CN109018387A - A kind of fuel tanker inerting unit and its method using high pressure water separation regenerative air cycle cooling system - Google Patents
A kind of fuel tanker inerting unit and its method using high pressure water separation regenerative air cycle cooling system Download PDFInfo
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- CN109018387A CN109018387A CN201811018318.7A CN201811018318A CN109018387A CN 109018387 A CN109018387 A CN 109018387A CN 201811018318 A CN201811018318 A CN 201811018318A CN 109018387 A CN109018387 A CN 109018387A
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- 239000000446 fuel Substances 0.000 title claims abstract description 71
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 69
- 238000001816 cooling Methods 0.000 title claims abstract description 24
- 238000000926 separation method Methods 0.000 title claims abstract description 22
- 230000001172 regenerating effect Effects 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title claims abstract description 14
- 239000002828 fuel tank Substances 0.000 claims abstract description 43
- 239000001301 oxygen Substances 0.000 claims abstract description 42
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 42
- 239000001257 hydrogen Substances 0.000 claims abstract description 23
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 23
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 20
- 239000011261 inert gas Substances 0.000 claims abstract description 19
- 238000006243 chemical reaction Methods 0.000 claims abstract description 9
- 239000007789 gas Substances 0.000 claims description 60
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 22
- 239000000295 fuel oil Substances 0.000 claims description 22
- 238000003860 storage Methods 0.000 claims description 17
- 239000003921 oil Substances 0.000 claims description 16
- 239000007788 liquid Substances 0.000 claims description 13
- 239000000203 mixture Substances 0.000 claims description 12
- 239000000945 filler Substances 0.000 claims description 11
- 230000005611 electricity Effects 0.000 claims description 3
- 230000008450 motivation Effects 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 230000036647 reaction Effects 0.000 abstract description 3
- 238000005265 energy consumption Methods 0.000 abstract 1
- 125000004435 hydrogen atom Chemical class [H]* 0.000 abstract 1
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 11
- 238000005516 engineering process Methods 0.000 description 6
- 229910052757 nitrogen Inorganic materials 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 239000002671 adjuvant Substances 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 239000012528 membrane Substances 0.000 description 2
- 238000012913 prioritisation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 229910001873 dinitrogen Inorganic materials 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010892 electric spark Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000012510 hollow fiber Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002000 scavenging effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fuel Cell (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention discloses a kind of fuel tanker inerting units and its method using high pressure water separation regenerative air cycle cooling system, hydrogen, which is carried, with aircraft using engine bleed or cockpit bleed reacts the oxygen in consumed cabin air by hydrogen-oxygen fuel cell to generate inert gas for reducing fuel tank gas-phase space oxygen concentration, fuel cell reaction generates a large amount of vapor simultaneously, water separation is carried out to the inert gas that reaction generates using three-wheel boosting high pressure water separation regenerative air cycle cooling system system, collecting the water that separation generates can be used for aircraft daily water consumption, while the electric energy that fuel cell reaction generates is used for aviation power supply equipment.Present system simple and stable can reduce energy consumption, reduce influence of the engine high pressure side bleed to engine performance, and can reduce the panelty of aircraft.
Description
Technical field
The present invention relates to fire-proof and explosion-proof technical field more particularly to a kind of fuel tanker inerting units using high pressure water separation regenerative air cycle cooling system
And its method.
