CN111071466A - Aircraft fuel tank inerting system and working method thereof - Google Patents
Aircraft fuel tank inerting system and working method thereof Download PDFInfo
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- CN111071466A CN111071466A CN202010010275.9A CN202010010275A CN111071466A CN 111071466 A CN111071466 A CN 111071466A CN 202010010275 A CN202010010275 A CN 202010010275A CN 111071466 A CN111071466 A CN 111071466A
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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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0651—Environmental Control Systems comprising filters, e.g. dust filters
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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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0681—Environmental Control Systems with oxygen control
Abstract
The invention discloses an aircraft fuel tank inerting system and a working method thereof, and belongs to the technical field of fire prevention and explosion prevention. The invention introduces air from an aircraft engine, and enters a hollow fiber membrane air separation device after drying and filtering to prepare high-concentration nitrogen-rich gas, and the nitrogen-rich gas is introduced into an oil tank to reduce the oxygen concentration of the oil tank, thereby preventing the oil tank from being ignited and exploded to achieve the aim of inerting the oil tank; the system can realize fuel oil washing, oxygen removal and inerting of the fuel oil tank in the climbing stage of the airplane, flushing, oxygen removal and inerting of the gas phase space of the fuel oil tank in the cruising and descending stages of the airplane, monitor the oxygen concentration of the gas phase space of the fuel oil tank in real time through the oxygen concentration sensor, transmit signals to the control system, and adjust the air entraining amount of the engine by utilizing the control system according to the oxygen concentration so as to reduce the influence of the air entraining of the engine on the performance of the engine.
Description
Technical Field
The invention relates to the technical field of fire prevention and explosion prevention, in particular to an aircraft fuel tank inerting system and a working method thereof.
Background
With the development of economy and the progress of society, airplanes gradually become the mainstream means of transportation for trip, but airplane safety accidents happen occasionally, and great threat is generated to the safety of lives and properties of passengers, wherein the explosion of an airplane fuel tank is one of the main causes of flight accidents. For civil aircraft, when the oxygen concentration (volume fraction) in the gas phase space in the aircraft fuel tank is higher than 12%, the fuel tank is easy to burn and explode to cause the death of people and people when ignition sources such as thunder and lightning, static electricity, line electric sparks and the like exist. How to reduce the flammability of aircraft fuel tanks is therefore a critical issue in aircraft design.
Researches show that inert gases such as nitrogen, carbon dioxide and the like are used for replacing gas phase space of an oil tank or dissolved oxygen in fuel oil, so that the oxygen concentration in the oil tank is lower than the limit combustible concentration, the combustibility of the oil tank can be effectively reduced, and the occurrence of fire of an aircraft oil tank is reduced. At present, an aircraft fuel tank inerting system mainly adopts an airborne hollow fiber membrane nitrogen-making inerting system to flush and inerte a fuel tank, namely nitrogen-rich gas generated by the hollow fiber membrane nitrogen-making system is introduced into a gas phase space of the fuel tank to displace oxygen in the gas phase space, so as to reduce the oxygen concentration, but dissolved oxygen in fuel oil easily escapes along with the reduction of the pressure of the gas phase space in the climbing stage of an aircraft, so that the dissolved oxygen in the fuel oil is displaced by adopting fuel oil washing and inerting in the stage, so as to reduce the influence of the dissolved oxygen on the oxygen concentration of the gas phase space, and the oxygen concentration in the gas phase space in the fuel tank is greatly increased mainly because external air enters the fuel tank due to fuel oil consumption in the cruising and descending stages, so that a fuel tank flushing inerting mode is mainly adopted in the cruising and descending stages, and the oxygen concentration sensor is utilized to monitor the oxygen concentration of the gas, the air entraining amount of the engine is reduced, and the influence of the air entraining on the performance of the engine is reduced.
Disclosure of Invention
The invention discloses an aircraft fuel tank inerting system and a working method thereof, aiming at the problems in the prior art, the inerting mode of an aircraft at different flight stages is changed, so that the inerting efficiency of a fuel tank is improved, and meanwhile, the air entraining quantity of an engine is changed by monitoring the oxygen concentration in real time, so that the air entraining quantity of the engine is reduced, the influence of the air entraining quantity on the performance of the engine is reduced, and the safety of the aircraft is guaranteed.
