78 results about "Inerting system" patented technology

The present invention relates to a system, method, and use for the unloading of solid material particles used in a physical, chemical, and / or biological process in a tank and for the inertization of the tank. The receiving tank and the pump are fluidically connected. The inert gas supply device is fluidically connected to the tank and to at least one injector. The at least one injector is arranged along the transport line that connects the tank to the receiving tank and is configured to inject inert gas into the transport line. The pump is configured to generate negative pressure in the receiving tank and in the tank, and the inert gas supply device is configured to insert inert gas into the tank and supply inert gas to at least one injector, to allow the displacement of solid material particles from the tank to the receiving tank.

The aircraft composite fuel tank inerting system comprises a gas source distribution pipeline; the central wing inerting branch is connected with the central wing oil tank; the central wing inerting branch is provided with a first inert gas generator and a multi-flow switching valve, and the multi-flow switching valve is located on the downstream side of the first inert gas generator and can be switched into a first flow mode and a second flow mode. The flow of inert gas provided in the first flow mode is smaller than that in the second flow mode, the outer wing inerting branch is provided with a second inert gas generator and a first flow limiting piece located on the downstream side of the second inert gas generator, and a single flow mode is achieved through the first flow limiting piece. Inert gas is injected into the center wing fuel tank such that the initial value of the oxygen concentration in the center wing fuel tank in the descent phase is equal to or less than a first upper limit threshold value, and inert gas is injected into the outer wing fuel tank such that the oxygen concentration in the outer wing fuel tank in the cruise phase is equal to or less than a second upper limit threshold value higher than the first upper limit threshold value.

The invention discloses an aircraft green inerting system with a water removal function. The aircraft green inerting system comprises an oil tank, a catalytic reactor, a water removal device and a control system. The system extracts oxygen and fuel oil steam in an oil tank through a first fan, the oxygen and the fuel oil steam are mixed with ram air, then the mixture is heated through an electric heater and burnt in a catalytic reactor to generate high-temperature inert gas, then the high-temperature inert gas is subjected to water removal through a first water separator, cooling through a heat exchanger, pressurization through a compressor and secondary water removal through a second water separator in sequence, and pressure reduction and temperature reduction are conducted through a cooling turbine; finally, low-temperature dry inert gas is formed and is reinjected into an oil tank through a fuel oil ejector, and the dual functions of inerting and water removal are achieved. The system monitors in real time through an oxygen concentration sensor, a temperature sensor and a flow sensor, dynamically adjusts the electric heating power and the rotating speed of a valve and a fan, and ensures safe and efficient operation. Catalytic combustion and high-pressure water removal technologies are combined, the oxygen concentration of the fuel tank and the water content of fuel are effectively reduced, and the device is energy-saving, environment-friendly, efficient in inerting and suitable for safety protection of various aircraft fuel systems.

The invention belongs to the technical field of aircraft fuel tank inerting, and particularly relates to a method for calculating the shedding rate of a catalyst coating of an ozone converter in single flight. Comprising the following steps: S1, acquiring the mass M of a catalyst coating of the ozone converter; s2, acquiring flight profile data, wherein the flight profile data comprises a relationship H (t) between the flight height H and time t of the aircraft, time h required by one flight cycle of the aircraft, and time t1 and t2 for starting working and closing of an inerting system; s3, the relation m (H) between the mass m of dust contained in unit volume of entrained air in the entrained air of the inerting system and the flight height H is obtained; s4, the air entraining flow Q of the inerting system is obtained; s5, obtaining a guarantee value F and a dust holding capacity M1 of the minimum replacement interval of the filter; and S6, calculating the single flight shedding rate mu of the catalyst coating of the ozone converter.

The invention discloses a graded inerting device and method based on dynamic risk discriminating.The device comprises a continuous inerting system, a dust removal system and an efficient inerting system, the dust removal system comprises a dust removal main pipeline and a dust remover which are connected, the continuous inerting system comprises an inerting dust bin and feeding equipment, and the feeding equipment is connected with the dust removal main pipeline; the efficient inerting system comprises an efficient inerting powder tank; and the efficient inerting powder tank is connected with a dust remover. According to the method, the continuous inerting system and the efficient inerting system are used in a combined mode, the explosion risk of the main dust removal pipeline can be reduced through the continuous inerting system under the condition that the dust remover does not break down, and meanwhile the combustible dust explosion risk caused by the fault of the dust remover can be effectively controlled; the efficient inerting system is only triggered under the abnormal condition that the dust concentration of the dust remover is abnormally increased or explosion is generated, so that the energy consumption of fixed threshold inerting and the consumption of an inerting medium are effectively reduced, and more efficient inerting is realized.