Background technique
Fuel tanker gas-phase space oxygen concentration be higher than the flammable oxygen concentration of the limit, external incendiary source for example thunder and lightning, electrostatic,
In the presence of artillery fire strike etc., fuel vapor mixes with air object and combustion explosion easily occurs, and leads to fatal crass, causes greatly
Security of the lives and property hidden danger.The one frame TWA800 airliner on July 17th, 1996, Trans-World Airlines is international from New York Kennedy
Airport Paris Fei Zhu Charles de Gaulle Airport, which is taken off, explodes soon convenient for Long Island overhead, and 230 passenger and crews on machine is caused to suffer from
It is difficult.Investigation discovery accident is to cause short circuit to generate electric spark by electric wire broken on aircraft to enter fuel tank, causes Center Wing Tank
Explosion on fire.This time after accident, fuel tank gas-phase space combustibility is reduced, protection fuel tanker causes safely the wide of researcher
General concern.Three factors that fire occurs for fuel tank have incendiary source, combustible and combustion adjuvant.Since incendiary source is uncontrollable, fuel oil
Volatility cause gas-phase space to there is fuel vapor always, therefore preventing the important measures that fuel tanker fire occurs is to reduce
The presence of combustion adjuvant oxygen.Studies have shown that when fuel tanker gas-phase space oxygen concentration is lower than 12%(civil aircraft) and 9%(army
With aircraft) when the generation of fire can be effectively prevented.Federal Aviation management board (FAA) is by a large amount of theoretical and experimental studies
Show that fuel tank inerting technology is a kind of cost-effective method for reducing fuel tank gas-phase space oxygen concentration.
Fuel tank inerting technology refers to that (nitrogen gas concn can be high using inert gas such as nitrogen, carbon dioxide or nitrogen-rich gas
98%) etc. reach reduction gas-phase space up to the oxygen that fuel tank gas-phase space converts out gas-phase space is filled with to reduce oxygen concentration
Combustibility protects the purpose of fuel tank safety.The fuel tank inerting technology for developing comparative maturity at present is airborne nitrogen inerting technology processed, benefit
Nitrogen-rich gas is produced by hollow-fibre membrane with high-pressure engine bleed, inerting is carried out to fuel tank, the technology is in F-15, F-22, F-
35, the military secrets such as C-17 and Boeing 747, Airbus A320 etc. are widely used.But from current domestic and international application status
From the point of view of, the technology there are Middle hollow fiber membrane low efficiency, easily blocking, film inlet pressure is high, engine bleed amount is big the problems such as.
And with the development of airmanship, aircraft manufacturing develops towards larger capacity, safer direction, while aircraft electricity
To aviation power supply, more stringent requirements are proposed with water supply for the increase of sub- equipment and passenger.
Summary of the invention
The technical problem to be solved by the present invention is to provide a kind of using high for defect involved in background technique
The fuel tanker inerting unit and its method for pressing water removal, reduce the panelty of the aircraft during fuel tank inerting, improve energy
Utilization rate guarantees the flight safety of aircraft.
The present invention uses following technical scheme to solve above-mentioned technical problem:
A kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system, including hydrogen storage bottle, First Heat Exchanger, hydrogen-oxygen fuel cell,
One compressor, the second heat exchanger, fan, separator, turbo-expander, water tank, check valve and fuel tank；
The hydrogen storage bottle is exported equipped with high pressure hydrogen；Hydrogen-oxygen fuel cell is equipped with anodic gas entrance, cathode gas inlet, electric energy
Output port and offgas outlet；Separator is equipped with gas access, the gentle body outlet of liquid water out；Fuel tank is equipped with inert gas
Entrance and gas vent；Water tank is equipped with entrance and exit；
The cathode gas that the entrance of the First Heat Exchanger hot-side channel introduces engine bleed, outlet and hydrogen-oxygen fuel cell enters
Mouth is connected；
The high pressure hydrogen outlet of the anodic gas entrance of the hydrogen-oxygen fuel cell and hydrogen storage bottle is connected, power output port and outside
The connection of portion's aircraft electrical equipment；
The offgas outlet of the hydrogen-oxygen fuel cell, the first aerostatic press, the hot-side channel of the second heat exchanger, separator gas
Entrance is sequentially connected；
The gas vent of the separator, turbo-expander, check valve, fuel tank inert gas entrance be sequentially connected；
The liquid water out of the separator is connected with the entrance of water tank, the outlet of water tank and external water equipment phase
Even；
The shaft of the turbo-expander is coaxially connected with the shaft of first compressor, the shaft of fan respectively, wherein institute
Turbo-expander is stated for cooling down to the gas being discharged in separator, while supplying power to the first compressor and wind
Fan drives the first compressor and fan to work；
The entrance of the second heat exchanger cold side channel connects ram-air, the outlet of the second heat exchanger cold side channel, fan, first
The entrance of heat exchanger cold side channel is connected；
The outlet of the First Heat Exchanger cold side channel, the gas vent of fuel tank connect atmosphere outside.
