CN109018387B - Aircraft fuel tank inerting device adopting high-pressure water removal and method thereof - Google Patents
Aircraft fuel tank inerting device adopting high-pressure water removal and method thereof Download PDFInfo
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- CN109018387B CN109018387B CN201811018318.7A CN201811018318A CN109018387B CN 109018387 B CN109018387 B CN 109018387B CN 201811018318 A CN201811018318 A CN 201811018318A CN 109018387 B CN109018387 B CN 109018387B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Abstract
The invention discloses an aircraft fuel tank inerting device adopting high-pressure water removal and a method thereof, wherein engine bleed air or cabin bleed air and aircraft carried hydrogen are utilized to react with oxyhydrogen fuel cells to consume oxygen in the air so as to generate inert gas for reducing the gas-phase space oxygen concentration of the fuel tank, simultaneously, the fuel cells react to generate a large amount of water vapor, a three-wheel high-pressure water removal system is utilized to separate the inert gas generated by the reaction, the collected and separated water can be used for daily water of the aircraft, and meanwhile, the electric energy generated by the fuel cell reaction is used for power supply equipment of the aircraft. The system is simple and stable, can reduce energy consumption, reduce the influence of high-pressure side bleed air of the engine on the performance of the engine, and can reduce the compensation loss of the aircraft.
Description
Technical Field
The invention relates to the technical field of fire prevention and explosion prevention, in particular to an aircraft fuel tank inerting device adopting high-pressure water removal and a method thereof.
Background
The oxygen concentration in the gas phase space of the aircraft fuel tank is higher than the limit combustible oxygen concentration, and when an external ignition source such as thunder, static electricity, gunfire striking and the like exists, the fuel vapor and air mixture is extremely easy to burn and explode, so that the aircraft is destroyed and the aircraft is killed, and the potential safety hazard of life and property is caused greatly. In 7.17 1996, a TWA No. 800 airliner in the world of world airlines flown from International airport in Kennidi, N.Y. to take off from Paris-Dawley airport to facilitate air explosion on long islands, resulting in difficulties for 230 passengers and crewmembers onboard. The accident is found to be that electric sparks are generated by short circuit caused by broken wires on an airplane and enter the oil tank, so that the oil tank with the central wing is ignited and exploded. After the accident, the gas phase space flammability of the oil tank is reduced, and the safety of the aircraft oil tank is protected, so that the safety of researchers is widely concerned. The three factors of the fire disaster of the oil tank are ignition source, combustible and combustion improver. Because the ignition source is uncontrollable, the volatility of the fuel results in the vapor phase space always having fuel vapor, so an important measure for preventing the fire of the aircraft fuel tank is to reduce the presence of oxygen as a combustion improver. Studies have shown that fire is effectively prevented when the gas phase space oxygen concentration in the aircraft tank is below 12% (civilian aircraft) and 9% (military aircraft). The Federal Aviation Administration (FAA) in the United states has shown through a number of theoretical and experimental studies that the tank inerting technique is an economical and effective method for reducing the gas phase space oxygen concentration of the tank.
The fuel tank inerting technology refers to the method that inert gases such as nitrogen, carbon dioxide or nitrogen-rich gases (the nitrogen concentration can reach 98%) are filled into a gas phase space of a fuel tank to convert oxygen out of the gas phase space, so that the oxygen concentration is reduced, the purposes of reducing the combustibility of the gas phase space and protecting the safety of the fuel tank are achieved. The currently developed and mature fuel tank inerting technology is an airborne nitrogen making inerting technology, and the fuel tank is inerted by utilizing high-pressure engine bleed air to prepare nitrogen-rich gas through a hollow fiber membrane, and the technology is widely applied to military engines such as F-15, F-22, F-35, C-17 and the like, boeing 747, airbus A320 and the like. However, the technology has the problems of low separation efficiency, easy blockage, high membrane inlet pressure, large engine air-entraining amount and the like of the hollow fiber membrane from the current state of domestic and foreign application.
