CN208036637U - Aircraft fuel tank oxygen concentration control device based on low temperature plasma - Google Patents
Aircraft fuel tank oxygen concentration control device based on low temperature plasma Download PDFInfo
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- CN208036637U CN208036637U CN201820087828.9U CN201820087828U CN208036637U CN 208036637 U CN208036637 U CN 208036637U CN 201820087828 U CN201820087828 U CN 201820087828U CN 208036637 U CN208036637 U CN 208036637U
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- oxygen concentration
- fuel tank
- side channel
- sensor
- entrance
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- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 title claims abstract description 55
- 239000001301 oxygen Substances 0.000 title claims abstract description 55
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 55
- 239000002828 fuel tank Substances 0.000 title claims abstract description 42
- 239000007789 gas Substances 0.000 claims abstract description 30
- 238000001816 cooling Methods 0.000 claims abstract description 23
- 239000004215 Carbon black (E152) Substances 0.000 claims abstract description 21
- 229930195733 hydrocarbon Natural products 0.000 claims abstract description 21
- 150000002430 hydrocarbons Chemical class 0.000 claims abstract description 21
- 238000006243 chemical reaction Methods 0.000 claims abstract description 13
- 229910001868 water Inorganic materials 0.000 claims description 25
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 21
- 239000006096 absorbing agent Substances 0.000 claims description 14
- 239000007788 liquid Substances 0.000 claims description 8
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000000523 sample Substances 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims description 3
- -1 carbon Hydrogen compound Chemical class 0.000 claims description 2
- 239000001257 hydrogen Substances 0.000 claims 1
- 229910052739 hydrogen Inorganic materials 0.000 claims 1
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 abstract description 15
- 229910052757 nitrogen Inorganic materials 0.000 abstract description 7
- 239000000446 fuel Substances 0.000 abstract description 4
- 239000000295 fuel oil Substances 0.000 abstract description 3
- 238000001035 drying Methods 0.000 abstract description 2
- 230000006978 adaptation Effects 0.000 abstract 1
- 210000002381 plasma Anatomy 0.000 description 19
- 238000005516 engineering process Methods 0.000 description 12
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 7
- 229910002092 carbon dioxide Inorganic materials 0.000 description 6
- 238000004880 explosion Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000001569 carbon dioxide Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 239000012528 membrane Substances 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000010494 dissociation reaction Methods 0.000 description 2
- 230000005593 dissociations Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 239000011261 inert gas Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000012495 reaction gas Substances 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 239000012855 volatile organic compound Substances 0.000 description 2
- 206010000369 Accident Diseases 0.000 description 1
- 229920004449 Halon® Polymers 0.000 description 1
- CBENFWSGALASAD-UHFFFAOYSA-N Ozone Chemical compound [O-][O+]=O CBENFWSGALASAD-UHFFFAOYSA-N 0.000 description 1
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000036760 body temperature Effects 0.000 description 1
- 238000006555 catalytic reaction Methods 0.000 description 1
- 235000019628 coolness Nutrition 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000013480 data collection Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- PXBRQCKWGAHEHS-UHFFFAOYSA-N dichlorodifluoromethane Chemical compound FC(F)(Cl)Cl PXBRQCKWGAHEHS-UHFFFAOYSA-N 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000007792 gaseous phase Substances 0.000 description 1
- 230000005283 ground state Effects 0.000 description 1
- JEGUKCSWCFPDGT-UHFFFAOYSA-N h2o hydrate Chemical group O.O JEGUKCSWCFPDGT-UHFFFAOYSA-N 0.000 description 1
- 210000004209 hair Anatomy 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 230000010534 mechanism of action Effects 0.000 description 1
- VUZPPFZMUPKLLV-UHFFFAOYSA-N methane;hydrate Chemical compound C.O VUZPPFZMUPKLLV-UHFFFAOYSA-N 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- DOTMOQHOJINYBL-UHFFFAOYSA-N molecular nitrogen;molecular oxygen Chemical compound N#N.O=O DOTMOQHOJINYBL-UHFFFAOYSA-N 0.000 description 1
- JCXJVPUVTGWSNB-UHFFFAOYSA-N nitrogen dioxide Inorganic materials O=[N]=O JCXJVPUVTGWSNB-UHFFFAOYSA-N 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000012071 phase Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Abstract
The utility model discloses a kind of aircraft fuel tank oxygen concentration control device based on low temperature plasma, belongs to air line technical field, concrete principle is：The mixed gas of aircraft fuel oil upper box part is extracted out by wind turbine, is adjusted through excess temperature, is passed through in reaction of low temperature plasma device, and hydrocarbon therein is excited by low-temperature plasma, dissociated, ionization ultimately generates harmless CO2And H2O.Nitrogen-rich gas is obtained after cooling drying, fuel tank is flowed back to and carries out gas-phase space oxygen concentration control.System has many advantages, such as that simple in structure, adaptation condition range is wide, control efficiency is high, conforms better to the developing direction of Fuel On Board case oxygen concentration control system.