It further include the as a kind of further prioritization scheme of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system of the present invention
Two compressors and the first motor；
The air inlet joint chair cabin bleed of second compressor, gas outlet and the First Heat Exchanger hot-side channel entrance phase
Even；
The shaft of first motor and the shaft of second compressor are coaxially connected, and are used to provide power and calm the anger to second
Machine drives its work.
It further include the as a kind of further prioritization scheme of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system of the present invention
Two motor, fuel oil injector and oil pump；
The shaft of second motor and the shaft of first compressor are coaxially connected, for further carrying power to institute
It states the first compressor, drive its work；
The fuel oil injector is equipped with gas access, fuel filler and gas mixture outlet；The fuel tank is also set in its bottom
There are gas mixture entrance and fuel outlet；Oil pump is equipped with fuel filler and fuel outlet；
The fuel filler of the oil pump is connected with the fuel outlet of the fuel tank, the fuel outlet of oil pump and the fuel oil injector
Fuel filler connection；
The gas access of the fuel oil injector is connected with the gas vent of the check valve, the gas mixture of fuel oil injector
Outlet is connected with the gas mixture entrance of the fuel tank；
The inert gas entrance of the fuel tank is closed.
The invention also discloses a kind of working methods of fuel tanker inerting unit based on this using high pressure water separation regenerative air cycle cooling system, include
Following procedure:
Hydrogen in hydrogen storage bottle and the engine bleed after First Heat Exchanger cools down are reacted in hydrogen-oxygen fuel cell, consumption
Oxygen generates water simultaneously, reacts the electric energy input external power supply equipment of generation, and the tail gas of reaction is changed by the first compressor, second
Hot device and separator, the liquid water and dry inert gas isolated, wherein liquid water supplies after water tank stores
To external water equipment, dry inert gas, which enters fuel tank gas-phase space by check valve after turbo-expander cools down, to be carried out
Mixing is to reduce fuel tank gas-phase space oxygen concentration.
The invention adopts the above technical scheme compared with prior art, has following technical effect that
The present invention is produced electricl energy by hydrogen-oxygen fuel cell reaction using engine bleed or cockpit bleed and is increased day by day with water with providing
Long electricity consumption and water consumption.Vapor and rich nitrogen tail gas are generated by hydrogen-oxygen fuel cell real time reaction and are boosted using three-wheel high
It presses water scavenging system progress water separation to carry out liquid water storage to utilize, reduces the initial moisture storage capacity of aircraft, alleviate and take off always
Quality reduces aircraft panelty.The dry inert gas after high pressure water separation regenerative air cycle cooling system, which enters fuel tank, simultaneously reduces gas-phase space
Oxygen concentration guarantees fuel tank safety.This system can reduce the bleed of engine high pressure side from engine low-pressure side or cockpit bleed
Influence to engine performance, while electric energy is provided for aircraft and water reduces aircraft panelty, improve capacity usage ratio.
Detailed description of the invention
Fig. 1 is the system diagram of the fuel tanker inerting using high pressure water separation regenerative air cycle cooling system using engine bleed of embodiment 1；
Fig. 2 is the system diagram of the fuel tanker inerting using high pressure water separation regenerative air cycle cooling system using cockpit bleed of embodiment 2；
Fig. 3 is the system diagram that inerting is washed using the fuel tanker using high pressure water separation regenerative air cycle cooling system of cockpit bleed of embodiment 3.
In figure, 1, hydrogen storage bottle, 2, First Heat Exchanger, 3, hydrogen-oxygen fuel cell, 4, electrical equipment, the 5, first compressor, 6,
Second heat exchanger, 7, fan, 8, separator, 9, turbo-expander, 10, water tank, 11, check valve, 12, water equipment, 13,
Fuel tank, the 101, second compressor, the 102, first motor, the 201, second motor, 202, fuel oil injector, 203, oil pump.
