CN106770898A - Plasma enhancing liquid fuel Flammability limits research device based on opposed firing - Google Patents
Plasma enhancing liquid fuel Flammability limits research device based on opposed firing Download PDFInfo
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Abstract
The invention provides a kind of experimental provision that can be used to study plasma enhancing liquid fuel Flammability limits, basic composition mainly includes opposed firing platform part, liquid fuel atomization part, plasma filling part and measuring device part.Wherein opposed firing platform part includes burner body (including airtight cavity, up/down jet pipe), flow control system, preheating insulation system and water-cooling system；Wherein preheating insulation system and water-cooling system install liquid fuel within jet pipe periphery.Liquid fuel atomization part includes liquid injection pump, quartzy atomizer and insulation transfer pipeline；Wherein insulation transfer pipeline is connected with opposed firing platform fuel nozzle.Plasma filling part includes plasma electrode and power supply.Measuring device part includes high-speed camera and acquisition system.
Description
Technical field
It is a kind of experiment dress for studying plasma enhancing liquid fuel Flammability limits the invention belongs to Push Technology field
Put.
Background technology
Scramjet engine is the product that the mankind constantly pursue high-speed flight, and hydrocarbon class I liquid I fuel is mainly passed through at present
Spraying enters engine combustion and provides power.But include during liquid fuel combustion complexity physics and chemical process and its
Interact, especially needed badly in severe supersonic combustion environment and be effectively improved combustion efficiency.Have verified that plasma is auxiliary
Combustion-supporting burning is a kind of effective ameliorative way, but research to substantially combustion-supporting mechanism also needs deeply to be opened based on special research platform
Exhibition.Opposed firing platform as a kind of basic combustion experiment platform, by the fuel and oxidizer flow of opposite spray up and down stagnant
Approximate one-dimensional flat flame is only set up near face, flame temperature, extensibility, igniting/extinction temperature, Flammability limits can be carried out
Influence Deng basic combustion is studied.
The research of Plasma Assisted Combustion hydrocarbon fuel mechanism is directed to both at home and abroad at present mainly for gaseous fuel, especially near
The Yiguang Ju of Xie Nian Princeton Universities teach team based on opposed firing platform, have studied sliding arc discharge, medium
The plasma of the generations such as barrier discharge, nanosecond pulse discharge is to CH4Firing temperature, flame-out stretching Deng gas hydrocarbon fuel
Influence (Yiguang Ju, the Wenting Sun.Plasma assisted of the generations such as rate, active component generation
combustion:Dynamics and chemistry[J],Progress in Energy and Combustion
Science,2015,48:21-83), while obtaining abundant experimental phenomena and data, the numerical value of the combustion-supporting mechanism of plasma
Analog study also plays huge impetus.The research that liquid fuel is carried out is focused mostly on based on opposed firing platform is added in research
Plus key component, PAH, the NO generated under different component, different flame structuresx、SOxDifference and the spy such as basic ignition temperature
Influence (P.Berta, S.K.Aggarwal, Ishwar K.Puri, et al.Experimental the and Numerical of property
Investigation of n-Heptane/Air Counterflow Nonpremixed Flame Structure[J]
.Journal of Propulsion and Power,Vol.24,No.4,2008:797-804；Ning Liu,Fokion
N.Egolfopoulos.Ignition of Non-Premixed Flames of Ethylene/n-Dodecane Blends
[J].Journal of Propulsion and Power,Vol.31,No.3,2015:889-895)。
In the so severe working environment of scramjet engine, if the Flammability limits of liquid fuel can effectively expand by
It is remarkably contributing to improve the working condition of engine, so carrying out plasma from basic burned angle expands grinding for effect
Study carefully very necessary, but current also lacking can be used to study plasma particularly cold plasma to liquid fuel Flammability limits shadow
Loud research platform, the present invention can regarding to the issue above carry out effectively research, improve plasmaassisted combustion mechanism and application
The Research Ability of aspect.
The content of the invention
Liquid fuel atomizer, cold plasma electric discharge device and opposed firing platform are coupled as a set of system by the present invention
System, realizes that global equivalent proportion is adjustable by controlling liquid fuel spray and oxidizer flow flow, enters in oxidant jet pipe side
Row dielectric barrier discharge, so as to the research work that plasma influences on liquid fuel Flammability limits can be carried out.
