of separating gas components of the Compressed air diverted from the Aircraft engine's compressed air line to the Air Conditioning System, for subsequent re-cycling of the inert, non-combustible nitrogen and argon gas components into its hydrocarbon fuel tank's

What is claimed is: 1. A method of separating gas components of the Compressed air diverted from the Aircraft engine's compressed air line to the Air Conditioning System, for subsequent re-cycling of the inert, non-combustible nitrogen and argon gas components into its hydrocarbon fuel tank's “ullage”, thereby preventing Tank explosions generated by such installations; and diverting the remaining, separated combustible oxygen gas component into the airplane/rocket engine's combustion air for increasing fuel economy of the engine, said method comprising: effecting a first separation of the Air gas mixture into heavier, medium and lighter components, wherein the heavier and lighter components are primarily noncombustible, inert gases and the medium is combustible; effecting a second separation in which the heavier and medium components are separated into a first portion comprising substantially of medium, combustible oxygen gas for egress to the oxygen storage tank; and a second portion comprised substantially of the heavier, non combustible, inert argon gas for egress to the inert nitrogen/argon gas storage tank; providing means for periodical removal of the sedimentation collecting in chamber; and mixing said second portion of said second separation stage (argon) gas with the lighter component (nitrogen) gas effected in the first separation stage, to effect a non-combustible mixture for inerting the “ullage” space in the airplane's fuel tank. 2. An apparatus for separating gas components of the air diverted from the Aircraft engine's compressed air line to the Air Conditioning System, for subsequent re-cycling of the inert, non-combustible nitrogen and argon gas components into its hydrocarbon fuel tank's “ullage” and other “OBGIS”areas, thereby preventing Tank explosions and suppression of cargo fires respectively, and diverting the remaining, separated combustible oxygen gas component into the airplane/rocket engine's combustion air for increasing the fuel economy of the engine, said method comprising: an electrically driven, variable flow, adjustable discharge pressure Air Compressor(s) of either centrifugal or rotary screw type or similar, with each device or a plurality of devices, as may be required to fully energize these devices; a first air gas separating device and means for bringing suitably, compressed air thereto from the said compressor, whereby the air is separated into its lighter and heavier primarily, inert, non-combustible components and substantially separated from its medium and primarily combustible components; a second separating device and means for conducting said heavier and medium components thereto from the said first separating device; said second separating device communicating with the atmosphere and having means to substantially separate the heavier non-combustible and medium combustible gases into a first portion comprising substantially of the medium, combustible oxygen gas for egress to the atmosphere; and a second portion comprised substantially of the heavier, incombustible argon gas for separate egress to the atmosphere; means to feed the said lighter incombustible gases separated from the said first gas separating device and the heavier incombustible gases separated in the second portion of the second separating device, to an Inert gas storage tank, until required for inerting the “ullage” in the airplane's fuel tank or the “OBGIS” areas; while said combustible oxygen gases of the first portion of the second separation device flow out from an open end of the second separation device, for storage into an Oxygenating Tank, until required for combustion efficiency improvements during “take-off” of the aircraft or rocket. 3. The apparatus as set forth in claim 2, where in said first gas separating device comprises: an upstream stator, followed by a compressed air driven turbine and a conical vortex tube open at both ends and connected thereto at its larger end via a down stream stator, so as to receive the rotating gas discharge there from for separation therein into an inner gas core of said primarily incombustible lighter gases moving axially towards said turbine and an outer layer of said heavier gases moving axially in the opposite direction for; separation in said second separating device into said primarily combustible and non-combustible gas and said means for conducting said lighter gases of said inner core from said conical vortex tube to an Inert gas storage tank, and means to provide a hollow shaft for support of said turbine communicating with said vortex tube at the inner core region thereof. 4. An apparatus as set forth in claim 2, wherein said first gas separating device comprises: an upstream stator, followed by a compressed air driven turbine and a conical vortex tube, open at both ends and connected thereto at its larger end via a down stream stator, so as to receive the rotating gas discharge there-from for separation there-in into an inner gas core of said primarily incombustible lighter gases moving axially towards said turbine and an outer layer of said heavier gases moving axially in the opposite direction for separation in said second separating device into said primarily combustible and non-combustible gases. 5. An apparatus as set forth in claim 2, said second separating device comprising: a plurality of elongated, horizontal slots machined on the smaller end of the said vortex tube, so as to afford a streamlined egress of the outer layer of heavier, incombustible gases, into a gas collector chamber surrounding the said slotted area, whereby the outer layer of heavier gases passing through said vortex tube exit there from through said slotted area into said gas collector chamber; means provided for return of the said heavier, incombustible gases to the Inert gas storage tank, while the medium weight, inner core of primarily combustible gas of said heavier outer layer, flow out from an open end of the second separation device, namely the vortex tube small end, for storage into an Oxygenating Tank. 6. The apparatus as set forth in claim 2, said second separating device comprising: a plurality of elongated, horizontal machined slots on the smaller end of said vortex tube; means provided for a gas collector chamber comprising a cylindrical shell, centrally mounted over said slots; said gas collector chamber provided with a converging gas exit tube mounted peripherally and tangentially to the cylindrical shell of the gas collector chamber and centrally located over the said slots, whereby affording improved streamlined flow of the said outer convoluting layer of heavier gases, in to an Inert gas storage tank. 7. An apparatus as set forth in