And with the development of flight technology, aircraft manufacturing is moving toward larger capacity and safer, while the addition of aircraft electronics and passengers has placed higher demands on aircraft power and water supply.
Disclosure of Invention
Aiming at the defects related to the background technology, the invention provides the aircraft fuel tank inerting device adopting high-pressure water removal and the method thereof, which can reduce the compensation loss of the aircraft in the fuel tank inerting process, improve the energy utilization rate and ensure the flight safety of the aircraft.
The invention adopts the following technical scheme for solving the technical problems:
an aircraft fuel tank inerting device adopting high-pressure water removal comprises a hydrogen storage bottle, a first heat exchanger, an oxyhydrogen fuel cell, a first air compressor, a second heat exchanger, a fan, a water separator, a turbine expander, a water storage tank, a one-way valve and a fuel tank;
the hydrogen storage bottle is provided with a high-pressure hydrogen outlet; the oxyhydrogen fuel cell is provided with an anode gas inlet, a cathode gas inlet, an electric energy output port and a tail gas outlet; the water separator is provided with a gas inlet, a liquid water outlet and a gas outlet; the oil tank is provided with an inert gas inlet and a gas outlet; the water storage tank is provided with an inlet and an outlet;
the inlet of the hot side channel of the first heat exchanger is used for introducing engine bleed air, and the outlet of the hot side channel of the first heat exchanger is connected with the cathode gas inlet of the oxyhydrogen fuel cell;
the anode gas inlet of the oxyhydrogen fuel cell is connected with the high-pressure hydrogen outlet of the hydrogen storage bottle, and the electric energy output port is connected with external aircraft electric equipment;
the tail gas outlet of the oxyhydrogen fuel cell, the hot side channel of the first air compressor, the hot side channel of the second heat exchanger and the gas inlet of the water separator are sequentially connected;
the gas outlet of the water separator, the turbine expander, the one-way valve and the inert gas inlet of the oil tank are sequentially connected;
the liquid water outlet of the water separator is connected with the inlet of the water storage tank, and the outlet of the water storage tank is connected with external water equipment;
the rotating shaft of the turboexpander is coaxially and fixedly connected with the rotating shaft of the first air compressor and the rotating shaft of the fan respectively, wherein the turboexpander is used for cooling the gas discharged from the water separator, and simultaneously providing power for the first air compressor and the fan and driving the first air compressor and the fan to work;
the inlet of the second heat exchanger cold side channel is connected with ram air, and the outlet of the second heat exchanger cold side channel, the fan and the inlet of the first heat exchanger cold side channel are connected;
and the outlet of the cold side channel of the first heat exchanger and the gas outlet of the oil tank are both connected with the external atmosphere.
As a further optimization scheme of the aircraft fuel tank inerting device adopting high-pressure water removal, the aircraft fuel tank inerting device further comprises a second air compressor and a first motor;
the air inlet of the second air compressor is connected with the cabin air entraining and the air outlet of the second air compressor and is connected with the inlet of the hot side channel of the first heat exchanger;
the rotating shaft of the first motor is coaxially and fixedly connected with the rotating shaft of the second air compressor, and is used for providing power for the second air compressor and driving the second air compressor to work.
As a further optimization scheme of the aircraft fuel tank inerting device adopting high-pressure water removal, the aircraft fuel tank inerting device further comprises a second motor, a fuel injector and an oil pump;
the rotating shaft of the second motor is coaxially and fixedly connected with the rotating shaft of the first air compressor, and is used for further lifting power to the first air compressor and driving the first air compressor to work;
the fuel injector is provided with a gas inlet, a fuel inlet and an oil-gas mixture outlet; the bottom of the oil tank is also provided with an oil-gas mixture inlet and a fuel outlet; the oil pump is provided with a fuel inlet and a fuel outlet;
the fuel inlet of the oil pump is connected with the fuel outlet of the oil tank, and the fuel outlet of the oil pump is connected with the fuel inlet of the fuel injector;
the gas inlet of the fuel injector is connected with the gas outlet of the one-way valve, and the oil-gas mixture outlet of the fuel injector is connected with the oil-gas mixture inlet of the oil tank;
the inert gas inlet of the oil tank is closed.