The present invention relates to a positive and negative pressure injection inerting system and method for rapid fire prevention and extinguishing in goafs, belonging to the field of fire prevention and extinguishing in goafs; it solves the problem of poor fire extinguishing effect of existing fire extinguishing methods in goafs; the technical solution is: it includes a first gas injection main pipe and a plurality of air collecting devices, the air collecting devices are placed in the first gas injection main pipe, the air collecting devices and the first gas injection main pipe are gap-matched, the first gas injection main pipe is connected to the gas injection equipment, an air flow channel is provided through the air collecting device, the air collecting air inlet of the air flow channel is interconnected with the first gas injection main pipe, the air collecting air outlet of the air flow channel is connected to a pumping branch pipe, the low-pressure part of the air flow channel is connected to one end of the main drilling pipe through a gas return pipe, the gas return pipe and the air flow channel are interconnected, the main drilling pipe is arranged in the goaf, and the other end of the main drilling pipe is connected to the second gas injection main pipe, so as to achieve the effect of rapid fire extinguishing coordinated by pumping and injection; the present invention is applied to fire prevention and extinguishing in goafs.

The invention belongs to the electromechanical technology of helicopters, and relates to a fuel tank inerting system based on engine tail gas and a control method of the fuel tank inerting system. One end of a pipeline blows air from an engine exhaust nozzle, and the other end of the pipeline is connected with upper air of a fuel tank; a fan, a pressure safety valve, a temperature adjusting unit, a three-way catalyst, an oxygen monitoring unit, a cooling unit and a temperature monitoring unit are sequentially arranged in the pipeline; a fuel tank oxygen sensor is arranged at the upper part of the fuel tank; the fuel tank is further connected with the outside atmosphere through a ventilation pipeline.

One aspect of the invention relates to a method (100) for selecting activation logic of an inerting system (3122) of at least one fuel tank of an aircraft (31) for at least one flight mission of the aircraft (31), the method (100) comprising the steps of:-sending (101) data relating to a preparation flight mission to a computer (32); -estimating (102), by the calculator (32), N flammability risks of the fuel comprised in the fuel tank, N being a non-zero natural number, each flammability risk being estimated as a function of:-a single activation logic of an inerting system selected from the N activation logics of the inerting system (3122); and-data relating to the preparation of a flight mission; -selecting (103) an activation logic from among the N activation logics as a function of the estimated N flammability risks and as a function of conditions relating to the inerting system (3122).

The invention relates to a fuel tank inerting system, a fuel tank inerting method and an aircraft. On one hand, the low-temperature rare gas generated by gasification of the liquid rare gas is directly used for replacing oxygen and fuel steam in the fuel tank and reducing the temperature in the fuel tank, and on the other hand, the low-temperature rare gas is used for cooling the fuel steam discharged out of the fuel tank; and then the cooled fuel steam or the fuel liquid drops formed by condensation are returned to the fuel tank to further reduce the temperature in the fuel tank and the concentration of the fuel steam, so that double inerting of the fuel tank is realized. The fuel tank inerting system and method according to the present disclosure may be applicable to various types of aircraft.

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).

The application discloses an ozone decomposition catalyst with catalytic performance and water resistance, and a preparation method and application thereof, and belongs to the field of gas purification and treatment in the field of energy and environment. The ozone decomposition catalyst comprises a carrier, an active component, a catalytic component and a reinforcing component; the active component and the catalytic component are loaded on the carrier to form a core layer; and the reinforcing component is wrapped around the periphery of the core layer to form a reinforcing layer. The ozone decomposition catalyst adopts a configuration of "reinforcing layer @ catalytic component" or "reinforcing layer @ catalytic component @ metal honeycomb substrate", so as to ensure the ozone catalytic decomposition performance and water resistance of the catalyst under high flux and high humidity conditions. The metal wall ozone decomposition catalyst with the configuration of "reinforcing layer @ catalytic component @ metal honeycomb substrate" is especially suitable for the ozone decomposition catalyst required in an ozone converter of an aircraft cabin control system and a fuel tank inerting system.

Disclosed are a method and a system for reducing thermal runaway in a battery pack (1), the method comprising the steps of: detecting a temperature inside the battery pack (1); when the detected temperature is higher than a predetermined temperature, a gas containing nitrogen gas and oxygen gas is injected into the battery pack (1), the volume of the oxygen gas being less than 10%, and the oxygen gas is removed from the inside of the battery pack (1). The system comprises a temperature sensor (2); the inerting system (4) is used for injecting gas containing nitrogen and oxygen into the battery pack (1) under the condition that the temperature detected by the temperature sensor (2) is higher than a preset temperature, and the volume of the oxygen is smaller than 10%; and an outlet duct (7) through which oxygen is removed from the battery pack (1) when the temperature detected by the temperature sensor (2) is higher than a predetermined temperature.

