CN103277231A - Aero-engine air rotational flow plasma igniter - Google Patents
Aero-engine air rotational flow plasma igniter Download PDFInfo
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- CN103277231A CN103277231A CN2013100846970A CN201310084697A CN103277231A CN 103277231 A CN103277231 A CN 103277231A CN 2013100846970 A CN2013100846970 A CN 2013100846970A CN 201310084697 A CN201310084697 A CN 201310084697A CN 103277231 A CN103277231 A CN 103277231A
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Abstract
Provided is an aero-engine air rotational flow plasma igniter. An insulating sleeve and a supporting sleeve are installed inside a shell, the insulating sleeve is arranged on one side of a separating plate inside the shell, the supporting sleeve is arranged inside the shell, and an air chamber is formed between the outer surface of the supporting sleeve and the inner surface of the shell. An anode sleeve is sleeved at one end, provided with the supporting sleeve, of the shell. A swirler is arranged inside the anode sleeve, and the end surface of the swirler makes contact with the end surface of the supporting sleeve. A cathode installation base is arranged inside the insulating sleeve, and the end surface of the cathode installation base makes contact with a cathode binding post in a coaxial cable. The external thread end of a cathode is fixed inside the cathode installation base and sequentially penetrates through the supporting sleeve and the swirler from top to bottom, and the arc end of the cathode extends out of the lower end surface of the swirler. The aero-engine air rotational flow plasma igniter does not change the structure and the position of an electric spark igniter originally installed in an engine combustor, penetrates through the outer duct of an engine, is installed on the outer wall of the combustor vertically, improves reliability of products, and has the advantages of being small in size, light in weight, simple in structure, and convenient to use and maintain.
Description
Technical field
The present invention relates to plasma igniting and the combustion intensification technology in aviation power field, plasma igniter is working medium with the air, working medium forms Arc Discharge through high-voltage breakdown, form with high temp jet penetrates from the igniter spout, form the high temperature tongues of fire, utilize the high temperature, the high speed plasma jet that are rich in active particle to light the indoor fuel-air mixture of aeroengine combustor buring.
Background technique
Along with improving constantly of fighter performance, to the aeroengine combustor buring chamber under the motor-driven and aloft work condition of height starting characteristic and have higher requirement.At present, the high energy ignition unit of aeroengine use both at home and abroad adopts semiconductor discharge plug usually, in abominable hot environment, work for a long time, its characteristic of semiconductor is aging gradually, the sparking plug breakdown voltage is more and more higher, surpass the operating voltage of igniter gradually and lost efficacy, make the low-frequency high-voltage pulse of ignition mechanism output can't the breakdown voltage semiconductor sparking plug, cause a whole set of electric fiery failure of apparatus.In addition, the ignition energy of conventional ignition mechanism is lower, and there is the problem of the ignition limit deficiency under plateau, the little indicated airspeed situation in high/low gentle high-altitude in the aero gas turbine engine of China, and conventional ignition system is difficult to satisfy the needs that start again in the engine air of high-altitude (the particularly above and even near space of 20km).
Plasma-ignition technique has characteristics such as ignition energy is big, tongues of fire penetrating power is strong, be conducive to improve the reliability of under abominable working environment (near space) condition, lighting flow at high speed fuel/air mixture mixed gas, enlarge ignition range, improve the airstart performance of motor.Therefore, carry out the plasma-ignition technique research of aeroengine combustor buring chamber, be to improve pressing for of its Security, functional reliability in aeroengine development and the use, for the application of plasma-ignition technique in high thrust weight ratio turbofan engine, big power to weight ratio turboshaft engine firing chamber provides technological reserve.
The research of plasma-ignition technique has just caused various countries experts' extensive concern as far back as the seventies in 20th century.But owing to be subjected to the restriction of technical specifications at that time, its research only limits to the industrial combustion aspect.The mid-80, this technology begin to turn on ground combustion machine and the Aero-Space power plant.Particularly along with kinetics of combustion and other high-tech development, plasma-ignition technique is subjected to showing great attention to and paying attention to of Aero-Space power circle gradually with its intrinsic characteristics and significant advantage.In recent years, the big state of World Airways all begins to be applicable to the research of the plasma-ignition technique in Aeronautics and Astronautics engine chamber and the tail pipe burner.Aviation developed country such as the U.S. and Russia has developed plasma igniter, and has carried out the high-altitude ignition demonstration test in aeroengine, and a lot of key technologies of plasma igniting have obtained bigger development.
