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CN103216317A - Supersonic combustion method actuated by combination plasma - Google Patents

Supersonic combustion method actuated by combination plasma Download PDF

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Publication number
CN103216317A
CN103216317A CN2013101316878A CN201310131687A CN103216317A CN 103216317 A CN103216317 A CN 103216317A CN 2013101316878 A CN2013101316878 A CN 2013101316878A CN 201310131687 A CN201310131687 A CN 201310131687A CN 103216317 A CN103216317 A CN 103216317A
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China
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hole
plasma
thermal equilibrium
combustion method
combustion
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CN2013101316878A
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唐井峰
徐敏
李楠
于达仁
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Harbin Institute of Technology
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Harbin Institute of Technology
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    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

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Abstract

The invention discloses a supersonic combustion method actuated by combination plasma, relates to the supersonic combustion method for an engine combustion chamber, and solves the problems that by using an existing concave chamber type combustion method, the concave chamber dimensions are large, the flow loss is large, and the supersonic combustion performance is poor. The method comprises the steps that 1) a ceramic membrane is plated on the inner surface of each through hole; 2) the first through hole is connected with a fuel oil outlet pipe, the second through hole and the fourth through hole are connected with a thermal equilibrium plasma generator respectively, and the third through hole and the fifth through hole are connected with a non-thermal equilibrium plasma generator respectively; 3) fuel oil is injected into the combustion chamber through the first through hole; 4) a working medium is ejected from the thermal equilibrium plasma generator, is injected into a combustion area of the engine combustion chamber and ignites the fuel oil at the combustion area to form diffusion flame and realize ignition; and 5) jet cooling plasma is ejected from the non-thermal equilibrium plasma generator, and is injected into different positions of the combustion chamber through the third through hole and the fifth through hole for forming reliable combustion. The method provided by the invention is used for organizing supersonic combustion.