Description
Technical field
The utility model is related to air line technical fields, are related to airborne tank oxygen concentration control system more particularly to one
Aircraft fuel tank oxygen concentration control device of the kind based on low temperature plasma.
Background technology
The safety problem of modern aircraft is all the time by the extensive concern of society, and fuel system burning, explosion are to draw
One of the main reason for playing aviation accident.There is data to suggest that in Vietnam War, United States Air Force is damaged by ground fire attack
Thousands of airplanes are lost, wherein since fuel tanker explosion on fire causes the ratio of fatal crass to be as high as 50%.Cabin security study
Technology group（cabin safety research technical group,GSRTG）To 1966 to 2009 whole world
3726 civil aircraft accident statistics are the results show that share 370 accidents related with fuel tank combustion explosion.It can be seen that, it is necessary to it uses
Effective measures prevent the aircraft fuel tank from firing.
Aircraft fuel tank upper space is full of flammable gas mixture, and inflammable, explosive feature seriously threatens aircraft
Safety, it is necessary to adopt an effective measure to reduce the probability of its combustion, outburst life, and reduce its extent of injury.System is protected in fuel tank
In, fuel tank explosion on fire can be prevented by reducing fuel tank upper gaseous phase space oxygen concentration, ensure passenger and aircraft safety.Reduce fuel oil
Case oxygen concentration can be used the gases such as inert gas such as nitrogen and carbon dioxide and carry out fuel tank inerting, and so that its oxygen content is reduced to can
Fire the limit or less.
Common aircraft fuel tank oxygen concentration control technology mainly have liquid nitrogen inerting technology, 1301 inerting technologies of Halon,
Sieve technology, membrane separation technique etc..Wherein hollow-fibre membrane produces the airborne nitrogen inerting technology processed of nitrogen-rich gas（On-Board
Inert Gas Generator System, OBIGGS）It is that most economical, practical fuel tanker fires suppression technology.But
OBIGGS technologies such as detach that membrane efficiency is low to lead to that aircraft panelty is big, seperation film entrance demand pressure there are still many problems
Height causes not using on many types（Such as helicopter）, tiny film wire and infiltration aperture gradually block and air source in ozone
Cause causes fuel-steam to leak when serious film properties decaying, nitrogen-rich gas filling fuel tank pollutes environment etc..
In recent years, non-thermal plasma trap is quickly grown in processing exhaust gas and rubbish etc., plasma and VOCs's
The mechanism of action mainly has two aspects：First, the high energy electron of tens thousand of degree is directly and gas molecule（Atom）Inelastic collision occurs,
Convert the energy into ground state molecule（Atom）Interior energy, make its excitation, dissociation, ionization ultimately generate harmless CO2 And H2O；
Second is that the O in high energy electron energized gas2、N2、H2O equimoleculars have Strong oxdiative ability O, OH, O to generate3, etc. from
By base or active particle, they destroy the chemical bonds such as C-H, C=C or C-C, make the hairs such as H, C1, F in VOCs molecules
Raw displacement reaction and decomposition oxidation, ultimately generate innocuous substance CO2And H2O.The utility model can be incited somebody to action using low-temperature plasma
The fuel-steam catalysis of fuel oil upper box part generates CO2And H2O.Reaction gas is nitrogen-rich gas after being dried, and flows back to fuel tank progress
Inerting controls the oxygen concentration of fuel tank gas-phase space.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of base for defect involved in background technology
In the aircraft fuel tank oxygen concentration control device of low temperature plasma.