claim 2, said second separating device comprising: a plurality of elongated, horizontal slots machined at an angle of 30 degrees to the vertical axis, on the smaller end of said vortex tube; means provided for a gas collector chamber comprising a cylindrical shell centrally mounted over said slots; and said gas collector chamber provided with a converging gas exit tube mounted peripherally and tangentially to the cylindrical shell of the gas collector chamber and located centrally over the said slots, in order to tangentially tilt the out flow of the said convoluting heavier gases, towards the gas collector chamber's exit tube; whereby further streamlining and enhancing the said heavier gas flow in to the said Inert gas storage tank. 8. The apparatus as set forth in claim 2, said separating device comprising: a plurality of elongated, horizontal slots machined at an angle of 30 degrees to the vertical axis, on the smaller end of the said vortex tube; means provided for a gas collector chamber comprising a cylindrical shell, centrally mounted over said slots; said gas collector chamber provided with a converging gas exit tube mounted peripherally and tangentially to the cylindrical shell of the gas collector chamber and located centrally over said slots; means provided for the interior surfaces of the gas collector chamber and exit tube to be completely coated with a friction reducing, high temperature, abrasion resistant thermo-setting and organic industrial coating; thereby further improving the streamlined and smooth, out-flow of the said outer layer of heavier gases, to the Inert gas storage tank. 9. The apparatus as set forth in claim 2, including an aircraft jet/rocket engine where in the compressed air supply to its Air Conditioned system is at 90˜150 pounds per square inch or higher pressure, in combination there with and having an engine or other water cooling supply and comprising: a bearing support means for said turbine; means for conducting cooling fluid from said radiator to said bearing support means; means for the return of cooling fluid to said radiator, after the cooling of said bearing support means; whereby reducing the bearing working temperature and achieving higher System turbine speeds, resulting in the improved separation and storage of the said lighter, medium and heavier constituent gases of air, for feeding the Inert gas and Oxygenating storage tanks of this Invention. 10. An apparatus for separation of the gas components of the air diverted from the Aircraft engine's air-intake line, for subsequent re-cycling of the inert, non-combustible nitrogen and argon gas components into its hydrocarbon fuel tank's “ullage”, and “OBGIS” areas, thereby preventing Tank explosions and suppression of cargo fires, and diverting the combustible oxygen gas component into the airplane/rocket engine's combustion air, for increasing the fuel economy of the engine and passenger breathing comfort, said apparatus comprising: a rotational device and means for feeding a portion of an aircraft engine's combustion in-take air, at pre-adjustable pressure thereto, to be rotated thereby to effect a rotational directional speed of air passing there-through, significantly greater than the speed of the intake air fed to the said device; a vortex tube connected to said rotational device for receiving rotating air from the engine air intake, there-from to be stratified therein into a heavier outer layer of mixed non-combustible and combustible gases and a lighter inner core of primarily non-combustible gases; means for feeding said inner core gases to said installation's Inert gas storage tank, for subsequent flow into the fuel tank “ullage” for preventing its explosions and “OBGIS” supplies; means for separating said heavier outer layer into substantially heavier non-combustible gases and medium weight combustible gases, which egress through the open end of vortex cone, into said intallation's Oxygenating storage tank; means comprising a horizontal, elongated slotted area of vortex tube, through which area said heavier non-combustible gases, leave said vortex tube for feed into the said installation's Inert gas storage tank; means provided for removal of the heavier sedimentation particles collecting in said gas collector chamber surrounding the slotted area of vortex tube. 11. The apparatus as set forth in claim 10, wherein said vortex tube is tapered to increase the rotational speed of the gases therein; the larger end thereof being connected to said rotational device and the smaller end being open for exhausting said combustible gases; said horizontal, elongated slotted area being located adjacent to said smaller open end of vortex tube, benefits from the significantly increased air-constituent gases' convoluting speed as they approach the second separation stage at the said slotted area in the smaller end of the vortex tube; there by, improving the separation amount of the heavier non-combustible gases and sedimentation particulates from the lighter combustible gases. 12. The apparatus as set forth in claim 10, including an electrically driven, variable flow, adjustable discharge pressure Air Compressor(s) of either centrifugal or rotary screw type or similar, with each device or a plurality of devices, as may be required to fully energize these devices, in combination with said apparatus and said rotational device being a turbine connected thereto for tangential compressed air feed thereto and axial flow there from to said vortex tube and said rotational device connected thereto, to be driven by the aircraft engine's combustion air-intake thereof. 13. The apparatus as set forth in claim 10, including means provided for: an automated valved communication of the inert gas flow lines for the lighter and heavier inert gases into an inert gas storage tank; an automated valved communication of the combustible gas flowline into oxygen storage tank. 14. The apparatus as set forth in claim 10, including means provided for: an automated valved communication of the inert gas flow line from the inert gas storage tank to the “ullage” volume in the fuel tank, for its complete inertness; an automated controller responsive to the detection of a partial pressure of oxygen and the temperature within said “ullage” volume that is higher than a pre-determined, explosive level to cause inert gas to flow into the “ullage” from storage tank, to establish the oxygen partial pressure in the “ullage” volume to a safe and lower level. 15. The apparatus as set forth in claim 10, including means provided for: an automated controller responsive to detection of a partial pressure of oxygen with in the airplane/aerospace rocket engine' combustion air supply or the passenger cabin, that is lower than a predetermined level to cause oxygen gas to flow in to either flow line, to re-establish the correct partial pressure for improved engine fuel economy, and/or the passenger's breathing comfort.