1988, Britain RR fuel adding company combustion study chamber and department of mechanical engineering of University of Leeds utilize the AIT altitude simulation unit to use spark plug boundling discharge plasma igniter successfully to test in the motor can annular type combustor, have verified this technology Application feasibility and superior high-altitude reignition capability on aeroengine.1992, U.S. GE company, Siemens motor Compak Systems Ltd., aviation plasma technology company were with aeroengine main combustion chamber or the tail pipe burner patent (Fig. 1) of plasma igniting system that has been the application application., U.S. Applied Plasma Technologies(APT in 2004) the Igor Matveev of company etc. has carried out the plasma igniting test of 12Km high-altitude to the plasma igniter of developing, and has showed its good high-altitude ignition performance reliably.
The plasma igniting research of China is started late, technical foundation is relatively weaker, plasma-ignition technique has certain application at civil boiler, ground and naval gas turbine, and key technologies for application is still waiting further research in the aeroengine combustor buring chamber.Longyuan Electric Technology Co., Ltd., Yantai produced first industrial plasma ignition device of DLZ-200 (Fig. 2) in 1998, under the situation of normal temperature powder feeding, had successfully lighted fugitive constituent and be Zibo meager coal of 11%.Calendar year 2001, Harbin Engineering University bore the pulsed plasma ignition system production domesticization task of GT25000 naval gas turbine.Above-mentioned two kinds of plasma igniters are mainly used in civil boiler and the naval gas turbine, and the volume and weight of plasma igniter is bigger, and the striking mode is the arcing of electrode linear slide, are unsuitable for using in the high temperature and high pressure environment of aeroengine combustor buring chamber.2006, the Song Wenyan of Northwestern Polytechnical University's power and energy institute etc. cooperates (Fig. 3) with Chinese aerodynamic investigation and carried out plasma igniting in the scramjet engine firing chamber with the centre of development, plasma igniter forms the tongues of fire light hydrogen in precombustion chamber after, thereby at supersonic speed condition down-firing, realized reliable ignition and the smooth combustion of kerosene under the supersonic speed condition.This plasma igniter volume and weight is bigger, electrode temperature height, nothing cooling, life-span weak point, and also working environment pressure is low, is unsuitable for using in the high temperature and high pressure environment of aeroengine combustor buring chamber.
Summary of the invention
Bigger for overcoming the volume and weight that exists in the prior art, electrode temperature height, nothing cooling, life-span weak point, and working environment pressure is low, be unsuitable for the deficiency in the high temperature and high pressure environment of aeroengine combustor buring chamber, used, the present invention proposes a kind of aeroengine air swirl plasma igniter.
The present invention includes housing, suction tude, anode jacket, insulating bush, negative electrode fitting seat, supporting sleeve, negative electrode and cyclone separator.Wherein, insulating bush and supporting sleeve are installed in the housing.Insulating bush is positioned at described housing internal partition one side; Supporting sleeve is positioned at the opposite side of described housing internal partition, and forms air chamber between the internal surface of the outer surface of this supporting sleeve and housing.Anode jacket is sleeved on the end that housing has supporting sleeve; The endoporus of described anode jacket is divided into linkage section, cyclone separator construction section and contraction section; Cyclone separator is positioned at described anode jacket, and the end face of this cyclone separator contacts with the end face of supporting sleeve.The negative electrode fitting seat is positioned at insulating bush, and the end face of negative electrode fitting seat is contacted with cathode terminal in the concentric cable.The male end of described negative electrode is fixed in the negative electrode fitting seat; Negative electrode passes supporting sleeve and cyclone separator from top to bottom successively, and the arc end of negative electrode stretches out the lower end surface of cyclone separator,
There is the mounting hole of suction tude at described housing middle part, and suction tude one end and housing weld, and are communicated with described air chamber; The other end of suction tude is connected with the motor air feeder by screw thread, and keeps sealing.The axis normal of suction tude and the axis of housing.