The utility model uses following technical scheme to solve above-mentioned technical problem：
Aircraft fuel tank oxygen concentration control device based on low temperature plasma, including fuel tank, the first spark arrester, wind
Machine, the first electric control valve, preheater, electric heater, the first temperature sensor, the first oxygen concentration sensor, the first hydrocarbonization
Object sensor, reaction of low temperature plasma device, the second hydrocarbon sensor, the second oxygen concentration sensor, aqueous slkali is closed to inhale
Receive device, primary cooler, primary separator, secondary cooling device, secondary separator, water jet, second temperature sensor, the
Two electric control valves, one way stop peturn valve, the second spark arrester, third oxygen concentration sensor and automatic controller；
The fuel tank includes gas vent and gas access；The water jet goes out comprising first to third entrance and one
Mouthful；The automatic controller includes current input terminal and current output terminal；
The gas vent of the fuel tank, the first spark arrester, wind turbine entrance be sequentially connected by pipeline；
Entrance of the outlet of the wind turbine respectively with the outlet of first electric control valve, preheater cold side channel passes through
Pipeline is connected；
The entrance of first electric control valve is connected by pipeline with external ram-air；
The outlet of the preheater cold side channel, electric heater, the first temperature sensor, the first oxygen concentration sensor,
One hydrocarbon sensor, reaction of low temperature plasma device, the second hydrocarbon sensor, the second oxygen concentration sensor,
The hot-side channel of aqueous slkali absorber, the hot-side channel of primary cooler, primary separator, the hot side of secondary cooling device are logical
The gas in road, secondary separator, second temperature sensor, the second electric control valve, one way stop peturn valve, the second spark arrester, fuel tank
Body entrance is sequentially connected by pipeline；
The probe of third oxygen concentration sensor stretches into the fuel tank, the concentration for incuding oxygen in the fuel tank, and
Pass it to the automatic controller；
The entrance of the aqueous slkali absorber cold side channel, the entrance of primary cooler cold side channel, the water jet
Third entrance is connected by pipeline with outside cooling with ram-air；
The outlet of the aqueous slkali absorber cold side channel, the outlet of primary cooler cold side channel respectively by pipeline and
The entrance of the preheater cold side channel connects；
The outlet of the preheater cold side channel is connected by pipeline with the external world；
The first entrance of the water jet is connected with the liquid outlet of the primary separator by pipeline, water jet
Second entrance is connected with the liquid outlet of secondary separator by pipeline, the outlet of water jet and the secondary cooling device cold side
The entrance in channel is connected by pipeline；
The outlet of the secondary cooling device cold side channel is connected by pipeline with the external world；
The current input terminal of the automatic controller respectively with the third oxygen concentration sensor, the first temperature sensor,
First oxygen concentration sensor, the first hydrocarbon sensor, the second hydrocarbon sensor, the second oxygen concentration sensor,
Second temperature sensor is electrically connected, current output terminal respectively with first electric control valve, the second electric control valve, wind
Mechanical, electrical heater, reaction of low temperature plasma device are electrically connected.
The utility model has the following technical effects using above technical scheme is compared with the prior art：
1, technology is high-end, concise in technology：It after booting, i.e., voluntarily operates, is limited by operating mode considerably less；
2, energy saving：Without mechanical equipment, air drag is small, and power consumption is about 0.003kw/m3 exhaust gas；
3, it is wide to adapt to condition range：Equipment starts, stopping is very rapid, with with opening, is not influenced by temperature.?
It 250 DEG C or less and can run well in mist state work condition environment.It still can normally be transported in -50 DEG C to+50 DEG C of environment temperatures
Turn；
4, simple in structure：Electricity consumption is only needed, operation is extremely simple, and no mechanical equipment, failure rate is low, and repair is easy.
Description of the drawings
Fig. 1 is the aircraft fuel tank oxygen concentration control device schematic diagram based on low temperature plasma.
In figure, 1- fuel tanks, the first spark arresters of 2-, 3- wind turbines, the first electric control valves of 4-, 5- preheaters, 6- electric heaters,
The first temperature sensors of 7-, the first oxygen concentration sensors of 8-, the first hydrocarbon sensors of 9-, 10- low temperature plasmas are anti-
Answer device, the second hydrocarbon sensors of 11-, the second oxygen concentration sensors of 12-, 13- aqueous slkali absorbers, 14- primary coolings
Device, 15- primary separators, 16- secondary cooling devices, 17- grade separator, 18- water jets, 19- second temperature sensors,
The second electric control valves of 20-, 21- one way stop peturn valves, the second spark arresters of 22-, 23- third oxygen concentration sensors, 24- are automatically controlled
Device.