Specific embodiment
Technical solution of the present invention is described in further detail with reference to the accompanying drawing:
The present invention can be embodied in many different forms, and should not be assumed that be limited to the embodiments described herein.On the contrary, providing
These embodiments are thoroughly and complete to make the disclosure, and will give full expression to the scope of the present invention to those skilled in the art.
In the accompanying drawings, for the sake of clarity it is exaggerated component.
1), embodiment 1:
Fig. 1 including hydrogen storage bottle 1, first is changed using the system of the fuel tanker inerting using high pressure water separation regenerative air cycle cooling system of engine bleed
Hot device 2, hydrogen-oxygen fuel cell 3, the first compressor 5, the second heat exchanger 6, fan 7, separator 8, turbo-expander 9, water storage
Case 10, check valve 11 and fuel tank 13；Hydrogen storage bottle 1 is exported equipped with high pressure hydrogen；Hydrogen-oxygen fuel cell 3 be equipped with anodic gas entrance,
Cathode gas inlet, power output port and offgas outlet；Separator 8 is equipped with gas access, the gentle body of liquid water out goes out
Mouthful；Fuel tank 13 is equipped with inert gas entrance and gas vent；Water tank 10 is equipped with entrance and exit.
The entrance of 2 hot-side channel of First Heat Exchanger introduces the cathode gas of engine bleed, outlet and hydrogen-oxygen fuel cell 3
Entrance is connected；The high pressure hydrogen outlet of the anodic gas entrance of hydrogen-oxygen fuel cell 3 and hydrogen storage bottle 1 is connected, power output port
It is connected with external aircraft electrical equipment 4；The hot side of the offgas outlet of hydrogen-oxygen fuel cell 3, the first aerostatic press 5, the second heat exchanger 6
Channel, separator 8 gas access be sequentially connected；Gas vent, turbo-expander 9, check valve 11, the oil of separator 8
The inert gas entrance of case 13 is sequentially connected；The liquid water out of separator 8 is connected with the entrance of water tank 10, water tank 10
Outlet be connected with external water equipment 12.
The shaft of turbo-expander 9 is coaxially connected with the shaft of the first compressor 5, the shaft of fan 7 respectively, wherein whirlpool
Wheel expanding machine 9 supplies power to the first compressor 5 and fan for cooling down to the gas being discharged in separator 8
7, the first compressor 5 and fan 7 is driven to work.
The entrance of second heat exchanger, 6 cold side channel connects ram-air, the outlet of 6 cold side channel of the second heat exchanger, fan 7,
The entrance of 2 cold side channel of First Heat Exchanger is connected；The outlet of 2 cold side channel of First Heat Exchanger, the gas vent of fuel tank 13 connect
Atmosphere outside.
The invention also discloses a kind of working methods of fuel tanker inerting unit based on this using high pressure water separation regenerative air cycle cooling system, specifically
Process is as follows:
1 li of hydrogen and the engine bleed after the cooling of First Heat Exchanger 2 are reacted in hydrogen-oxygen fuel cell 3 hydrogen storage bottle,
Consumption oxygen generates water simultaneously, reacts the electric energy input external power supply equipment 4 of generation, the tail gas of reaction by the first compressor 5,
Second heat exchanger 6 and separator 8, the liquid water and dry inert gas isolated, wherein liquid water passes through water tank
External water equipment 12 is supplied after 10 storages, dry inert gas enters after the cooling of turbo-expander 9 by check valve 11
13 gas-phase space of fuel tank is mixed to reduce fuel tank gas-phase space oxygen concentration.
2), embodiment 2:
As shown in Fig. 2, on the basis of embodiment 1 further including the second compressor 101 and the first motor 102；Second compressor
101 air inlet joint chair cabin bleed, gas outlet are connected with the entrance of 2 hot-side channel of First Heat Exchanger；First motor 102 turns
The shaft of axis and the second compressor 101 is coaxially connected, and is used to provide power to the second compressor, drives its work.
The present embodiment is difference from example 1 is that using the second compressor 101 and the first motor 102 to cockpit
Bleed is compressed to replace engine bleed, it is possible to reduce influence of the engine bleed to engine performance reduces aircraft generation
Repay loss.