The linkage section of described anode jacket is positioned at the open-mouth end of anode jacket, and the internal surface of this connecting end has screw thread.The contraction section of anode jacket is positioned at the other end of this anode jacket, is taper.The axial length of described anode jacket contraction section is 4～8mm, and cone angle is 60～90 °.Described cyclone separator construction section is between linkage section and contraction section.There is spout at the end cap center of anode jacket.The described length that is positioned at anode jacket end cap center nozzle is 6～10mm, and the shape of spout or aperture are the isometrical hole of 2～6mm, or cone angle gamma is 20～50 ° taper diffusion hole.
The internal face of described insulating bush and housing is fitted.The aperture of insulating bush endoporus is identical with the external diameter of negative electrode fitting seat, and makes interference fit between the two, simultaneously the cathode terminal in the concentric cable is installed in this insulating bush.There is the through hole of negative electrode at the end cap center of insulating bush.The mounting groove that supporting sleeve is arranged at the center, exterior edge face of described insulating bush end cap, the diameter of this mounting groove is identical with the external diameter of supporting sleeve.
Described negative electrode fitting seat smaller diameter end is useful on the tapped blind hole that negative electrode is installed.
One end of described supporting sleeve passes the center hole of internal partition, embeds in the groove of insulating bush end face.The other end contacts with the cyclone separator upper surface.The internal diameter of supporting sleeve is identical with the external diameter of negative electrode.
The arc end of described negative electrode is that the cone angle beta of this cone of cone is 40 °.
The through hole that has negative electrode to pass at the center of described cyclone separator is evenly equipped with 3 eddy flow grooves at the outer round surface of cyclone separator, when working medium produces eddy flow during by the eddy flow groove.Described eddy flow groove spiral shell revolve shape along the axial distribution of cyclone separator.The helix angle of eddy flow groove is 45 °.
Among the present invention, housing is connected by anode jacket, the negative electrode of concentric cable respectively at the plasma igniter driving power with the negative electrode fitting seat, working medium gap breakdown between negative electrode lower end striking section and anode jacket forms electric arc, the working medium that high-temperature electric arc heating and ionization are passed through produces the high-temperature plasma tongues of fire.Negative electrode, anode jacket can adopt the metal or alloy that tungsten or tungsten copper etc. are high temperature resistant, conductive capability is strong, and both high temperature resistant arc erosion had stronger electron emissivity again.The negative electrode head is taper, the other end adopts screw thread to be fixed on the negative electrode fitting seat, discharging gap between conveniently adjusted negative electrode and the anode jacket, voltage and current when the breakdown voltage of change plasma igniter and work, the degree of ionization of control arc stiffness and working medium, thereby the high-temperature plasma tongues of fire special parameter (speed, length and temperature etc.) of point of adjustment firearm ejection also is convenient to the replacing of negative electrode in addition.
Plasma igniter adopts the side intake method, is conducive to the vertical length of control point firearm, and insulating bush lower end anti-backflow concave station cooperates with supporting sleeve, and working medium is played airtight effect; Insulating bush, supporting sleeve material are the insulating material that is easy to process, and are used for isolating negative electrode and anode jacket, prevent from producing discharge between other parts, thereby improve capacity usage ratio.
The cyclone separator material is the boron nitride of high temperature resistant and good insulation preformance, working medium produces eddy flow during by the eddy flow groove on the cyclone separator outer surface, the centrifugal force that produces has been formed centrally low pressure area in whirlpool, make arc column and cathode spot very stably remain on axial location, the stability in the time of can improving igniter work.
Working medium of the present invention is air, and source of the gas is available air supply system on the motor, can be the plasma igniter air feed easily, does not need extra air feeder.During plasma igniter work, working medium adopts the plenum system of " walking first ", and gassy between anode jacket and negative electrode is conducive to puncture the starting the arc earlier; After the igniter driving power is closed, continue air feed several seconds, help the cooling of anode jacket and negative electrode in case oxidation.