It is main special the invention provides a kind of experimental provision for studying the burning of plasmaassisted liquid fuel spray
Levy including opposed firing platform part, liquid fuel atomization part, plasma filling part and measuring device part.It is wherein right
Rushing combustion platform part includes fuel (on)/oxidant (under) air-flow jet pipe, flow control system, preheating insulation system, water-cooled system
System and data collecting system；The relative wake for spraying fuel, oxidizer flow and surrounding of wherein upper and lower jet pipe；Preheating insulation system
Liquid fuel within jet pipe periphery is installed with water-cooling system, ensures that combustion platform can be transported for a long time while avoiding atomized fuel from liquefying
OK；
Liquid fuel atomization part includes liquid injection pump, quartzy atomizer and insulation transfer pipeline；Wherein syringe pump will
In liquid fuel injection atomizer, then warm transfer pipeline is connected with opposed firing platform fuel nozzle.
Plasma filling part includes plasma electrode and power supply；Wherein the aciculiform anode of plasma system is installed
At oxidant quartz jet pipe center, negative electrode is the metal pipe-wall of outside wake, can be studied not by adjusting voltage and discharge frequency
With the influence that dielectric barrier discharge form is produced.
Measuring device part includes high-speed camera and computer, and flame occurs under high-speed camera real time record difference operating mode
Situation, and show on computers.
During work, the nitrogen stream being charged into the fuel of atomizer from the pump housing is taken out of, and together enters insulation delivery pipe
To ensure that gas flow temperature is sufficiently high in road and opposed firing platform fuel nozzle, in course of conveying, so that fuel vapour partial pressure is not
Less than its saturated vapor pressure；Make the thermal cracking temperature of gas flow temperature not higher than liquid fuel again simultaneously.First without plasma
Under body discharging condition lean combustion and the fuel-rich limit in the experimental bench are drawn by changing fuel-oxy equivalent proportion；Then in chemistry
Appropriately than equivalent proportion is progressively decreased or increased respectively under flame condition, while open plasma discharge flame is exerted one's influence,
Observe the situation of flame by high-speed camera near former lean combustion and the fuel-rich limit respectively, interpretation respectively goes out to apply plasma
Lean combustion and fuel-rich extreme variations afterwards.
The advantage that the present invention is applied to plasmaassisted liquid fuel spray combustion research has：
(1) complete liquid fuel spray Plasma Assisted Combustion basic research device.By liquid fuel atomizer with etc.
Plasma discharge device is integrated into opposed firing experimental bench, can be for plasma to liquid fuel lean combustion and the fuel-rich limit
Expand effect and carry out careful research.
(2) plasma discharge module is easy to adjust.By the coupling side of rationally design sparking electrode and oxidant jet pipe
Formula, conveniently replaced plasma discharge form, to study the auxiliary combustion effect of different plasma.
(3) it is easy to carry out more rich basic combustion characteristics research by various optical measurement means.Opposed firing platform four
Week is respectively arranged with quartz window, advanced by LDV LDV, LIF LIF, laser absorption spectrometry etc.
Optical measurement means, can further carry out in plasma liquid fuel within spray burning to flame temperature, flame-out extensibility, fire
The research of many factors such as flame face structure, intermediate state component influence.
Brief description of the drawings
Fig. 1 is the structure of the plasmaassisted liquid fuel spray combustion research device based on opposed firing of the invention
Schematic diagram.
Fig. 2 is the plasma discharge partial side elevation view in Fig. 1 shown devices.
Fig. 3 is to study the experiment flow figure that plasma influences on Flammability limits.
Specific embodiment
In conjunction with accompanying drawing 1,2, the influence by dielectric barrier discharge plasma to the liquid fuel spray burn combustible limit
Apparatus of the present invention are described in further detail by research.