3, embodiment 3
As shown in figure 3, further including the second motor 201, fuel oil injector 202 and oil pump 203 on the basis of embodiment 2；The
The shaft of two motor 201 and the shaft of the first compressor 5 are coaxially connected, for further carry power to the first compressor 5,
Drive its work；Fuel oil injector 202 is equipped with gas access, fuel filler and gas mixture outlet；Fuel tank 13 is in its bottom
It is additionally provided with gas mixture entrance and fuel outlet；Oil pump 203 is equipped with fuel filler and fuel outlet；The fuel oil of oil pump 203 enters
Mouth is connected with the fuel outlet of fuel tank 13, and the fuel outlet of oil pump 203 is connected with the fuel filler of fuel oil injector 202；Fuel oil
The gas access of injector 202 is connected with the gas vent of check valve 11, gas mixture outlet and the oil of fuel oil injector 202
The gas mixture entrance of case 13 is connected；The inert gas entrance of fuel tank 13 is closed.
The present embodiment and embodiment 1 and embodiment 2 are the difference is that give the first compressor using the second motor 201
Water separative efficiency can be improved in 5 energy supplies, while being washed using fuel oil injector 202 and oil pump 203 to fuel oil and can reduce fuel oil
Dissolved oxygen and gas-phase space oxygen concentration reduce influence of the fuel oil dissolved oxygen to gas-phase space oxygen concentration.
Those skilled in the art can understand that unless otherwise defined, all terms used herein (including skill
Art term and scientific term) there is meaning identical with the general understanding of those of ordinary skill in fields of the present invention.Also
It should be understood that those terms such as defined in the general dictionary should be understood that have in the context of the prior art
The consistent meaning of meaning will not be explained in an idealized or overly formal meaning and unless defined as here.
Above-described specific embodiment has carried out further the purpose of the present invention, technical scheme and beneficial effects
It is described in detail, it should be understood that being not limited to this hair the foregoing is merely a specific embodiment of the invention
Bright, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in the present invention
Protection scope within.
Claims (4)
1. a kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system, which is characterized in that including hydrogen storage bottle (1), First Heat Exchanger
(2), hydrogen-oxygen fuel cell (3), the first compressor (5), the second heat exchanger (6), fan (7), separator (8), turbine expansion
Machine (9), water tank (10), check valve (11) and fuel tank (13)；
The hydrogen storage bottle (1) exports equipped with high pressure hydrogen；Hydrogen-oxygen fuel cell (3) is equipped with anodic gas entrance, cathode gas enters
Mouth, power output port and offgas outlet；Separator (8) is equipped with gas access, the gentle body outlet of liquid water out；Fuel tank
(13) inert gas entrance and gas vent are equipped with；Water tank (10) is equipped with entrance and exit；
The entrance of First Heat Exchanger (2) hot-side channel introduces the cathode of engine bleed, outlet and hydrogen-oxygen fuel cell (3)
Gas access is connected；
The high pressure hydrogen outlet of the anodic gas entrance of the hydrogen-oxygen fuel cell (3) and hydrogen storage bottle (1) is connected, electric energy output end
Mouth and external aircraft electrical equipment (4) connect；
The offgas outlet of the hydrogen-oxygen fuel cell (3), the first aerostatic press (5), the second heat exchanger (6) hot-side channel, moisture
Gas access from device (8) is sequentially connected；
The gas vent of the separator (8), turbo-expander (9), check valve (11), fuel tank (13) inert gas entrance
It is sequentially connected；
The liquid water out of the separator (8) is connected with the entrance of water tank (10), the outlet and outside of water tank (10)
Water equipment (12) is connected；
The shaft of the turbo-expander (9) is coaxially solid with the shaft of first compressor (5), the shaft of fan (7) respectively
Even, wherein the turbo-expander (9) is used to cool down to the gas being discharged in separator (8), supplies power to simultaneously
First compressor (5) and fan (7) drive the first compressor (5) and fan (7) to work；
The entrance of second heat exchanger (6) cold side channel connects ram-air, the outlet of the second heat exchanger (6) cold side channel, wind
Fan (7), the entrance of First Heat Exchanger (2) cold side channel is connected；
The outlet of First Heat Exchanger (2) cold side channel, the gas vent of fuel tank (13) connect atmosphere outside.