Description

Ultrasound velocity combustion method under the combination plasma excitation
Technical field
The present invention relates to a kind of engine chamber ultrasound velocity combustion method, be specifically related to a kind of ultrasound velocity combustion method that makes up under the plasma excitation.
Background technique
In the ultrasound velocity combustion technology, incoming flow flows with ultrasound velocity in the firing chamber, and the viscous flow time has only several milliseconds, so will realize the igniting of fuel and burn very difficult in the short time.
Cavity formula combustion method is a ultrasound velocity burning method for organizing commonly used at present.Pipeline by the cavity upper reaches is introduced fuel in the firing chamber, utilizes fuel to spread the burning that realizes in the high velocity air in the low speed whirlpool district in cavity.For the steady flame, require the cavity size bigger, make up the low speed whirlpool district of its large scale, be beneficial to inflammable gas and form stable hot flame in this zone enough time of stop.The flow losses that large scale whirlpool district in the supersonic speed combustion chamber in the cavity is brought are often bigger, reduced the performance of ultrasound velocity burning.Cavity flame often is close to wall simultaneously, increases the engine structure thermal force.
Summary of the invention
The objective of the invention is for solving in the existing cavity formula combustion method cavity yardstick greatlyyer, the problem that flow losses are big, the ultrasound velocity combustion performance is low proposes a kind of ultrasound velocity combustion method that makes up under the plasma excitation.
The inventive method realizes by following steps:
Step 1, process first through hole, second through hole, third through-hole, fourth hole and fifth hole from front to back successively on the wall thickness of engine chamber, the internal surface of first through hole, second through hole, third through-hole, fourth hole and fifth hole all is coated with ceramic membrane;
The input end of step 2, first through hole is connected with the fuel oil output tube, the input end of second through hole and fourth hole is connected with outlet on the thermal equilibrium plasma generator respectively, and the input end of third through-hole and fifth hole is connected with outlet on the thermal nonequilibrium plasma generator respectively;
Step 3, fuel oil are injected in the engine chamber by first through hole;
Step 4, needle-like electrodes in the thermal equilibrium plasma generator connects dc power anode, the sidewall of thermal equilibrium plasma generator connects dc power cathode, two sidewall cusps on the electrode pinnacle of needle-like electrodes and the madial wall of thermal equilibrium plasma generator form the arc discharge passage, mixed gas forms the elevated temperature heat plasma during by the arc discharge passage and is sprayed by the thermal equilibrium plasma generator, be injected into generation jet type plasma in the engine chamber through second through hole and fourth hole, produce the fuel oil in the jet type plasma ignition firing chamber, form the combustion flame that one continues, wherein, the supply voltage of thermal equilibrium plasma is 500V～1000V, and electric current is 50A～200A;
Step 5, stoneware pipe in the nonthermal plasma generating means connects high-frequency and high-voltage power supply, the nonthermal plasma generating means is receiving electrode not, form suspension electrode, argon gas injects the nonthermal plasma generating means by stoneware pipe and side opening, under the high-frequency high-voltage source forcing, produce jet type cold plasma, jet type cold plasma is sprayed by the nonthermal plasma generating means, be injected into diverse location in the engine chamber through third through-hole and fifth hole, form reliable burning, wherein, the supply voltage of nonequilibrium plasma is 5000V～10000V, and power supply frequency is 30000Hz～50000Hz.
The present invention has the following advantages: one, utilize the high temperature of thermal equilibrium plasma, come the igniting of combustion gas in the inducing combustion chamber, have the advantages that ignition energy is low, ignition delay time is short, can realize the flame holding under the thermal equilibrium plasma excitation.Two, the thermal nonequilibrium jet plasma produces a large amount of chemical activation groups, forms combustive activation nuclear efficiently, can improve the efficient of ultrasound velocity burning.Three, certain variation can take place in flame structure under the different inlet flow conditions, according to needing and can injecting the thermal nonequilibrium jet plasma at the lower wall surface diverse location of firing chamber, with the combustion field in the control firing chamber, and then comes the organization ultrasonic quick burning to burn performance.Four, increased the passage that is coated with ceramic membrane among the present invention on the wall thickness of firing chamber, the outside plasma that produces in firing chamber imports in the firing chamber by this passage, has avoided the technical need at the indoor layout animating electrode of high-temp combustion.
Description of drawings
Fig. 1 is that (mark 6 is fuel oil stream among the figure for the structural representation of step 2 in the specific embodiment of the present invention one, 7 is the thermal equilibrium plasma jet, 8 is the nonthermal plasma jet), Fig. 2 is that (mark 2-3 is a high-temperature seal ring among the figure for the structural representation of thermal equilibrium plasma generator 2,2-4 is a Stainless Steel Tube, 2-5 is the outlet of thermal equilibrium plasma, 2-6 is the ceramic insulation packing ring, 2-7 is a ceramics insulator), Fig. 3 is that (mark 5 is the high voltage high-frequency power among the figure for the structural representation of thermal nonequilibrium plasma generator 3,3-1 is for stopping up, 3-2 is the high strength quartz tube, 3-3 is a Stainless Steel Tube, 3-4 is the outlet of thermal nonequilibrium plasma).
Embodiment
Embodiment one: in conjunction with Fig. 1～Fig. 3 present embodiment is described, present embodiment realizes by following steps:
