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Nitrogen inerting system for explosion prevention in aircraft fuel tank and oxygenating system for improving combustion efficiency of aerospace rockets/ aircraft engines
Nitrogen inerting system for explosion prevention in aircraft fuel tank and oxygenating system for improving combustion efficiency of aerospace rockets/ aircraft engines
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机译：用于飞机油箱防爆的氮气惰化系统和用于提高航空火箭/飞机发动机燃烧效率的充氧系统
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摘要
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.
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