The invention is realized by the following steps:
an aircraft fuel tank inerting system is characterized in that components connected in sequence in the system comprise a first electromagnetic valve, a dry filter, a heat exchanger, a water separator, a second electromagnetic valve, a hollow fiber membrane air separation component and a three-way valve; the heat exchanger is respectively connected with the drying filter and the water separator through the hot side of the heat exchanger, and the cold side of the heat exchanger is exhausted to the external environment through introducing ram air; the hollow fiber membrane air separation component is respectively provided with two gas outlets, wherein one nitrogen-rich gas outlet is connected with an inlet of a three-way valve, and the other oxygen-rich gas outlet is connected with an aircraft cabin; the three-way valve is provided with two outlets, a first outlet of the three-way valve is connected with an inlet of the third electromagnetic valve, and a second outlet of the three-way valve is sequentially connected with the fourth electromagnetic valve and a gas inlet of the fuel injector; the outlet of the third electromagnetic valve is connected with a nitrogen-rich gas inlet of an aircraft fuel tank; a fuel pump is connected between the liquid inlet of the fuel injector and the fuel outlet at the bottom of the aircraft fuel tank, and the gas-liquid mixing outlet of the fuel injector is communicated with the bottom of the aircraft fuel tank; the upper part of the aircraft fuel tank is connected with an oxygen concentration sensor.
Further, an inlet of the first electromagnetic valve is connected with an engine air-entraining end, or an inlet of the first electromagnetic valve is connected with an aircraft cabin, and a gas compressor is further arranged between the aircraft cabin and the inlet of the first electromagnetic valve.
Further, the system is controlled by a control system; specifically, the control system is respectively connected with the first electromagnetic valve, the second electromagnetic valve, the third electromagnetic valve, the fourth electromagnetic valve and the oxygen concentration sensor in a control mode.
Furthermore, the signal input end of the first electromagnetic valve is connected with the signal output end of the control system through a cable; the signal input end of the second electromagnetic valve is connected with the signal output end of the control system through a cable; the signal input end of the third electromagnetic valve is connected with the signal output end of the control system through a cable; the signal input end of the fourth electromagnetic valve is connected with the signal output end of the control system through a cable; and the signal output end of the oxygen concentration sensor is connected with the signal input end of the control system through a cable.
The invention also discloses a working method of the aircraft fuel tank inerting system, which is characterized in that an inlet of the first electromagnetic valve is connected with an engine air-entraining end, and the working method of the system comprises the following steps: high-pressure bleed air of an aircraft engine flows through a first electromagnetic valve, impurities and moisture in the air are removed by a drying filter, then the high-pressure bleed air enters a hot side channel of a heat exchanger, the cold side of the heat exchanger is used for stamping air for cooling, the stamped air is discharged to the external environment after passing through the heat exchanger, the moisture in the air is removed by a water separator after the air is cooled, the air enters a gas inlet of a hollow fiber membrane air separation assembly after passing through a second electromagnetic valve, the air is separated by a hollow fiber membrane to form oxygen-enriched gas and nitrogen-enriched gas, the oxygen-enriched gas enters an aircraft cabin for pressurization and oxygen supply;
1) the control system closes the third electromagnetic valve and opens the fourth electromagnetic valve in the takeoff and climbing stage of the airplane, the nitrogen-rich gas only enters the fuel injector to be mixed with the high-pressure fuel conveyed by the fuel pump and is conveyed into the oil tank from the bottom of the airplane oil tank to replace oxygen dissolved in the fuel, meanwhile, the nitrogen-rich gas enters the gas phase space of the airplane oil tank to replace gas phase space oxygen, and finally, the nitrogen-rich gas is discharged into the external environment to reduce the concentration of the oxygen in the oil tank;
2) when the aircraft is in a cruising or descending stage, the control system opens the third electromagnetic valve, closes the fourth electromagnetic valve, allows nitrogen-rich gas to enter the gas phase space of the aircraft oil tank only through the third electromagnetic valve, and replaces and exhausts oxygen in the gas phase space to the external environment, so as to reduce the oxygen concentration in the aircraft oil tank;
3) the oxygen concentration sensor installed on the upper portion of the aircraft fuel tank monitors the oxygen concentration of the gas phase space of the fuel tank in real time and transmits signals to the control system, and the control system adjusts the air entraining amount of the engine by adjusting the opening degree of the first electromagnetic valve and the second electromagnetic valve, so that the nitrogen-rich gas flow is adjusted, and the air entraining amount of the engine can be reduced while the oxygen concentration of the aircraft fuel tank is reduced.