The invention also discloses a working method based on the aircraft fuel tank inerting device adopting high-pressure water removal, which comprises the following steps:
the hydrogen in the hydrogen storage bottle and the engine bleed air cooled by the first heat exchanger react in the oxyhydrogen fuel cell, oxygen is consumed, water is produced at the same time, electric energy generated by the reaction is input into external power supply equipment, the tail gas of the reaction passes through the first air compressor, the second heat exchanger and the water separator to obtain separated liquid water and dry inert gas, wherein the liquid water is stored in the water storage tank and then is supplied to external water equipment, and the dry inert gas is cooled by the turbine expander and then enters the gas phase space of the oil tank through the one-way valve to be mixed so as to reduce the oxygen concentration in the gas phase space of the oil tank.
Compared with the prior art, the technical scheme provided by the invention has the following technical effects:
the invention utilizes engine bleed air or cabin bleed air to generate electric energy and water through hydrogen-oxygen fuel cell reaction to provide daily-increase electricity and water consumption. The hydrogen-oxygen fuel cell is used for generating water vapor and nitrogen-rich tail gas through real-time reaction, and the three-wheel pressurizing high-pressure water removal system is used for separating water for storing and utilizing liquid water, so that the initial water storage capacity of the aircraft is reduced, the total take-off mass of the aircraft is reduced, and the compensation loss of the aircraft is reduced. And meanwhile, the dry inert gas subjected to high-pressure water removal enters the oil tank to reduce the oxygen concentration in the gas phase space, so that the safety of the oil tank is ensured. The system can bleed air from the low-pressure side of the engine or the cabin, reduces the influence of the bleed air from the high-pressure side of the engine on the performance of the engine, simultaneously provides electric energy and water for the aircraft, reduces the compensation loss of the aircraft and improves the energy utilization rate.
Drawings
FIG. 1 is a system diagram of an aircraft fuel tank inerting with high pressure water removal using engine bleed air of example 1;
FIG. 2 is a system diagram of the inerting of an aircraft fuel tank using high pressure water removal using cabin bleed air of example 2;
fig. 3 is a system diagram of the aircraft fuel tank wash inerting with high pressure water removal using cabin bleed air of example 3.
In the figure, 1, a hydrogen storage bottle, 2, a first heat exchanger, 3, an oxyhydrogen fuel cell, 4, electric equipment, 5, a first air compressor, 6, a second heat exchanger, 7, a fan, 8, a water separator, 9, a turboexpander, 10, a water storage tank, 11, a one-way valve, 12, water equipment, 13, an oil tank, 101, a second air compressor, 102, a first motor, 201, a second motor, 202, a fuel injector, 203 and an oil pump.
Detailed Description
The technical scheme of the invention is further described in detail below with reference to the accompanying drawings:
this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, the components are exaggerated for clarity.
1) Example 1:
FIG. 1 is a system for inerting an aircraft fuel tank employing high pressure water removal using engine bleed air, comprising a hydrogen storage bottle 1, a first heat exchanger 2, a hydrogen-oxygen fuel cell 3, a first compressor 5, a second heat exchanger 6, a fan 7, a water separator 8, a turbo-expander 9, a water storage tank 10, a check valve 11 and a fuel tank 13; the hydrogen storage bottle 1 is provided with a high-pressure hydrogen outlet; the oxyhydrogen fuel cell 3 is provided with an anode gas inlet, a cathode gas inlet, an electric energy output port and a tail gas outlet; the water separator 8 is provided with a gas inlet, a liquid water outlet and a gas outlet; the oil tank 13 is provided with an inert gas inlet and a gas outlet; the water storage tank 10 is provided with an inlet and an outlet.