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 compact lightweight air filtration system is disclosed. The air filtration system includes a hydrophobic particulate / coalescing filter and a cleanable ozone converter housed in a housing with an inlet and an outlet. Air flowing from the inlet to the outlet passes through the particulate / coalescing filter element and then the cleanable ozone converter to remove particulates, aerosols, liquids, and ozone. The air filtration system may comprise a fuel tank inerting system (FTIS) filter assembly. The FTIS filter assembly may include a binderless media (no binder) suitable for use in high temperatures. The FTIS filter assembly includes a catalytic converter configured to adsorb one or more VOCs.

The invention provides an underwater lithium ion power battery toxic and harmful gas treatment system and method.The system comprises an inert gas filling system, an oxygen elimination and disinfection system and an inerting system control system, the inert gas filling system comprises a nitrogen cylinder and an inert gas filling pipeline, and the inert gas filling pipeline is communicated with the nitrogen cylinder and a storage battery chamber; nitrogen is conveyed to the storage battery chamber; the oxygen-eliminating and disinfecting system comprises an oxygen-eliminating and disinfecting pipeline, and two ends of the oxygen-eliminating and disinfecting pipeline are respectively communicated with the storage battery chamber to form closed circulation; the inerting system control system controls on-off and flow of an inert gas filling pipeline and controls starting and stopping of an oxygen elimination and disinfection program, the oxygen concentration can be controlled, harmful and toxic gas can be removed in time, and explosion accidents caused by gas leakage due to thermal runaway in a storage battery chamber are avoided.

The invention relates to an inerting system, an aircraft and a method for inerting a fuel cell system by means of an inerting system. More specifically, the present invention relates to an improved inerting system that injects inert gas around a fuel cell in a distributed manner to ensure correct dissipation of flammable agent that may occur around the fuel cell.

The utility model discloses a surge tank structure of a marine methanol supply pipeline, which comprises a methanol supply pipeline and a nitrogen inerting system, the methanol supply pipeline is provided with a surge tank, and the top of the surge tank is provided with a gas inlet connected with the nitrogen inerting system through an electronic ball valve. A pressure sensor in signal connection with the electronic ball valve is installed on a pipeline between the electronic ball valve and the gas inlet, a dynamic pressure adjusting mechanism is constructed, when the pressure drops to a preset value, nitrogen is supplemented into the surge tank in time through a nitrogen inerting system, and unsmooth methanol fuel supply caused by sudden pressure drop is avoided; a safety valve used for exhausting is further installed at the top of the surge tank, when the pressure in the surge tank is too high, the safety valve is automatically opened to exhaust redundant gas, the situation that a methanol supply pipeline is impacted due to the too high pressure is avoided, the methanol leakage risk is reduced, meanwhile, the service life of the pipeline and related equipment is prolonged, and the operation and maintenance cost of the ship is reduced.

This invention discloses a five-level safety and explosion suppression device for aviation hydrogen fuel. The device comprises a hydrogen storage tank, a hydraulic buffer structure, a distributed fiber-optic hydrogen sensor, a nitrogen inerting system, a pressure relief valve, and a water mist explosion suppression system. This device enables rapid response to hydrogen leaks and explosion suppression. The compact structure ensures rapid leak response and full-process explosion risk suppression, making it suitable for hydrogen-powered aircraft and hydrogen storage facilities, significantly improving the safety of hydrogen energy applications.

An aircraft fuel system includes a first fuel storage tank arranged to store a first fuel, a second fuel storage tank arranged to store a reduced oxygen fuel, and a fuel tank inerting system arranged to provide a reduced oxygen gas through a fuel contained within the second fuel storage tank to generate the reduced oxygen fuel within the second fuel storage tank. The fuel tank inerting system may include a fuel tank sparging system to inject the reduced oxygen gas directly into the fuel contained within the second fuel storage tank to generate the reduced oxygen fuel.

The present application relates to the technical field of aviation system, more particularly to an aviation engine integrated with an inerting system and an aviation aircraft. It solves the problem that the traditional on-board nitrogen generation system technology needs to use the engine bleed air, thereby affecting the engine performance. The aviation engine comprises a compressor, a rotating shaft, a gas turbine, a power turbine, a generator, a compressor air splitter, an anode tail gas splitter, a combustion chamber, an anode tail gas blower, a reforming reactor, a fuel inerting system, a fuel pump, an electric propulsion system and a cathode tail gas splitter, wherein the fuel inerting system comprises a solid oxide fuel cell, a reformer heat exchange channel, a first heat exchanger, a second heat exchanger and an oil tank. It reduces the influence of the inerting system on the weight of the aircraft, avoids the additional demand of the nitrogen generation system on the engine bleed air, and also meets the demand for electric energy under the trend of aircraft electrification, thereby ensuring the normal working performance of the engine.