Step 1, process the first through hole 1-1, the second through hole 1-2, third through-hole 1-3, fourth hole 1-4 and fifth hole 1-5 from front to back successively on the wall thickness of engine chamber 1, the internal surface of the first through hole 1-1, the second through hole 1-2, third through-hole 1-3, fourth hole 1-4 and fifth hole 1-5 all is coated with ceramic membrane;
The input end of step 2, the first through hole 1-1 is connected with fuel oil output tube 4, the input end of the second through hole 1-2 and fourth hole 1-4 is connected with outlet on the thermal equilibrium plasma generator 2 respectively, and the input end of third through-hole 1-3 and fifth hole 1-5 is connected with outlet on the thermal nonequilibrium plasma generator 3 respectively;
Step 3, fuel oil are injected in the engine chamber 1 by the first through hole 1-1;
Step 4, needle-like electrodes 2-1 in the thermal equilibrium plasma generator 2 connects dc power anode 9, the sidewall of thermal equilibrium plasma generator 2 connects dc power cathode 10, two sidewall cusps on the electrode pinnacle of needle-like electrodes 2-1 and the madial wall of thermal equilibrium plasma generator 2 form arc discharge passage 2-2, mixed gas forms the elevated temperature heat plasma during by arc discharge passage 2-2 by 2 ejections of thermal equilibrium plasma generator, be injected into generation jet type plasma 7 in the engine chamber 1 through the second through hole 1-2 and fourth hole 1-4, produce the fuel oil in the jet type plasma ignition combustion chambers 7, form the combustion flame that one continues, and this flame can be on the engine chamber wall stable existence, thereby realize the stable of ultrasound velocity flame, wherein, the supply voltage of thermal equilibrium plasma is 500V～1000V, and electric current is 50A～200A; The jet thermal plasma at the second through hole 1-2 place has higher energy, can light fuel oil easily and form the combustion flame that one continues, and the jet thermal plasma at fourth hole 1-4 place is injected into and carries out afterburning in the flame.
Step 5, stoneware pipe 3-2 in the nonthermal plasma generating means 3 connects high-frequency and high-voltage power supply 5, nonthermal plasma generating means 3 is receiving electrode not, form suspension electrode, argon gas injects nonthermal plasma generating means 3 by stoneware pipe 3-2 and side opening 3-5, under the high-frequency high-voltage source forcing, produce jet type cold plasma 8, jet type cold plasma 8 is by 3 ejections of nonthermal plasma generating means, be injected into diverse location in the engine chamber 1 through third through-hole 1-3 and fifth hole 1-5, form reliable burning, jet type cold plasma 8 has very extensive chemical activity, induce and produce a large amount of active groups, and then formation mainly depends on the local active combustion district of jet type cold plasma, strengthened the ultrasound velocity velocity of combustion, wherein, the supply voltage of nonequilibrium plasma is 5000V～10000V, and power supply frequency is 30000Hz～50000Hz.The injection of jet type cold plasma 8 can be induced and be produced a large amount of activated groups, with further strengening burning; Inject cold plasma on the axial diverse location, can satisfy the demand of ultrasound velocity burning tissue; Jet type cold plasma 8 fully mixes with incoming flow, improved the activation energy of fuel integral body, help accelerated combustion, and inject the position that cold plasma can to a certain degree be controlled flame, make in the firing chamber flame smooth combustion and guarantee position-controllable by diverse location.
Embodiment two: in conjunction with Fig. 1 present embodiment is described, present embodiment is that the thickness of the internal surface ceramic membrane of the first through hole 1-1, the second through hole 1-2, third through-hole 1-3, fourth hole 1-4 and fifth hole 1-5 in the step 1 is 0.1mm～0.2mm.Ceramic membrane has been realized the insulating effect between plasma and wall, and ceramic membrane can produce secondary emission under the collision of plasma, helps the stable propagation of plasma in through hole.Other step is identical with embodiment one.
Embodiment three: in conjunction with Fig. 1 present embodiment is described, present embodiment is that the thickness of the internal surface ceramic membrane of the first through hole 1-1, the second through hole 1-2, third through-hole 1-3, fourth hole 1-4 and fifth hole 1-5 in the step 1 is 0.15mm.Other step is identical with embodiment two.
Embodiment four: in conjunction with Fig. 1 present embodiment is described, present embodiment is that the mixed gas in the step 4 in the step 4 is oxygen and nitrogen, and the volume ratio of oxygen and nitrogen is 1: 4.Other step is identical with embodiment one.
Embodiment five: in conjunction with Fig. 1 present embodiment is described, present embodiment is that the supply voltage of the thermal equilibrium plasma in the step 4 is 1000V, and electric current is 50A.Other step is identical with embodiment one.
Embodiment six: in conjunction with Fig. 1 present embodiment is described, present embodiment is that the supply voltage of the thermal equilibrium plasma in the step 4 is 500V, and electric current is 100A.Other step is identical with embodiment one.
Embodiment seven: in conjunction with Fig. 1 present embodiment is described, present embodiment is that the supply voltage of the thermal equilibrium plasma in the step 4 is 500V, and electric current is 200A.Other step is identical with embodiment one.
Embodiment eight: in conjunction with Fig. 1 present embodiment is described, present embodiment is that the supply voltage of the cold plasma in the step 5 is 6500V, and power supply frequency is 50000Hz.Other step is identical with embodiment one.
Embodiment nine: in conjunction with Fig. 1 present embodiment is described, present embodiment is that the supply voltage of the cold plasma in the step 5 is 7500V, and power supply frequency is 40000Hz.Other step is identical with embodiment one.
Embodiment ten: in conjunction with Fig. 1 present embodiment is described, present embodiment is that the supply voltage of the cold plasma in the step 5 is 8500V, and power supply frequency is 50000Hz.Other step is identical with embodiment one.