The invention also discloses a working method of the aircraft fuel tank inerting system, which is characterized in that an inlet of the first electromagnetic valve is connected with an aircraft cabin, a gas compressor is arranged between the aircraft cabin and the inlet of the first electromagnetic valve, and the working method of the system comprises the following steps: air in the cabin is sucked by the compressor, enters the first electromagnetic valve, impurities and moisture in the air are removed by the aid of the drying filter, then enters the hot side channel of the heat exchanger, the cold side of the heat exchanger is used for stamping the air for cooling, the stamped air is discharged to the external environment after passing through the heat exchanger, the moisture in the air is removed by the aid of the water separator after being cooled, the air enters the gas inlet of the hollow fiber membrane air separation assembly after passing through the second electromagnetic valve, the air is separated by the hollow fiber membrane to form oxygen-enriched gas and nitrogen-enriched gas, the oxygen-enriched gas enters the aircraft cabin for pressurization and oxygen supply, and the nitrogen-;
1) the control system closes the third electromagnetic valve and opens the fourth electromagnetic valve in the takeoff and climbing stage of the airplane, the nitrogen-rich gas only enters the fuel injector to be mixed with the high-pressure fuel conveyed by the fuel pump and is conveyed into the oil tank from the bottom of the airplane oil tank to replace oxygen dissolved in the fuel, meanwhile, the nitrogen-rich gas enters the gas phase space of the airplane oil tank to replace gas phase space oxygen, and finally, the nitrogen-rich gas is discharged into the external environment to reduce the concentration of the oxygen in the oil tank;
2) when the aircraft is in a cruising or descending stage, the control system opens the third electromagnetic valve, closes the fourth electromagnetic valve, allows nitrogen-rich gas to enter the gas phase space of the aircraft oil tank only through the third electromagnetic valve, and replaces and exhausts oxygen in the gas phase space to the external environment, so as to reduce the oxygen concentration in the aircraft oil tank;
3) the oxygen concentration sensor installed on the upper portion of the aircraft fuel tank monitors the oxygen concentration of the gas phase space of the fuel tank in real time and transmits signals to the control system, and the control system adjusts the air entraining amount of the engine by adjusting the opening degree of the first electromagnetic valve and the second electromagnetic valve, so that the nitrogen-rich gas flow is adjusted, and the air entraining amount of the engine can be reduced while the oxygen concentration of the aircraft fuel tank is reduced.
The invention combines the modes of flushing the oil tank and inerting washing by using the fuel injector, can realize free switching of the inerting modes in different flight stages, and has the advantages compared with the prior art that:
according to the invention, the flow direction of the nitrogen-rich gas is adjusted through the automatic control system, and fuel washing and upper space flushing of the oil tank are combined, so that the problem of low efficiency of the existing single inerting mode of fuel washing and flushing of the airplane is solved, the airplane can realize different inerting modes in different flight stages, the inerting efficiency of the oil tank is effectively improved, and the oxygen concentration in the oil tank is reduced; meanwhile, the time monitoring is carried out on the gas phase space of the oil tank according to the oxygen concentration sensor, and the gas-entraining flow of the engine is fed back to the control system to adjust, so that the gas-entraining amount of the engine can be effectively reduced, the influence of the gas-entraining on the performance of the engine is further reduced, and the flight safety is guaranteed.
Drawings
FIG. 1 is a diagram of an aircraft fuel tank inerting system utilizing engine bleed air in accordance with example 1 of the present invention;
fig. 2 is a diagram of an aircraft fuel tank inerting system for bleeding air from an aircraft cabin according to example 2 of the present invention.