Apparatus of the present invention include opposed firing platform part, liquid fuel atomization part, plasma filling part and measurement
Device part.Wherein opposed firing platform part include fuel (on) 11/ oxidant (under) air-flow jet pipe 14, flow control system 5,
Preheating insulation system 10, water-cooling system 13；The relative wake for spraying fuel, oxidizer flow and surrounding of wherein upper and lower jet pipe；On
Heating system 12 and water-cooling system 13 are installed simultaneously around jet pipe, ensure that combustion platform can while avoiding atomized fuel from liquefying
Long-play；
Liquid fuel atomization part includes liquid injection pump 1, quartzy atomizer 6 and insulation transfer pipeline 10；Experiment starts
Shi Shouxian is injected in atomizer 6 liquid fuel by syringe pump 1, while by N2Carrier gas passes through atomizer 6 by injected fuel spray band
Go out, then warm transfer pipeline 10 is connected with opposed firing platform fuel nozzle 11.O2Air-flow 3 and N2Carrier gas 4 is injected mixed simultaneously
Close in chamber 7, be then connected with oxidant jet pipe 14 through transfer pipeline；
Plasma filling part includes plasma electrode 16 and power supply 9；Wherein plasma system negative electrode is limitation
The metal pipe-wall 14 of outside wake, negative electrode 16 is copper bar electrode, is arranged in oxidant quartz jet pipe 15 by copper rod set 17
The heart, both are connected with plasma electrical source 9, and plasma discharge is realized by adjusting voltage and frequency；
Measuring device part include high-speed camera 8 and computer, high-speed camera 8 can real time record difference operating mode under flame
The situation of appearance, and show on computers.
The specific steps of experimental study are described with reference to accompanying drawing 3.Carry out plasma on the platform flammable to liquid fuel
The research specific implementation step of limit influence is as follows：
Step one, experiment determine liquid fuel lean combustion/fuel-rich limit under the conditions of discharge off
For selected liquid fuel (such as n-decane), determine that its lean combustion/fuel-rich limit is the first step on the experimental bench,
Embodiment is as follows：
1) pipeline heating and combustion platform water-cooling system are opened, to insulation transfer pipeline preheating；
2) fuel, oxidant, nitrogen wake and argon gas stream (with oxidizer flow mixing jetting) each road air-flow are opened, and is led to
Excessively stream amount control system is by fuel and oxidizer flow flow rate in stoichiometric ratio state；
3) it is so as to produce flame and relative by adjusting upper and lower jet pipe by spark ignition air-flow after air-flow is basicly stable
Position and upper and lower wake flow form basicly stable one-dimensional plane flame；
4) by flow control system progressively small size increasing or decreasing oxidizer flow flow rate, global equivalent proportion is realized progressively
Successively decrease or be incremented by, while the shooting by high speed camera to flame image, judges that flame whether there is, so that it is determined that lean combustion and richness
Equivalence ratio under the combustion limit.Judge that flame whether there is the position that pay special attention to flame appearance from shooting image, need to be with sight
Survey whether still suffered near district center position flame as whether flame-out criterion.
Step 2, under the conditions of dielectric barrier discharge Study of Liquid fuel lean combustion/fuel-rich limit expansion
Specific embodiment is as follows：
1) in the experimental program of repeat step one 1), 2), 3) step, be formed about and step one in two jet pipe stagnation face positions
Middle operating mode identical stabilization one-dimensional plane flame；
2) plasma electrical source is opened, discharge voltage and frequency is adjusted to setting value；
3) by flow control system progressively small size increasing or decreasing oxidizer flow flow rate, realize global equivalent proportion by
Step is successively decreased or is incremented by, and is shot flame image by high speed camera and judged whether to extinguish, so that it is determined that under lean combustion and the fuel-rich limit
Equivalence ratio.
Plasma can be obtained to liquid fuel (n-decane) by lean combustion in comparison step one and two and the fuel-rich limit
The influence situation of Flammability limits.Extensibility, discharge voltage, frequency etc. can be further studied in a comparable manner to variety classes
The influence of liquid fuel spray burning, for analyzing and verifying plasmaassisted combustion mechanism.