Claims (10)

1. ultrasound velocity combustion method that makes up under the plasma excitation, it is characterized in that: described method realizes by following steps:
Step 1, process first through hole (1-1), second through hole (1-2), third through-hole (1-3), fourth hole (1-4) and fifth hole (1-5) from front to back successively on the wall thickness of engine chamber (1), the internal surface of first through hole (1-1), second through hole (1-2), third through-hole (1-3), fourth hole (1-4) and fifth hole (1-5) all is coated with ceramic membrane;
The input end of step 2, first through hole (1-1) is connected with fuel oil output tube (4), the input end of second through hole (1-2) and fourth hole (1-4) is connected with outlet on the thermal equilibrium plasma generator (2) respectively, and the input end of third through-hole (1-3) and fifth hole (1-5) is connected with outlet on the thermal nonequilibrium plasma generator (3) respectively;
Step 3, fuel oil are injected in the engine chamber (1) by first through hole (1-1);
Step 4, needle-like electrodes (2-1) in the thermal equilibrium plasma generator (2) connects dc power anode (9), the sidewall of thermal equilibrium plasma generator (2) connects dc power cathode (10), two sidewall cusps on the madial wall of the electrode pinnacle of needle-like electrodes (2-1) and thermal equilibrium plasma generator (2) form arc discharge passage (2-2), mixed gas forms the elevated temperature heat plasma during by arc discharge passage (2-2) and is sprayed by thermal equilibrium plasma generator (2), be injected into generation jet type plasma (7) in the engine chamber (1) through second through hole (1-2) and fourth hole (1-4), produce the fuel oil in jet type plasma (7) the ignition combustion chamber, form the combustion flame that one continues, wherein, the supply voltage of thermal equilibrium plasma is 500V～1000V, and electric current is 50A～200A;
Step 5, stoneware pipe (3-2) in the nonthermal plasma generating means (3) connects high-frequency and high-voltage power supply (5), nonthermal plasma generating means (3) is receiving electrode not, form suspension electrode, argon gas injects nonthermal plasma generating means (3) by stoneware pipe (3-2) and side opening (3-5), under the high-frequency high-voltage source forcing, produce jet type cold plasma (8), jet type cold plasma (8) is sprayed by nonthermal plasma generating means (3), be injected into diverse location in the engine chamber (1) through third through-hole (1-3) and fifth hole (1-5), form reliable burning, wherein, the supply voltage of nonequilibrium plasma is 5000V～10000V, and power supply frequency is 30000Hz～50000Hz.
2. according to the ultrasound velocity combustion method under the described combination plasma excitation of claim 1, it is characterized in that: the thickness of the internal surface ceramic membrane of first through hole (1-1) in the described step 1, second through hole (1-2), third through-hole (1-3), fourth hole (1-4) and fifth hole (1-5) is 0.1mm～0.2mm.
3. according to the ultrasound velocity combustion method under the described combination plasma excitation of claim 2, it is characterized in that: the thickness of the internal surface ceramic membrane of first through hole (1-1) in the described step 1, second through hole (1-2), third through-hole (1-3), fourth hole (1-4) and fifth hole (1-5) is 0.15mm.
4. according to the ultrasound velocity combustion method under the described combination plasma excitation of claim 1, it is characterized in that: the mixed gas in the described step 4 is oxygen and nitrogen, and the volume ratio of oxygen and nitrogen is 1: 4.
5. according to the ultrasound velocity combustion method under the described combination plasma excitation of claim 1, it is characterized in that: the supply voltage of the thermal equilibrium plasma in the described step 4 is 1000V, and electric current is 50A.
6. according to the ultrasound velocity combustion method under the described combination plasma excitation of claim 1, it is characterized in that: the supply voltage of the thermal equilibrium plasma in the described step 4 is 500V, and electric current is 100A.
7. according to the ultrasound velocity combustion method under the described combination plasma excitation of claim 1, it is characterized in that: the supply voltage of the thermal equilibrium plasma in the described step 4 is 500V, and electric current is 200A.
8. according to the ultrasound velocity combustion method under the described combination plasma excitation of claim 1, it is characterized in that: the supply voltage of the cold plasma in the described step 5 is 6500V, and power supply frequency is 50000Hz.
9. according to the ultrasound velocity combustion method under the described combination plasma excitation of claim 1, it is characterized in that: the supply voltage of the cold plasma in the described step 5 is 7500V, and power supply frequency is 40000Hz.
10. according to the ultrasound velocity combustion method under the described combination plasma excitation of claim 1, it is characterized in that: the supply voltage of the cold plasma in the described step 5 is 8500V, and power supply frequency is 50000Hz.
CN2013101316878A 2013-04-16 2013-04-16 Supersonic combustion method actuated by combination plasma Pending CN103216317A (en)