Specific implementation mode
The technical solution of the utility model is described in further detail below in conjunction with the accompanying drawings：
The utility model can be embodied in many different forms, and should not be assumed that be limited to the embodiments described herein.
On the contrary, thesing embodiments are provided so that the disclosure is thorough and complete, and this reality will be given full expression to those skilled in the art
With novel range.In the accompanying drawings, for the sake of clarity it is exaggerated component.
It will be appreciated that though term first, second, third, etc., which may be used herein, describes each element, component and/or portion
Point, but these elements, component and/or part should not be limited by these terms.These terms be used only for by element, component and/or
Part mutually distinguishes.Therefore, first element discussed below, component and/or part are imparted knowledge to students without departing substantially from the utility model
Under the premise of can become second element, component or part.
As shown in Figure 1, the aircraft fuel tank oxygen concentration control device based on low temperature plasma.The outlet of fuel tank 1 passes through
Pipeline is connected with the first spark arrester 2,3 entrance of wind turbine in turn；The ram-air passes through 4 entrance of pipeline and the first electric control valve
Connection；The wind turbine 3 export with first electric control valve 4 outlet by pipeline simultaneously with 5 cold side channel entrance of preheater
Connection；The outlet of 5 cold side channel of the preheater is connected with electrical heating 6, the first temperature sensor 7, the first oxygen in turn by pipeline
Concentration sensor 8, the first hydrocarbon sensor 9, reaction of low temperature plasma device 10, the second hydrocarbon sensor
11, the second oxygen concentration sensor 12,13 hot-side channel entrance of aqueous slkali absorber, 13 hot-side channel of aqueous slkali absorber go out
Mouthful by pipeline be connected in turn 14 hot-side channel of primary cooler, primary separator 15,16 hot-side channel of secondary cooling device,
Secondary separator 17, second temperature sensor 19, the second electric control valve 20, one way stop peturn valve 21, the second spark arrester 22, institute
State 1 entrance of fuel tank；Third oxygen concentration sensor 23 is connect by popping one's head in the fuel tank 1.The cooling is shared with ram-air
Three strands, one is connect by pipeline with 13 cold side channel entrance of the aqueous slkali absorber；Secondly stock by pipeline with it is described
14 cold side channel entrance of primary cooler connects；13 cold side channel of the aqueous slkali absorber outlet and the primary cooler 14
Cold side channel outlet is connect with 5 cold side channel entrance of the preheater simultaneously by pipeline；5 cold side channel of the preheater exports
It is drained into outside machine by pipeline.For water jet 18 there are three entrance and one outlet, 15 liquid outlet of the primary separator is logical
Piping is connect with 18 one entrance of the water jet；Secondary 17 liquid outlet of separator passes through pipeline and the water spray
Device 18 is secondly entrance connects；It is described it is cooling with its three strands of ram-air by pipeline with the water jet 18 thirdly entrance is connect；
The outlet of the water jet 18 is connect by pipeline with 16 cold side channel entrance of the secondary cooling device；The secondary cooling device 16 is cold
Wing passage outlet is drained by pipeline outside machine.
The third oxygen concentration sensor 23, the first temperature sensor 7, the first oxygen concentration sensor 8, the first nytron
Object sensor 9, the second oxygen concentration sensor 12, second temperature sensor 19, passes through cable at second hydrocarbon sensor 11
Parallel connection is simultaneously connect with 24 current input terminal of automatic controller；24 current output terminal of the automatic controller by cable respectively with institute
State the electric current of the first electric control valve 4, the second electric control valve 20, wind turbine 3, electric heater 6, reaction of low temperature plasma device 10
Input terminal connects.