The system comprises a first electromagnetic valve 1, a first electromagnetic valve 2, a drying filter 3, a heat exchanger, a second electromagnetic valve 4, a water separator 5, a second electromagnetic valve 6, a hollow fiber membrane air separation assembly 7, a three-way valve 8, a third electromagnetic valve 9, an aircraft fuel tank 10, an oxygen concentration sensor 101, a control system 201, a fourth electromagnetic valve 202, a fuel injector 203, a fuel pump 1001, an aircraft cabin 1002 and a gas compressor.
Detailed Description
The present 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, components are exaggerated for clarity.
Example 1
As shown in fig. 1, fig. 1 is an aircraft fuel tank inerting system using engine bleed air, which comprises a first solenoid valve 1, a dry filter 2, a heat exchanger 3, a water separator 4, a second solenoid valve 5, a hollow fiber membrane air separation assembly 6, a three-way valve 7, a third solenoid valve 8 and an aircraft fuel tank 9;
an inlet of the first electromagnetic valve 1 is connected with an engine air-entraining end, and a signal input end of the first electromagnetic valve 1 is connected with a signal output end of the control system 101 through a cable; the hot side of the heat exchanger 3 is connected with the drying filter 2 and the water separator 4, and the cold side is discharged to the external environment by introducing ram air; the inlet of the second electromagnetic valve 5 is connected with the water separator 4, the outlet of the second electromagnetic valve is connected with the air-entraining inlet of the hollow fiber membrane air separation component 6, and the signal input end of the second electromagnetic valve is connected with the signal output end of the control system 101 through a cable; the oxygen-rich gas outlet of the hollow fiber membrane air separation component 6 is connected with an aircraft cabin, and the nitrogen-rich gas outlet is connected with the inlet of a three-way valve 7; a first outlet of the three-way valve 7 is connected with an inlet of the third electromagnetic valve 8, and a second outlet is sequentially connected with a fourth electromagnetic valve 201 and a gas inlet of the fuel injector 202; the outlet of the third electromagnetic valve 8 is connected with a nitrogen-rich gas inlet of an aircraft fuel tank 9, and the signal input end is connected with the signal output end of the control system 101 through a cable; the upper part of the aircraft fuel tank 9 is connected with an oxygen concentration sensor 10, and the signal output end of the oxygen concentration sensor 10 is connected with the signal input end of a control system through a cable; the signal input end of the fourth electromagnetic valve 201 is connected with the signal output end of the control system 101 through a cable; a fuel pump 203 is connected between the liquid inlet of the fuel injector 202 and the fuel outlet at the bottom of the aircraft fuel tank 9, and the gas-liquid mixing outlet of the fuel injector 202 is communicated with the bottom of the aircraft fuel tank 9.
The invention also discloses a working method of the aircraft fuel tank inerting system, wherein an inlet of the first electromagnetic valve is connected with an engine air-entraining end, and the specific process is as follows:
the high pressure bleed air of aircraft engine utilizes drier-filter 2 to detach impurity and moisture in the air behind first solenoid valve 1, get into 3 hot side passageways of heat exchanger afterwards, utilize cold side ram air to cool down, ram air discharges to external environment behind heat exchanger 3, the moisture in the air is got rid of through water separator 4 after the gas is cooled down, get into the 6 gas inlets of hollow fiber membrane air separation subassembly behind second solenoid valve 5, the air forms oxygen-enriched gas and rich nitrogen gas through hollow fiber membrane separation, oxygen-enriched gas gets into aircraft cabin pressure boost oxygen suppliment, the three-way valve 7 is flowed through to the oxygen-enriched gas.
The control system closes the third electromagnetic valve 8 and opens the fourth electromagnetic valve 201 in the takeoff and climbing stage of the airplane, the nitrogen-rich gas only enters the fuel injector 202 to be mixed with the high-pressure fuel conveyed by the fuel pump 203 and is conveyed into the oil tank from the bottom of the airplane oil tank so as to replace oxygen dissolved in the fuel, meanwhile, the nitrogen-rich gas enters the gas phase space of the airplane oil tank and then replaces oxygen in the gas phase space, and finally, the nitrogen-rich gas is discharged into the external environment so as to reduce the concentration of the oxygen in the oil tank.