The invention belongs to the technical field of civil aircraft inerting system air filters, and discloses a two-stage filtering air filter with an automatic drain valve, which comprises a shell with a cylindrical structure, a gas inlet and a gas outlet which are arranged on two sides of the top of the shell, the gas inlet is communicated with an outer ring channel in the shell, and the gas outlet is communicated with a central circle in the shell. The outer ring channel in the shell is separated from the central circle through a cylindrical surface; two layers of cylindrical coaxially-sleeved filtering structures are arranged on the lower portion, in the shell, of the outer ring way and the center circle, and a drainage valve assembly is arranged below the filtering structures. The double filter elements are connected in series, the installation space is saved, the product weight is reduced, the spring is arranged to press the hydrophobic filter element and eject the end cover assembly, and the end cover assembly is convenient to disassemble.

The invention provides a ship fuel filling device and a ship fuel filling method, the filling device comprises a vehicle body, a filling system and an inerting system, and a sealing cavity is formed in the vehicle body. And the filling system is arranged in the sealing cavity. The filling system comprises a liquid-state filling pipeline, a gas-state circulating pipeline and a release valve. The first end of the liquid filling pipeline forms a liquid inlet connector, and the second end of the liquid filling pipeline forms a liquid outlet connector. The first end of the gas-state circulating pipeline forms a gas inlet connector, and the second end of the gas-state circulating pipeline forms a gas outlet connector. And the release valve is arranged on the liquid filling pipeline. The inerting system is arranged in the vehicle body and comprises a nitrogen inlet, and the nitrogen inlet is formed in the vehicle body. According to the ship fuel filling device, the filling system and the inerting system are both integrated on the vehicle body, the filling device can be conveniently moved to the filling position to conduct ship fuel filling operation, and the deployment efficiency is high.

The present invention relates to an inert gas distribution system for a fuel tank. The fuel tank includes fuel and a gaseous space. The inert gas distribution system includes: a gas inlet port for introducing inert gas; a gas branch line that is fluidically connected to the gas inlet port and can be arranged within the fuel tank; the gas branch line includes a plurality of exhaust holes distributed along its length, at least one of the plurality of exhaust holes being submersible into the fuel within the fuel tank. Thus, as the fuel liquid level decreases, at least one exhaust hole is exposed to the gaseous space, allowing inert gas to flow therein, thereby regulating the flow rate of the inert gas distributed to the fuel tank. Thus, a simple structure can be used to resolve the mismatch between the inert gas flow distribution within the fuel tank and the volume of the gaseous space within the fuel tank, rapidly reducing the flammability of the fuel tank. The present invention also relates to an aircraft fuel tank inerting system and a method for regulating the flow rate of inert gas within the fuel tank.

The application provides a system for processing excess BOG of an LNG ship, and belongs to the technical field of ships.The system comprises a BOG supply system, an excess BOG utilization system, a flue gas energy storage system, a flue gas energy release system and an inerting system.Based on the complex sailing conditions of a ship, when the LNG ship sails at low load, sails in a maneuvering mode or is anchored, the excess BOG generated in the LNG liquid cargo tank is sent into a boiler for combustion, and then the energy of the excess BOG is converted into the pressure energy of flue gas and stored through a series of devices, so that the problem of waste of the BOG in the excess state is effectively solved; when the ship sails at high load or is unloaded at a discharge port, the energy of the flue gas is released, so that the energy of the BOG is reused.In addition, the stored flue gas can also be used for inerting of low-temperature pipelines and equipment at normal temperature or at a temperature of 0 DEG C to -60 DEG C, so that the inerting cost of the ship is reduced.

An inerting system for an aircraft and a method of inerting fuel cell systems. The inerting system injects inert gas into a casing around the fuel cells in a distributed manner to ensure a correct dissolution of flammable agents like oxygen and hydrogen that could be present inside the casing around the fuel cells.

The invention discloses an aircraft fuel tank composite inerting system and method based on liquid hydrogen cold energy gradient utilization, and belongs to the technical field of aviation safety. The system comprises a liquid hydrogen supply module, a membrane method nitrogen-rich gas generation module and a fuel tank active cooling module; the membrane method nitrogen-rich gas generation module comprises an electric compressor, a first micro-channel heat exchanger and an air separation membrane assembly; the electric compressor, a hot side channel of the first micro-channel heat exchanger and the air separation membrane assembly are sequentially connected, and a nitrogen-rich gas outlet of the air separation membrane assembly is connected with an oil tank of an airplane. The oil tank active cooling module comprises a second micro-channel heat exchanger and a cold plate; the cold plate is arranged in the oil tank; a hot side channel of the second micro-channel heat exchanger is connected with the cold plate to form a cooling medium circulation loop; the liquid hydrogen supply module, a cold side channel of the first micro-channel heat exchanger and a cold side channel of the second micro-channel heat exchanger are sequentially connected. The invention has the advantages of high energy efficiency, safety, reliability, strong environmental adaptability and the like.

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.