Specifically, the aircraft fuel tank oxygen concentration control device course of work based on low temperature plasma is as follows：
1）Inerting process：The gas on 1 top of the fuel tank flows through first resistance under the swabbing action of the wind turbine 3
Firearm 2, the wind turbine 3；It is mixed with the ram-air for flowing through first electric control valve 4；Mixed gas is in the preheater 5
In be preheated；Then it is further heated in the electric heater 6 to reaction required temperature；High-temperature gas is followed by described
First temperature sensor 7, the first oxygen concentration sensor 8, the first hydrocarbon sensor 9；It is anti-in the low temperature plasma
It answers in device 10 by low-temperature plasma excitation, dissociation, ionization；Gas after reaction is mainly nitrogen, carbon dioxide, water and nitrogen oxygen
Compound；High temperature and humidity gas flows successively through second hydrocarbon sensor 11, the second oxygen concentration sensor 12；Described
Nitrogen oxides and carbon dioxide are absorbed in aqueous slkali absorber 13；The air that is stamped in the primary cooler 14 is tentatively cold
But；Elutriation is gone out in the primary separator 15；It is further cooled down in the secondary cooling device 16；In the secondary water
Water is further precipitated in separator 17；It is electronic followed by the second temperature sensor 19, second to obtain the air of low temperature drying
Regulating valve 20, one way stop peturn valve 21, the second spark arrester 22；It finally flows back to fuel tank and is rinsed inerting.
2）Cooling procedure：The cooling is divided into three strands with ram-air, one passes through the aqueous slkali absorber 13
Cold side gas exchanges heat；Secondly stock is exchanged heat by 13 cold side gas passage of the primary cooler；After two bursts of heatings
5 hot-side channel of the preheater is flowed through after ram-air mixing, preheats for reaction gas, is finally discharged to the outside.The cooling
It is mixed with the liquid water from primary separator 15, secondary separator 17 in the water jet 18 with its three strands of ram-air
It closes, is that gas cools down after reacting by 16 cold side channel of secondary cooling device.
3）Data collection and control process：
The third oxygen concentration sensor 23 detects fuel tank top oxygen concentration and transfers signals to the automatic controller
24；When oxygen concentration is more than given value, the controller 24 exports control signal to the wind turbine 3, turns on；According to described
Gas temperature that first temperature sensor 7 detects controls the heating frequency of the electric heater 6；It is dense according to first oxygen
Spend sensor 8, the first hydrocarbon sensor 9, the second hydrocarbon sensor 11, the detection of the second oxygen concentration sensor 12
To reaction before and after gas oxygen concentration and hydrocarbon concentration control the aperture of first electric control valve 4 and described
The power of reaction of low temperature plasma device 10, to improve inerting efficiency.Pass through 19 probe gas body temperature of the second temperature sensor
It spends and transfers signals to the automatic controller 24；When temperature is more than given value, the output control signal of the controller 24
To second electric control valve 20, make its closing, to ensure fuel tank safety.
Those skilled in the art of the present technique are it is understood that unless otherwise defined, all terms used herein（Including skill
Art term and scientific terminology）With meaning identical with the general understanding of the those of ordinary skill in the utility model fields
Justice.It should also be understood that those terms such as defined in the general dictionary should be understood that with upper with the prior art
The consistent meaning of meaning hereinafter, and unless defined as here, will not with the meaning of idealization or too formal come
It explains.
Above-described specific implementation mode, to the purpose of this utility model, technical solution and advantageous effect carried out into
One step is described in detail, it should be understood that the foregoing is merely specific embodiment of the present utility model, is not used to limit
The utility model processed, within the spirit and principle of the utility model, any modification, equivalent substitution, improvement and etc. done,
It should be included within the scope of protection of this utility model.
