14 results about "Inerting system" patented technology

A system (22) is disclosed having an inerting device (44) that receives an intake air stream and separates it into nitrogen-enriched air (NEA) and oxygen-enriched air (OEA). The inerting system also has an oxygen concentration sensor (46) and a controller (48) connected to the oxygen concentration sensor (46). The controller (48) adjusts operation of the inerting system (22) during use based at least in part on feedback received from the oxygen concentration sensor (46).

This invention relates to an air preparation system and an aircraft including such a system. The air preparation system includes an engine bleed air branch, a cabin exhaust branch, a compressor, a one-way valve, and a main heat exchanger. The engine bleed air branch draws air from the bleed air manifold to supply the compressor or the one-way valve, and is equipped with an air preparation system pressure regulating valve. The cabin exhaust branch draws air from the cabin exhaust area to supply the compressor or the one-way valve, and is equipped with a cabin exhaust supply valve. The one-way valve is arranged in parallel with the compressor. The main heat exchanger is located downstream of the compressor and the one-way valve and is in fluid communication with them. The main heat exchanger is used to regulate the temperature of the air from the compressor or the one-way valve before supplying it to the inerting system. According to the above technical solution, this invention can achieve the following beneficial technical effects: reducing engine bleed air consumption, thereby reducing aircraft fuel consumption.

A vortex tube assembly for an aircraft enclosure inerting system has a plenum chamber and a swirl generator which has an inlet passage that allows air in the plenum chamber to enter a vortex chamber whereupon the air can be centrifugally separated into nitrogen enriched air (NEA) and oxygen enriched air (OEA). A throttle pin is positioned within the inlet passage, an outer surface of the throttle pin and an inner surface of the inlet passage co-operatively defining a flow path for air to enter the vortex chamber from the plenum chamber. The throttle pin is movable between a restrictive position and a permissive position, with the flow path being more constricted when the throttle pin is in the restrictive position than when the throttle pin is in the permissive position. The throttle pin is biased to the permissive position and movable to the restrictive position against this bias.

An inerting system 22 has an inerting apparatus 44 which receives an inlet air flow and separates it into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system also has an oxy

A vortex tube assembly 42 for an aircraft enclosure inerting system (22, fig. 1) has a plenum chamber 34 and a swirl generator 36 which has an inlet passage 38 that allows air in the plenum chamber to

An inerting system is provided with a vortex tube for separating air into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system has a warming device which warms NEA as it flows between an NEA outlet of the vortex tube and an NEA port of the inerting system. A method is also provided of supplying conditioned NEA to an enclosure, in which air is centrifugally separated into NEA and OEA in a vortex tube and the NEA is warmed so as to produce the conditioned NEA.

A method of clearing a swirl generator of a vortex tube for an aircraft enclosure inerting system. The vortex tube has an inlet chamber and a vortex chamber which can receive air from the inlet chamber via flow paths in the swirl generator. The method comprises operating the vortex tube in a foreign matter clearance mode in which a reversed flow of gas is passed from the vortex chamber into the inlet chamber through the flow paths and dislodges accumulated foreign matter therefrom. Dislodged foreign matter is then exhausted from the vortex tube then the vortex tube is operated in a normal mode of operation.

The present application belongs to the field of coal mining, and particularly relates to a mine fire area intelligent linkage sealing and unsealing device, which comprises a door frame fixed on a tunnel wall, a porous diffuser inlaid on the fire-facing side of the door frame, an annular sealing groove arranged on the inner side of the door frame, and a micro nozzle in series embedded in the annular sealing groove; a protective door body hinged to the door frame, an internal integrated pressure relief pipeline and an inert gas pipeline, a side frame of the protective door body provided with a groove, an expansion type rubber sealing sleeve in the groove communicated with the inert gas pipeline; an arc-shaped pressing assembly slidingly arranged on the fire-facing side of the protective door body, a dynamic inertization system for controlling directional distribution of inert gas, a sealing structure comprising a two-component adhesive injection system, the two-component adhesive injection system communicated with the micro nozzle, and the two-component adhesive injection system connected in parallel with the dynamic inertization system. The present application can quickly seal, resist explosion and relieve pressure, and improve the reliability and safety of mine fire emergency isolation.

A control system for operating and / or monitoring an inerting system for a wet-pipe fire sprinkler system includes a logic determining device; a user interface to display a status of the sprinkler system; at least one sensor to monitor operating parameters of the sprinkler system and transmit a signal to the logic determining device with sensor data relating to the at least operating parameter; a memory module to record the sensor data; a communications module to transmit the sensor data to a receiving device; and a power module to deliver power for the control system. Associated methods of automating and / or monitoring of an inerting system for a wet-pipe fire sprinkler system are also disclosed.

The invention provides an inerting system 22 with a vortex tube 24 for separating air into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system 22 has a warming device 58 whi

A method of clearing a vortex tube 24 swirl generator 36 for an aircraft inerting system. The method comprises operating in normal mode by supplying air flow 44 to a vortex chamber 32 through flow pat

An inerting system has an inerting apparatus which receives an inlet air flow and separates it into nitrogen enriched air and oxygen enriched air. The inerting system also has an oxygen concentration sensor and a controller connected to the oxygen concentration sensor. The controller adjusts operation of the inerting system during use, based at least in part on feedback received from the oxygen concentration sensor.

The application provides a liquid leakage storage device, belonging to the technical field of airborne fuel tank inerting, which comprises a cavity 1, a locking screw and nut assembly 3, a liquid discharge nozzle 4 and a cap assembly 5. The cavity 1 is a cylindrical structure, the upper end surface is provided with a flange plate interface for connecting with a reserved mounting surface of a pipeline shell, and a thin tube is arranged on the upper end surface and extends into the cavity. The lower end surface is provided with a flange plate interface for connecting with the liquid discharge nozzle 4. The locking screw and nut assembly 3 fastens the liquid discharge nozzle 4 and the cavity 1. The cap assembly 5 is threadedly connected with the liquid discharge nozzle 4. The device can prevent fuel slow seepage through a one-way valve and further pollute the airborne inerting system, and can realize that the stored liquid leakage cannot flow back under different flight postures, and can be widely applied to the structure design with liquid leakage storage requirements.

An inerting system 22, for instance an aircraft enclosure inerting system, is configured to separate an inlet air flow into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting syst