Claims (1)
1. a kind of experimental provision for carrying out plasma enhancing liquid fuel Flammability limits research, mainly includes opposed firing platform
Partly, liquid fuel atomization part, plasma filling part and measuring device part, it is characterised in that：
(1) opposed firing platform part includes burner body, flow control system, preheating insulation system and water-cooling system；Wherein
Burner body by airtight cavity and upper (fuel)/under (oxidant) air-flow jet pipe constitute, formed by the air-flow of opposite injection
Quasi-one-dimensional planar diffusion flame；
Flow control system is made up of mass flowmenter, control software, control fuel gas stream, oxidizer flow, up/down wake,
The flow of plasma flow of feed gas；
Preheating insulation system is made up of heating tape, attemperating unit, by heating upper jet pipe fuel jet pipe pipe in burner body
Wall makes fuel gas stream temperature be maintained at 200 DEG C or so, it is to avoid liquid fuel spray liquefies；
Water-cooling system is made up of water-cooled pipeline, water-cooling groove, and burner cavity is cooled down, it is ensured that experimental bench stable work time
It is not shorter than 30 minutes；
(2) liquid fuel atomization part includes liquid injection pump, quartzy atomizer and insulation transfer pipeline；Liquid fuel is by note
Penetrate pump to enter in atomizer, then warm transfer pipeline is connected with opposed firing platform fuel nozzle；
(3) plasma filling part includes sparking electrode and power supply；Wherein electric discharge device anode is aciculiform copper bar, installed in oxygen
In the copper rod set at agent quartz jet pipe center, negative electrode is the copper metal tube wall of outside wake, and power supply is high-frequency and high-voltage power supply；
(4) measuring device part includes high-speed camera and computer, can be with flame under the frequency record of 3000 frames/second difference operating mode
The situation of appearance, as the criterion of igniting success or not.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109270208A (en) * | 2018-10-09 | 2019-01-25 | 内蒙航天动力机械测试所 | Liquid fuel igniting pilot system |
| CN109884244A (en) * | 2019-03-12 | 2019-06-14 | 南京理工大学 | Wide pressure limit flames in opposing direction experimental provision |
| CN110045081A (en) * | 2019-03-28 | 2019-07-23 | 西北工业大学 | A kind of experimental provision for studying novel liquid carbon hydrogen fuel ignition performance |
| CN111678128A (en) * | 2020-06-30 | 2020-09-18 | 安徽工业大学 | Liquid combustion system and combustion method for obtaining high-stability flame based on high-precision control |
| CN114324735A (en) * | 2022-01-05 | 2022-04-12 | 西安交通大学 | System for measuring variable pressure and wide temperature range working condition fuel flameout characteristics |
| CN115014767A (en) * | 2022-04-25 | 2022-09-06 | 西北工业大学 | Oxygen-enriched air wake combustion test device based on laser ignition |
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| WO2012088552A1 (en) * | 2010-12-29 | 2012-07-05 | Fronius International Gmbh | Heating element, steam cutting device, and burner of a power-generating device |
| CN103900107A (en) * | 2014-03-11 | 2014-07-02 | 哈尔滨工程大学 | Dual-fuel nozzle for plasma and gas-assisted atomization burning |
| CN105765304A (en) * | 2013-12-31 | 2016-07-13 | 克利尔赛恩燃烧公司 | Method and apparatus for extending flammability limits in a combustion reaction |
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Patent Citations (4)
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|---|---|---|---|---|
| CN1464221A (en) * | 2002-06-06 | 2003-12-31 | 曹蕴明 | Thermal dissociation gasification turbulent flow injection combustion apparatus |
| WO2012088552A1 (en) * | 2010-12-29 | 2012-07-05 | Fronius International Gmbh | Heating element, steam cutting device, and burner of a power-generating device |
| CN105765304A (en) * | 2013-12-31 | 2016-07-13 | 克利尔赛恩燃烧公司 | Method and apparatus for extending flammability limits in a combustion reaction |
| CN103900107A (en) * | 2014-03-11 | 2014-07-02 | 哈尔滨工程大学 | Dual-fuel nozzle for plasma and gas-assisted atomization burning |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109270208A (en) * | 2018-10-09 | 2019-01-25 | 内蒙航天动力机械测试所 | Liquid fuel igniting pilot system |
| CN109884244A (en) * | 2019-03-12 | 2019-06-14 | 南京理工大学 | Wide pressure limit flames in opposing direction experimental provision |
| CN110045081A (en) * | 2019-03-28 | 2019-07-23 | 西北工业大学 | A kind of experimental provision for studying novel liquid carbon hydrogen fuel ignition performance |
| CN111678128A (en) * | 2020-06-30 | 2020-09-18 | 安徽工业大学 | Liquid combustion system and combustion method for obtaining high-stability flame based on high-precision control |
| CN114324735A (en) * | 2022-01-05 | 2022-04-12 | 西安交通大学 | System for measuring variable pressure and wide temperature range working condition fuel flameout characteristics |
| CN115014767A (en) * | 2022-04-25 | 2022-09-06 | 西北工业大学 | Oxygen-enriched air wake combustion test device based on laser ignition |
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