2. using the fuel tanker inerting unit of high pressure water separation regenerative air cycle cooling system as described in claim 1, which is characterized in that further include the second pressure
Mechanism of qi (101) and the first motor (102)；
The air inlet joint chair cabin bleed of second compressor (101), gas outlet and the First Heat Exchanger (2) hot-side channel
Entrance is connected；
The shaft of first motor (102) and the shaft of second compressor (101) are coaxially connected, and are used to provide power
To the second compressor, drive its work.
3. using the fuel tanker inerting unit of high pressure water separation regenerative air cycle cooling system as claimed in claim 2, which is characterized in that further include the second electricity
Motivation (201), fuel oil injector (202) and oil pump (203)；
The shaft of second motor (201) and the shaft of first compressor (5) are coaxially connected, for further carrying
Power gives first compressor (5), drives its work；
The fuel oil injector (202) is equipped with gas access, fuel filler and gas mixture outlet；The fuel tank (13) is at it
Bottom is additionally provided with gas mixture entrance and fuel outlet；Oil pump (203) is equipped with fuel filler and fuel outlet；
The fuel filler of the oil pump (203) is connected with the fuel outlet of the fuel tank (13), the fuel outlet of oil pump (203) and
The fuel filler of the fuel oil injector (202) connects；
The gas access of the fuel oil injector (202) is connected with the gas vent of the check valve (11), fuel oil injector
(202) gas mixture outlet is connected with the gas mixture entrance of the fuel tank (13)；
The inert gas entrance of the fuel tank (13) is closed.
4. the working method based on the fuel tanker inerting unit described in claim 1 using high pressure water separation regenerative air cycle cooling system, which is characterized in that
Include following procedure:
(1) inner hydrogen and the engine bleed after First Heat Exchanger (2) cooling are in hydrogen-oxygen fuel cell (3) in hydrogen storage bottle
Reaction, consumption oxygen generate water simultaneously, react electric energy input external power supply equipment (4) of generation, and the tail gas of reaction passes through first
Compressor (5), the second heat exchanger (6) and separator (8), the liquid water and dry inert gas isolated, wherein liquid
State water supplies external water equipment (12) after water tank (10) store, and dry inert gas is dropped by turbo-expander (9)
Enter fuel tank (13) gas-phase space by check valve (11) after temperature to be mixed to reduce fuel tank gas-phase space oxygen concentration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811018318.7A CN109018387B (en) | 2018-09-03 | 2018-09-03 | Aircraft fuel tank inerting device adopting high-pressure water removal and method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811018318.7A CN109018387B (en) | 2018-09-03 | 2018-09-03 | Aircraft fuel tank inerting device adopting high-pressure water removal and method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109018387A true CN109018387A (en) | 2018-12-18 |
| CN109018387B CN109018387B (en) | 2023-05-09 |
Family
ID=64622784
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811018318.7A Active 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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| CN (1) | CN109018387B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109888333A (en) * | 2019-04-24 | 2019-06-14 | 吉林大学 | A kind of hydrogen fuel cell cold start and emergency starting device based on injector |
| CN110963059A (en) * | 2019-11-27 | 2020-04-07 | 南京航空航天大学 | Cabin pressurization and oxygenation device and method based on hollow fiber membrane airborne nitrogen production technology |
| CN111071468A (en) * | 2020-01-06 | 2020-04-28 | 南京航空航天大学 | Energy recovery type fuel tank inerting system configuration and working method thereof |
| CN111071467A (en) * | 2020-01-06 | 2020-04-28 | 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 |
| CN111086645A (en) * | 2020-01-06 | 2020-05-01 | 南京航空航天大学 | Device for reducing combustibility of oil tank by using ring control cold system and working method |
| CN111794864A (en) * | 2019-04-05 | 2020-10-20 | 通用电气公司 | Pump mixer separator unit |
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