When the aircraft is in a cruising or descending stage, the control system opens the third electromagnetic valve 8, the fourth electromagnetic valve 201 is closed, the nitrogen-rich gas only enters the gas phase space of the aircraft oil tank through the third electromagnetic valve 8, and the gas phase space oxygen is replaced and discharged to the external environment, the oxygen concentration in the aircraft oil tank is reduced, the oxygen concentration sensor 10 installed on the upper portion of the aircraft oil tank monitors the gas phase space oxygen concentration of the oil tank in real time and transmits signals to the control system, the control system adjusts the engine air entraining amount by adjusting the opening degree of the first electromagnetic valve 1 and the second electromagnetic valve 2, so that the nitrogen-rich gas flow is adjusted, and the engine air entraining amount can be reduced while the oxygen concentration of the aircraft oil tank is reduced. In the embodiment, the air is introduced from the aircraft engine, dried and filtered, and then enters the hollow fiber membrane air separation device to prepare the high-concentration nitrogen-rich gas, and the nitrogen-rich gas is introduced into the oil tank to reduce the oxygen concentration of the oil tank, so that the aim of inerting the oil tank by preventing the oil tank from being ignited and exploded is fulfilled. The system can realize fuel oil washing, oxygen removal and inerting of the fuel oil tank in the climbing stage of the airplane, gas phase space washing, oxygen removal and inerting of the fuel oil tank in the cruising and descending stages of the airplane, real-time monitoring of the oxygen concentration of the gas phase space of the fuel oil tank through the oxygen concentration sensor, signal transmission to the control system, and adjustment of the engine bleed air quantity by the control system according to the oxygen concentration so as to reduce the influence of the engine bleed air on the performance of the engine bleed air
Example 2
As shown in fig. 2, on the basis of the embodiment 1, the inerting system is changed into cabin bleed air, and air in the cabin is sucked by a compressor to enter the inerting system, so that the nitrogen-rich gas is obtained. Specifically, the inlet of the first electromagnetic valve 1 is connected with an aircraft cabin 1001, and a gas compressor 1002 is arranged between the aircraft cabin 1001 and the inlet of the first electromagnetic valve 1
The working method of the embodiment is different from the working method of the embodiment 1 in that the air is introduced into the cockpit by utilizing the aircraft cockpit, and the air in the cockpit is sucked by the compressor and enters the inerting system, so that the preparation of the nitrogen-rich gas is realized, the influence of the air introduced by the aircraft engine on the performance of the engine is eliminated, the fuel compensation loss of the aircraft is reduced, and the safety of the aircraft is ensured.
The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only illustrative of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. An aircraft fuel tank inerting system is characterized in that components connected in sequence in the system comprise a first electromagnetic valve (1), a drying filter (2), a heat exchanger (3), a water separator (4), a second electromagnetic valve (5), a hollow fiber membrane air separation component (6) and a three-way valve (7);
the heat exchanger (3) is respectively connected with the drying filter (2) and the water separator (4) through the hot side of the heat exchanger, and ram air is introduced into the cold side of the heat exchanger (3) and is exhausted to the external environment;
the hollow fiber membrane air separation component (6) is respectively provided with two gas outlets, wherein a nitrogen-rich gas outlet is connected with an inlet of a three-way valve (7), and a oxygen-rich gas outlet is connected with an aircraft cabin;
the three-way valve (7) is provided with two outlets, a first outlet of the three-way valve (7) is connected with an inlet of the third electromagnetic valve (8), and a second outlet is sequentially connected with a fourth electromagnetic valve (201) and a gas inlet of the fuel injector (202); the outlet of the third electromagnetic valve (8) is connected with a nitrogen-rich gas inlet of an aircraft fuel tank (9);
a fuel pump (203) is connected between a liquid inlet of the fuel injector (202) and a fuel outlet at the bottom of the aircraft fuel tank (9), and a gas-liquid mixing outlet of the fuel injector (202) is communicated with the bottom of the aircraft fuel tank (9); the upper part of the aircraft fuel tank (9) is connected with an oxygen concentration sensor (10).