The inlet of the hot side channel of the first heat exchanger 2 is used for introducing engine bleed air, and the outlet is connected with the cathode gas inlet of the oxyhydrogen fuel cell 3; the anode gas inlet of the oxyhydrogen fuel cell 3 is connected with the high-pressure hydrogen outlet of the hydrogen storage bottle 1, and the electric energy output port is connected with external aircraft electric equipment 4; the tail gas outlet of the oxyhydrogen fuel cell 3, the first air compressor 5, the hot side channel of the second heat exchanger 6 and the gas inlet of the water separator 8 are sequentially connected; the gas outlet of the water separator 8, the turbo-expander 9, the one-way valve 11 and the inert gas inlet of the oil tank 13 are sequentially connected; the liquid water outlet of the water separator 8 is connected to the inlet of a water storage tank 10, and the outlet of the water storage tank 10 is connected to an external water device 12.
The rotating shafts of the turboexpander 9 are respectively and coaxially fixedly connected with the rotating shaft of the first air compressor 5 and the rotating shaft of the fan 7, wherein the turboexpander 9 is used for cooling the gas discharged from the water separator 8, and simultaneously providing power for the first air compressor 5 and the fan 7 and driving the first air compressor 5 and the fan 7 to work.
The inlet of the cold side channel of the second heat exchanger 6 is connected with ram air, and the outlet of the cold side channel of the second heat exchanger 6, the fan 7 and the inlet of the cold side channel of the first heat exchanger 2 are connected; the outlet of the cold side channel of the first heat exchanger 2 and the gas outlet of the oil tank 13 are both connected with the external atmosphere.
The invention also discloses a working method based on the aircraft fuel tank inerting device adopting high-pressure water removal, which comprises the following specific processes:
the hydrogen in the hydrogen storage bottle 1 and the engine bleed air cooled by the first heat exchanger 2 react in the oxyhydrogen fuel cell 3, oxygen is consumed, water is produced at the same time, electric energy produced by the reaction is input into the external power supply equipment 4, the tail gas of the reaction passes through the first air compressor 5, the second heat exchanger 6 and the water separator 8 to obtain separated liquid water and dry inert gas, wherein the liquid water is stored by the water storage tank 10 and then is supplied to the external water equipment 12, and the dry inert gas is cooled by the turbine expander 9 and then enters the gas-phase space of the oil tank 13 through the one-way valve 11 to be mixed so as to reduce the oxygen concentration in the gas-phase space of the oil tank.
2) Example 2:
as shown in fig. 2, the compressor further comprises a second compressor 101 and a first motor 102 on the basis of embodiment 1; the air inlet of the second air compressor 101 is connected with the cabin air entraining and the air outlet of the second air compressor and is connected with the inlet of the hot side channel of the first heat exchanger 2; the rotating shaft of the first motor 102 is coaxially and fixedly connected with the rotating shaft of the second compressor 101, and is used for providing power for the second compressor and driving the second compressor to work.
The present embodiment differs from embodiment 1 in that the use of the second compressor 101 and the first motor 102 to compress cabin bleed air instead of engine bleed air reduces the impact of engine bleed air on engine performance and reduces aircraft compensation losses.
3, example 3
As shown in fig. 3, the fuel injector further comprises a second motor 201, a fuel injector 202 and an oil pump 203 on the basis of embodiment 2; the rotating shaft of the second motor 201 is coaxially and fixedly connected with the rotating shaft of the first air compressor 5, and is used for further lifting power to the first air compressor 5 and driving the first air compressor 5 to work; the fuel injector 202 is provided with a gas inlet, a fuel inlet and an oil-gas mixture outlet; the oil tank 13 is also provided with an oil-gas mixture inlet and a fuel outlet at the bottom thereof; the oil pump 203 is provided with a fuel inlet and a fuel outlet; the fuel inlet of the oil pump 203 is connected with the fuel outlet of the oil tank 13, and the fuel outlet of the oil pump 203 is connected with the fuel inlet of the fuel injector 202; the gas inlet of the fuel injector 202 is connected with the gas outlet of the one-way valve 11, and the gas-oil mixture outlet of the fuel injector 202 is connected with the gas-oil mixture inlet of the fuel tank 13; the inert gas inlet of the tank 13 is closed.