The present invention does not change structure and the position of the original installation electric spark igniter of engine chamber, design according to existing size and the gabarit that electric spark igniter is installed in firing chamber, run through the motor by-pass air duct, vertically be installed on outer wall of combustion chamber, when not changing firing chamber geometrical construction and dynamics, simplify to make like this and mounting process, and contain air-flow outward and can cool off by article on plasma body igniter.
Description of drawings
Accompanying drawing 1 is the disclosed plasma igniter of U.S. GE company, and wherein Fig. 1 a is plan view, and Fig. 1 b is the partial enlarged drawing of Fig. 1 a;
Accompanying drawing 2 is industrial plasma igniters of DLZ-200 that Longyuan Electric Technology Co., Ltd., Yantai makes;
Accompanying drawing 3 is plasma igniters of Northwestern Polytechnical University and Chinese aerodynamic investigation and centre of development cooperation research and development;
Accompanying drawing 4 is structural representations of the present invention;
Accompanying drawing 5 is structural representations of housing;
Accompanying drawing 6 is structural representations of anode jacket, and wherein, Fig. 6 a is the anode jacket schematic representation of straight-through shape spout, and Fig. 6 b is the anode jacket schematic representation of divergent contour spout;
Accompanying drawing 7 is schematic representation of insulating bush;
Accompanying drawing 8 is schematic representation of negative electrode fitting seat;
Accompanying drawing 9 is schematic representation of negative electrode,
Accompanying drawing 10 is structural representations of cyclone separator, and wherein, Figure 10 a is plan view, and Figure 10 b is plan view.
Among the figure:
1. housing 2. suction tude 3. anode jackets 4. insulating bushs 5. negative electrode fitting seats
6. supporting sleeve 7. negative electrodes 8. cyclone separators
Embodiment
Embodiment one
Present embodiment is a kind of aeroengine combustor buring chamber air swirl plasma jet igniter, comprises housing 1, suction tude 2, anode jacket 3, insulating bush 4, negative electrode fitting seat 5, supporting sleeve 6, negative electrode 7 and cyclone separator 8.Wherein, insulating bush 4 and supporting sleeve 6 are installed in the housing 1.Described insulating bush 4 is positioned at internal partition one side of this housing, and interference fit between insulating bush 4 and the housing 1; Described supporting sleeve 6 is positioned at the opposite side of the internal partition of this housing, and forms air chamber between the internal surface of the outer surface of this supporting sleeve 6 and housing 1.One end of supporting sleeve 6 passes the center hole of internal partition, embeds in the groove of insulating bush 4 end faces.Anode jacket 3 has on the shell of supporting sleeve one end at housing 1 by thread set.Cyclone separator 8 is positioned at described anode jacket 3, and these cyclone separator 8 one end end faces contact with the end face of supporting sleeve 6 the other ends.Negative electrode fitting seat 5 is positioned at insulating bush 4.Negative electrode 7 is installed in the supporting sleeve 6, and an end is fixed in the negative electrode fitting seat 5, and the other end is positioned at cyclone separator 8.
Described anode jacket 3, insulating bush 4, negative electrode fitting seat 5, supporting sleeve 6, negative electrode 7 and cyclone separator 8 are coaxial.
Described housing 1 is the hollow solid of rotation, adopts stainless steel to make.There is internal partition at middle part at housing 1.There is through hole at center at described internal partition, is used for passing supporting sleeve 6.The outer surface of housing 1 is stepped, insulating bush one end surfaces wherein is installed is useful on the outside thread that is connected with concentric cable, housing 1 is connected with concentric cable with swivel nut by this outside thread; One end surfaces of housing 1 mounting support cover 6 also has screw thread, with anode jacket 3 by being threaded.
There is the mounting hole of suction tude 2 at housing 1 middle part, 1 welding of suction tude one end and housing, and be communicated with by the air chamber that forms between supporting sleeve 6 and the housing 1; The other end of suction tude is connected with the motor air feeder by screw thread, and keeps sealing.The axis of the axis normal of suction tude 2 and housing 1.