2. An aircraft fuel tank inerting system according to claim 1, characterized in that the inlet of the first solenoid valve (1) is connected to the bleed air end of the engine, or the inlet of the first solenoid valve (1) is connected to the cockpit (1001), and a gas compressor (1002) is arranged between the cockpit (1001) and the inlet of the first solenoid valve (1).
3. An aircraft fuel tank inerting system as claimed in claim 1, characterized in that said system is controlled by a control system (101); specifically, the control system (101) is respectively in control connection with the first electromagnetic valve (1), the second electromagnetic valve (5), the third electromagnetic valve (8), the fourth electromagnetic valve (201) and the oxygen concentration sensor (10).
4. An aircraft fuel tank inerting system according to claim 3, characterized in that the signal input of the first solenoid valve (1) is connected to the signal output of the control system (101) by means of a cable; the signal input end of the second electromagnetic valve (5) is connected with the signal output end of the control system (101) through a cable; the signal input end of the third electromagnetic valve (8) is connected with the signal output end of the control system (101) through a cable; the signal input end of the fourth electromagnetic valve (201) is connected with the signal output end of the control system (101) through a cable; and the signal output end of the oxygen concentration sensor (10) is connected with the signal input end of the control system through a cable.
5. A method for operating an aircraft fuel tank inerting system according to claim 1, characterized in that the inlet of the first solenoid valve (1) is connected to the bleed air end of the engine, and in that the method for operating the system comprises:
high-pressure bleed air of an aircraft engine flows through a first electromagnetic valve (1), then impurities and moisture in the air are removed by a drying filter (2), then the high-pressure bleed air enters a hot side channel of a heat exchanger (3), cold side ram air of the heat exchanger (3) is used for cooling, the ram air is discharged to the external environment after passing through the heat exchanger (3), the moisture in the air is removed by a water separator (4) after the air is cooled, the air enters a gas inlet of a hollow fiber membrane air separation component (6) after passing through a second electromagnetic valve (5), the air is separated by a hollow fiber membrane to form oxygen-enriched gas and nitrogen-enriched gas, the oxygen-enriched gas enters an aircraft cabin for pressurizing and supplying oxygen, and the nitrogen-enriched gas flows through a;
1) the control system (101) closes the third electromagnetic valve (8) and opens the fourth electromagnetic valve (201) in the takeoff and climbing stage of the airplane, the nitrogen-rich gas only enters the fuel injector (202) to be mixed with the high-pressure fuel conveyed by the fuel pump (203) and is conveyed into the oil tank from the bottom of the airplane oil tank (9) so as to replace oxygen dissolved in the fuel, meanwhile, the nitrogen-rich gas enters the gas phase space of the airplane oil tank (9) and then replaces the gas phase space oxygen, and finally, the nitrogen-rich gas is discharged into the external environment so as to reduce the concentration of the oxygen in the oil tank;
2) when the aircraft is in a cruising or descending stage, the control system (101) opens the third electromagnetic valve (8), closes the fourth electromagnetic valve (201), and nitrogen-rich gas enters the gas phase space of the aircraft oil tank (9) only from the third electromagnetic valve (8) and replaces and exhausts oxygen in the gas phase space to the external environment to reduce the oxygen concentration in the aircraft oil tank (9);
3) an oxygen concentration sensor (10) installed on the upper portion of an aircraft fuel tank (9) monitors the oxygen concentration of a fuel tank gas phase space in real time and transmits signals to a control system, and the control system adjusts the air entraining amount of an engine by adjusting the opening degree of a first electromagnetic valve (1) and a second electromagnetic valve (5), so that the flow of nitrogen-rich gas is adjusted, and the air entraining amount of the engine can be reduced while the oxygen concentration of the aircraft fuel tank (9) is reduced.