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103343983A (en) * 2013-07-31 2013-10-09 哈尔滨工业大学 Supersonic-speed stable combustion method based on strong magnetic field stable electric arc
CN103529719A (en) * 2013-09-24 2014-01-22 中国科学院力学研究所 Electric equipment control circuit applied to supersonic combustion test
CN107366928A (en) * 2017-06-20 2017-11-21 中国人民解放军空军工程大学 A kind of Plasma Assisted Combustion method of engine chamber
CN108104945A (en) * 2017-05-16 2018-06-01 大连民族大学 A kind of two-stroke internal combustion engine electrode assembly
CN109723577A (en) * 2018-12-24 2019-05-07 中国人民解放军战略支援部队航天工程大学 A kind of unstable Active Control Method of high-frequency combustion based on plasma
CN114234239A (en) * 2021-12-13 2022-03-25 哈尔滨工业大学 Combustion system and method based on cooperation of metal-based particles and microwaves

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009008524A1 (en) * 2007-07-12 2009-01-15 Imagineering, Inc. Ignition and chemical reaction accelerator and flame stabilizer, speed-type internal combustion engine, and furnace
EP2255081A2 (en) * 2008-02-12 2010-12-01 Foret Plasma Labs, Llc System, method and apparatus for lean combustion with plasma from an electrical arc
CN101949550A (en) * 2010-09-30 2011-01-19 哈尔滨工业大学 Stable supersonic combustion method based on jetting plasma activation
CN102797590A (en) * 2012-07-31 2012-11-28 哈尔滨工业大学 Plasma excitation-based method for restraining separation of boundary layer in air inlet passageway

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009008524A1 (en) * 2007-07-12 2009-01-15 Imagineering, Inc. Ignition and chemical reaction accelerator and flame stabilizer, speed-type internal combustion engine, and furnace
EP2255081A2 (en) * 2008-02-12 2010-12-01 Foret Plasma Labs, Llc System, method and apparatus for lean combustion with plasma from an electrical arc
CN101949550A (en) * 2010-09-30 2011-01-19 哈尔滨工业大学 Stable supersonic combustion method based on jetting plasma activation
CN102797590A (en) * 2012-07-31 2012-11-28 哈尔滨工业大学 Plasma excitation-based method for restraining separation of boundary layer in air inlet passageway

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
李飞等: "超声速气流中煤油射流的等离子体点火实验", 《航空动力学报》, vol. 27, no. 4, 30 April 2012 (2012-04-30), pages 824 - 831 *
韦宝禧等: "超燃燃烧室等离子体点火和火焰稳定性能", 《北京航空航天大学学报》, vol. 38, no. 12, 31 December 2012 (2012-12-31), pages 1572 - 1576 *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103343983A (en) * 2013-07-31 2013-10-09 哈尔滨工业大学 Supersonic-speed stable combustion method based on strong magnetic field stable electric arc
CN103343983B (en) * 2013-07-31 2014-12-24 哈尔滨工业大学 Supersonic-speed stable combustion method based on strong magnetic field stable electric arc
CN103529719A (en) * 2013-09-24 2014-01-22 中国科学院力学研究所 Electric equipment control circuit applied to supersonic combustion test
CN103529719B (en) * 2013-09-24 2016-05-04 中国科学院力学研究所 A kind of electrical equipment control circuit that is applied to Supersonic combustion tests
CN108104945A (en) * 2017-05-16 2018-06-01 大连民族大学 A kind of two-stroke internal combustion engine electrode assembly
CN107366928A (en) * 2017-06-20 2017-11-21 中国人民解放军空军工程大学 A kind of Plasma Assisted Combustion method of engine chamber
CN107366928B (en) * 2017-06-20 2019-07-16 中国人民解放军空军工程大学 A kind of Plasma Assisted Combustion method of engine chamber
CN109723577A (en) * 2018-12-24 2019-05-07 中国人民解放军战略支援部队航天工程大学 A kind of unstable Active Control Method of high-frequency combustion based on plasma
CN109723577B (en) * 2018-12-24 2020-04-24 中国人民解放军战略支援部队航天工程大学 Plasma-based active control method for instability of high-frequency combustion
CN114234239A (en) * 2021-12-13 2022-03-25 哈尔滨工业大学 Combustion system and method based on cooperation of metal-based particles and microwaves

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Application publication date: 20130724