The present embodiment is different from embodiment 1 and embodiment 2 in that the water separation efficiency can be improved by energizing the first compressor 5 with the second motor 201, and simultaneously the fuel dissolved oxygen and the gas-phase space oxygen concentration can be reduced by washing the fuel with the fuel injector 202 and the oil pump 203, and the influence of the fuel dissolved oxygen on the gas-phase space oxygen concentration can be reduced.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (3)
1. The working method of the aircraft fuel tank inerting device adopting high-pressure water removal comprises the steps of a hydrogen storage bottle (1), a first heat exchanger (2), an oxyhydrogen fuel cell (3), a first air compressor (5), a second heat exchanger (6), a fan (7), a water separator (8), a turbine expander (9), a water storage tank (10), a one-way valve (11) and a fuel tank (13);
the hydrogen storage bottle (1) is provided with a high-pressure hydrogen outlet; the oxyhydrogen fuel cell (3) is provided with an anode gas inlet, a cathode gas inlet, an electric energy output port and a tail gas outlet; the water separator (8) is provided with a gas inlet, a liquid water outlet and a gas outlet; the oil tank (13) is provided with an inert gas inlet and a gas outlet; the water storage tank (10) is provided with an inlet and an outlet;
the inlet of the hot side channel of the first heat exchanger (2) is connected with the inlet of the cathode gas of the oxyhydrogen fuel cell (3) and the inlet and outlet of the engine bleed air;
an anode gas inlet of the oxyhydrogen fuel cell (3) is connected with a high-pressure hydrogen outlet of the hydrogen storage bottle (1), and an electric energy output port is connected with external aircraft electric equipment (4);
the tail gas outlet of the oxyhydrogen fuel cell (3), the hot side channel of the first gas compressor (5), the second heat exchanger (6) and the gas inlet of the water separator (8) are connected in sequence;
the gas outlet of the water separator (8), the turbo-expander (9), the one-way valve (11) and the inert gas inlet of the oil tank (13) are sequentially connected;
the liquid water outlet of the water separator (8) is connected with the inlet of the water storage tank (10), and the outlet of the water storage tank (10) is connected with an external water utilization device (12);
the rotating shaft of the turboexpander (9) is respectively and coaxially fixedly connected with the rotating shaft of the first air compressor (5) and the rotating shaft of the fan (7), wherein the turboexpander (9) is used for cooling the gas discharged from the water separator (8) and simultaneously providing power for the first air compressor (5) and the fan (7) to drive the first air compressor (5) and the fan (7) to work;
the inlet of the cold side channel of the second heat exchanger (6) is connected with ram air, and the outlet of the cold side channel of the second heat exchanger (6), the fan (7) and the inlet of the cold side channel of the first heat exchanger (2) are connected;
the outlet of the cold side channel of the first heat exchanger (2) and the gas outlet of the oil tank (13) are both connected with the external atmosphere;
the working method of the aircraft fuel tank inerting device adopting high-pressure water removal is characterized by comprising the following steps of:
the hydrogen in the hydrogen storage bottle (1) reacts with engine bleed air cooled by the first heat exchanger (2) in the oxyhydrogen fuel cell (3), oxygen is consumed, water is produced at the same time, electric energy produced by the reaction is input into external aircraft electric equipment (4), tail gas of the reaction passes through the first air compressor (5), the second heat exchanger (6) and the water separator (8) to obtain separated liquid water and dry inert gas, wherein the liquid water is stored by the water storage tank (10) and then is supplied to external water equipment (12), and the dry inert gas enters the gas phase space of the oil tank (13) to be mixed through the one-way valve (11) after being cooled by the turbine expander (9) so as to reduce the oxygen concentration in the gas phase space of the oil tank.