6. An operation method of an aircraft fuel tank inerting system according to claim 1, characterized in that the inlet of the first solenoid valve (1) is connected with an aircraft cabin (1001), a gas compressor (1002) is arranged between the aircraft cabin (1001) and the inlet of the first solenoid valve (1), and the operation method of the system is as follows:
air in a cabin is sucked by a compressor, enters a first electromagnetic valve (1), then impurities and moisture in the air are removed by a drying filter (2), then enters a hot side channel of a heat exchanger (3), the cold side of the heat exchanger (3) is used for stamping the air for cooling, the stamped air is discharged to the external environment after passing through the heat exchanger (3), the air is cooled, then the moisture in the air is removed by a water separator (4), the air enters a gas inlet of a hollow fiber membrane air separation assembly (6) after passing through a second electromagnetic valve (5), the air is separated by a hollow fiber membrane to form oxygen-enriched gas and nitrogen-enriched gas, the oxygen-enriched gas enters an aircraft cabin for pressurization and oxygen supply, and the nitrogen-enriched gas flows through a three-way valve (7;
1) the control system (101) closes the third electromagnetic valve (8) and opens the fourth electromagnetic valve (201) in the takeoff and climbing stage of the airplane, the nitrogen-rich gas only enters the fuel injector (202) to be mixed with the high-pressure fuel conveyed by the fuel pump (203) and is conveyed into the oil tank from the bottom of the airplane oil tank (9) so as to replace oxygen dissolved in the fuel, meanwhile, the nitrogen-rich gas enters the gas phase space of the airplane oil tank (9) and then replaces the gas phase space oxygen, and finally, the nitrogen-rich gas is discharged into the external environment so as to reduce the concentration of the oxygen in the oil tank;
2) when the aircraft is in a cruising or descending stage, the control system (101) opens the third electromagnetic valve (8), closes the fourth electromagnetic valve (201), and nitrogen-rich gas enters the gas phase space of the aircraft oil tank (9) only from the third electromagnetic valve (8) and replaces and exhausts oxygen in the gas phase space to the external environment to reduce the oxygen concentration in the aircraft oil tank (9);
3) an oxygen concentration sensor (10) installed on the upper portion of an aircraft fuel tank (9) monitors the oxygen concentration of a fuel tank gas phase space in real time and transmits signals to a control system, and the control system adjusts the air entraining amount of an engine by adjusting the opening degree of a first electromagnetic valve (1) and a second electromagnetic valve (5), so that the flow of nitrogen-rich gas is adjusted, and the air entraining amount of the engine can be reduced while the oxygen concentration of the aircraft fuel tank (9) is reduced.
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Cited By (5)
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| CN111672342A (en) * | 2020-05-14 | 2020-09-18 | 天津大学 | Fuel premixing device for preventing fuel oil thermal oxidation coking problem |
| CN111994289A (en) * | 2020-09-02 | 2020-11-27 | 重庆交通大学 | Aircraft fuel tank inerting system and inerting method |
| CN112298581A (en) * | 2020-10-30 | 2021-02-02 | 金陵科技学院 | Device and method for inerting oil tank of military unmanned aerial vehicle by using fuel oil backwashing |
| CN112937874A (en) * | 2021-02-04 | 2021-06-11 | 南京航空航天大学 | Can realize that cabin disperses ring accuse of formula oxygen suppliment and machine carries nitrogen generation coupled system |
| CN112937883A (en) * | 2021-04-09 | 2021-06-11 | 重庆交通大学绿色航空技术研究院 | Onboard fuel tank inerting system and onboard fuel tank inerting method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111672342A (en) * | 2020-05-14 | 2020-09-18 | 天津大学 | Fuel premixing device for preventing fuel oil thermal oxidation coking problem |
| CN111994289A (en) * | 2020-09-02 | 2020-11-27 | 重庆交通大学 | Aircraft fuel tank inerting system and inerting method |
| CN112298581A (en) * | 2020-10-30 | 2021-02-02 | 金陵科技学院 | Device and method for inerting oil tank of military unmanned aerial vehicle by using fuel oil backwashing |
| CN112937874A (en) * | 2021-02-04 | 2021-06-11 | 南京航空航天大学 | Can realize that cabin disperses ring accuse of formula oxygen suppliment and machine carries nitrogen generation coupled system |
| CN112937874B (en) * | 2021-02-04 | 2022-03-04 | 南京航空航天大学 | Can realize that cabin disperses ring accuse of formula oxygen suppliment and machine carries nitrogen generation coupled system |
| CN112937883A (en) * | 2021-04-09 | 2021-06-11 | 重庆交通大学绿色航空技术研究院 | Onboard fuel tank inerting system and onboard fuel tank inerting method |
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