163 results about "Inerting system" patented technology

A self-regulating system for reducing concentration of hydrocarbon vapor in a container may be performed by introducing air into the container and extracting a mixture of air and vapor from the container. The extracted mixture may be compressed with a compressor to produce a flow of compressed mixture of air and vapor. The compressed mixture may be passed through an oxidation reactor that may be either catalytic or thermal to produce a flow air and CO2. A turbine may be driven with the flow of air and CO2. The compressor may be driven with the turbine. Extraction from the container may continue until vapor concentration is low enough so that flow of CO2 and air from the reactor is insufficient to drive the turbine.

A fuel system for an aircraft is disclosed. The fuel system comprises a fuel tank and a fuel reformer for receiving fuel from the fuel tank. The system includes a hydrogen fuel cell array for receiving hydrogen from the fuel reformer. The system further includes mechanism for providing an inerting gas from the fuel system to the fuel tank.

The invention provides an airplane environment control and fuel tank inerting coupled system based on a membrane separation method. The system is characterized in that gas dehumidification in an airplane environment control system and oxygen and nitrogen separation in a fuel tank inerting system are achieved respectively by the oxygen / nitrogen permselectivity of membranes; one part of dry gas passing a membrane dehumidification heat exchanger enters a membrane air separator, and the other part of the dry gas is subjected to turbine expansion cooling and then fed into a cockpit to perform refrigerating; nitrogen-enriched gas generated by the membrane air separator is fed into a fuel tank to perform inerting, and oxygen-enriched gas is mixed with gas supplied by the environment control system to increase the oxygen content of gas supplied for the cockpit. Compared with the independent environment control system and fuel tank inerting system of an existing airplane, the coupled system hasthe advantages that the coupled system is simple in structure, lightweight, capable of sufficiently utilizing an engine to guide gas and increasing the oxygen content of gas supplied for the cockpitand capable of reducing system compensatory loss, and the thermodynamic property of the coupled system is also better than that of the two independent systems.

The invention pertains to an inerting system for an aircraft featuring at least one air separation module with at least one air inlet, a first air outlet and a second air outlet. The air separation module is designed for splitting an input air flow into a first air flow and a second air flow, wherein the first air flow is enriched with oxygen in comparison with the input air flow and discharged at the first air outlet and the second air flow is enriched with nitrogen in comparison with the input air flow and discharged at the second air outlet. In comparison with known inerting systems, the inerting system according to the invention is characterized in that the air inlet can be connected to an air extraction point in an air processing system and the inerting system is designed for routing the first air flow into a cabin to be air-conditioned.

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.