2. The method of operating an aircraft fuel tank inerting apparatus employing high pressure water removal of claim 1, further comprising a second compressor (101) and a first motor (102);
the air inlet seat cabin air entraining and air outlet of the second air compressor (101) are connected with the inlet of the hot side channel of the first heat exchanger (2);
the rotating shaft of the first motor (102) is coaxially and fixedly connected with the rotating shaft of the second air compressor (101) and is used for providing power for the second air compressor and driving the second air compressor to work.
3. The method of operating an aircraft fuel tank inerting apparatus employing high pressure water removal of claim 2, further comprising a second motor (201), a fuel injector (202) and an oil pump (203);
the rotating shaft of the second motor (201) is coaxially and fixedly connected with the rotating shaft of the first air compressor (5) and is used for further lifting power to the first air compressor (5) and driving the first air compressor to work;
the fuel injector (202) is provided with a gas inlet, a fuel inlet and an oil-gas mixture outlet; the bottom of the oil tank (13) is also provided with an oil-gas mixture inlet and a fuel outlet; the oil pump (203) is provided with a fuel inlet and a fuel outlet;
the fuel inlet of the oil pump (203) is connected with the fuel outlet of the oil tank (13), and the fuel outlet of the oil pump (203) is connected with the fuel inlet of the fuel injector (202);
the gas inlet of the fuel injector (202) is connected with the gas outlet of the one-way valve (11), and the oil-gas mixture outlet of the fuel injector (202) is connected with the oil-gas mixture inlet of the oil tank (13);
the inert gas inlet of the oil tank (13) is closed.
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| CN201811018318.7A CN109018387B (en) | 2018-09-03 | 2018-09-03 | Aircraft fuel tank inerting device adopting high-pressure water removal and method thereof |
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| CN201811018318.7A CN109018387B (en) | 2018-09-03 | 2018-09-03 | Aircraft fuel tank inerting device adopting high-pressure water removal and method thereof |
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| CN109018387B true CN109018387B (en) | 2023-05-09 |
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| US20200318539A1 (en) * | 2019-04-05 | 2020-10-08 | General Electric Company | Pump Mixer Separator Unit |
| CN110963059B (en) * | 2019-11-27 | 2024-03-19 | 南京航空航天大学 | Cabin pressurizing and oxygenation device and method based on hollow fiber membrane airborne nitrogen production technology |
| CN111071467B (en) * | 2020-01-06 | 2021-05-25 | 南京航空航天大学 | Coupling system and method for inerting membrane nitrogen-making oil tank of airplane and controlling cabin environment |
| CN111071468B (en) * | 2020-01-06 | 2021-04-02 | 南京航空航天大学 | Energy recovery type fuel tank inerting system configuration and working method thereof |
| CN111086645B (en) * | 2020-01-06 | 2021-04-06 | 南京航空航天大学 | Device for reducing combustibility of oil tank by using ring control cold system and working method |
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| US20150333347A1 (en) * | 2012-03-19 | 2015-11-19 | Zodiac Aerotechinics | Fuel cell devices for fire and/or explosion prevention |
| US9604730B2 (en) * | 2014-03-27 | 2017-03-28 | Honeywell International Inc. | Aircraft systems and methods with integrated tank inerting and power generation |
| EP2990337B1 (en) * | 2014-08-28 | 2017-10-25 | Airbus Operations GmbH | Supply system for providing at least oxygen depleted air and water in a vehicle and aircraft having such a supply system |
| CN105083570B (en) * | 2015-09-22 | 2017-02-01 | 伊顿上飞（上海）航空管路制造有限公司 | Nitrogen-rich flushing inerting pipeline system for large commercial aircraft fuel tank |
| CN107867404A (en) * | 2017-11-20 | 2018-04-03 | 南京航空航天大学 | The apparatus and method of fuel tank inerting |
| CN208931665U (en) * | 2018-09-03 | 2019-06-04 | 南京航空航天大学 | A kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system |
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