Claims (1)
1. the aircraft fuel tank oxygen concentration control device based on low temperature plasma, which is characterized in that include fuel tank（1）,
One spark arrester（2）, wind turbine（3）, the first electric control valve（4）, preheater（5）, electric heater（6）, the first temperature sensor
（7）, the first oxygen concentration sensor（8）, the first hydrocarbon sensor（9）, reaction of low temperature plasma device（10）, the second carbon
Hydrogen compound sensor（11）, the second oxygen concentration sensor（12）, aqueous slkali absorber（13）, primary cooler（14）, it is primary
Separator（15）, secondary cooling device（16）, secondary separator（17）, water jet（18）, second temperature sensor（19）,
Two electric control valves（20）, one way stop peturn valve（21）, the second spark arrester（22）, third oxygen concentration sensor（23）With automatically control
Device（24）；
The fuel tank（1）Including gas vent and gas access；The water jet（18）Including first to third entrance and one
Outlet；The automatic controller（24）Including current input terminal and current output terminal；
The fuel tank（1）Gas vent, the first spark arrester（2）, wind turbine（3）Entrance be sequentially connected by pipeline；
The wind turbine（3）Outlet respectively with first electric control valve（4）Outlet, preheater（5）Cold side channel enters
Mouth is connected by pipeline；
First electric control valve（4）Entrance be connected with external ram-air by pipeline；
The preheater（5）The outlet of cold side channel, electric heater（6）, the first temperature sensor（7）, the first oxygen concentration sensing
Device（8）, the first hydrocarbon sensor（9）, reaction of low temperature plasma device（10）, the second hydrocarbon sensor
（11）, the second oxygen concentration sensor（12）, aqueous slkali absorber（13）Hot-side channel, primary cooler（14）Hot side it is logical
Road, primary separator（15）, secondary cooling device（16）Hot-side channel, secondary separator（17）, second temperature sensor
（19）, the second electric control valve（20）, one way stop peturn valve（21）, the second spark arrester（22）, fuel tank（1）Gas access pass through pipe
Road is sequentially connected；
Third oxygen concentration sensor（23）Probe stretch into the fuel tank（1）It is interior, for incuding the fuel tank（1）Interior oxygen it is dense
Degree, and pass it to the automatic controller（24）；
The aqueous slkali absorber（13）Entrance, the primary cooler of cold side channel（14）The entrance of cold side channel, the water spray
Device（18）Third entrance by pipeline with outside is cooling is connected with ram-air；
The aqueous slkali absorber（13）The outlet of cold side channel, primary cooler（14）The outlet of cold side channel passes through pipe respectively
Road and the preheater（5）The entrance of cold side channel connects；
The preheater（5）The outlet of cold side channel is connected by pipeline with the external world；
The water jet（18）First entrance and the primary separator（15）Liquid outlet by pipeline be connected, water spray
Device（18）Second entrance and secondary separator（17）Liquid outlet by pipeline be connected, water jet（18）Outlet and institute
State secondary cooling device（16）The entrance of cold side channel is connected by pipeline；
The secondary cooling device（16）The outlet of cold side channel is connected by pipeline with the external world；
The automatic controller（24）Current input terminal respectively with the third oxygen concentration sensor（23）, the first temperature sensing
Device（7）, the first oxygen concentration sensor（8）, the first hydrocarbon sensor（9）, the second hydrocarbon sensor（11）,
Two oxygen concentration sensors（12）, second temperature sensor（19）Be electrically connected, current output terminal respectively with first electric adjustable
Save valve（4）, the second electric control valve（20）, wind turbine（3）, electric heater（6）, reaction of low temperature plasma device（10）Electrical phase
Even.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820087828.9U CN208036637U (en) | 2018-01-18 | 2018-01-18 | Aircraft fuel tank oxygen concentration control device based on low temperature plasma |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820087828.9U CN208036637U (en) | 2018-01-18 | 2018-01-18 | Aircraft fuel tank oxygen concentration control device based on low temperature plasma |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208036637U true CN208036637U (en) | 2018-11-02 |
Family
ID=63953664
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820087828.9U Expired - Fee Related CN208036637U (en) | 2018-01-18 | 2018-01-18 | Aircraft fuel tank oxygen concentration control device based on low temperature plasma |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208036637U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108177786A (en) * | 2018-01-18 | 2018-06-19 | 南京航空航天大学 | Aircraft fuel tank oxygen concentration control device based on low temperature plasma |
| CN114313279A (en) * | 2021-12-28 | 2022-04-12 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Catalytic inerting system with bypass branch control and control method |
-
2018
- 2018-01-18 CN CN201820087828.9U patent/CN208036637U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108177786A (en) * | 2018-01-18 | 2018-06-19 | 南京航空航天大学 | Aircraft fuel tank oxygen concentration control device based on low temperature plasma |
| CN108177786B (en) * | 2018-01-18 | 2023-09-26 | 南京航空航天大学 | Aircraft fuel tank oxygen concentration control device based on low-temperature plasma |
| CN114313279A (en) * | 2021-12-28 | 2022-04-12 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Catalytic inerting system with bypass branch control and control method |
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