Insulating bush 4 is the hollow tubular that an end has end cap, adopts insulating property and the good teflon of processibility to make.Described insulating bush 4 is sleeved in the housing 1 and with the internal face of housing and fits.The aperture of insulating bush 4 endoporus is identical with the external diameter of negative electrode fitting seat 5, and makes interference fit between the two, simultaneously the cathode terminal in the concentric cable is installed in this insulating bush 4.There is the through hole of negative electrode 7 at the end cap center of insulating bush 4.The mounting groove that supporting sleeve 6 is arranged at the center, exterior edge face of described insulating bush end cap, the diameter of this mounting groove is identical with the external diameter of supporting sleeve 6, is used for mounting support cover 6 on the one hand, prevents that by this mounting groove the air-flow that suction tude 2 enters from upwards flowing on the other hand.
Negative electrode fitting seat 5 is cylindrical body, is made of copper.The outer round surface of described negative electrode fitting seat 5 is stepped shaft, and its enlarged diameter section is identical with the internal diameter of insulating bush 4.Negative electrode fitting seat 5 is installed in the insulating bush 4, the end face of negative electrode fitting seat 5 is contacted with cathode terminal in the concentric cable, and by the spring compression on the cathode terminal that is sleeved on cathode cable.Negative electrode fitting seat 5 smaller diameter end are useful on the tapped blind hole that negative electrode 7 is installed.
Supporting sleeve 6 is hollow tubular, makes with teflon.Described supporting sleeve 6 one ends cooperate with the supporting section mounting groove at center, insulating bush end cap exterior edge face, and the other end contacts with the cyclone separator upper surface.The external diameter of supporting sleeve 6 is 8mm, and internal diameter is identical with the external diameter of negative electrode 7.
Embodiment two
Present embodiment is a kind of aeroengine combustor buring chamber air swirl plasma jet igniter, comprises housing 1, suction tude 2, anode jacket 3, insulating bush 4, negative electrode fitting seat 5, supporting sleeve 6, negative electrode 7 and cyclone separator 8.Wherein, insulating bush 4 and supporting sleeve 6 are installed in the housing 1.Described insulating bush 4 is positioned at internal partition one side of this housing, and interference fit between insulating bush 4 and the housing 1; Described supporting sleeve 6 is positioned at the opposite side of the internal partition of this housing, and forms air chamber between the internal surface of the outer surface of this supporting sleeve 6 and housing 1.One end of supporting sleeve 6 passes the center hole of internal partition, embeds in the groove of insulating bush 4 end faces.Anode jacket 3 has on the shell of supporting sleeve one end at housing 1 by thread set.Cyclone separator 8 is positioned at described anode jacket 3, and these cyclone separator 8 one end end faces contact with the end face of supporting sleeve 6 the other ends.Negative electrode fitting seat 5 is positioned at insulating bush 4.Negative electrode 7 is installed in the supporting sleeve 6, and an end is fixed in the negative electrode fitting seat 5, and the other end is positioned at cyclone separator 8.
Described anode jacket 3, insulating bush 4, negative electrode fitting seat 5, supporting sleeve 6, negative electrode 7 and cyclone separator 8 are coaxial.
Described housing 1 is the hollow solid of rotation, adopts stainless steel to make.There is internal partition at middle part at housing 1.There is through hole at center at described internal partition, is used for passing supporting sleeve 6.The outer surface of housing 1 is stepped, insulating bush one end surfaces wherein is installed is useful on the outside thread that is connected with concentric cable, housing 1 is connected with concentric cable with swivel nut by this outside thread; One end surfaces of housing 1 mounting support cover 6 also has screw thread, with anode jacket 3 by being threaded.
There is the mounting hole of suction tude 2 at housing 1 middle part, 1 welding of suction tude one end and housing, and be communicated with by the air chamber that forms between supporting sleeve 6 and the housing 1; The other end of suction tude is connected with the motor air feeder by screw thread, and keeps sealing.The axis of the axis normal of suction tude 2 and housing 1.
Insulating bush 4 is that an end has the end cap hollow tubular, adopts insulating property and the good bakelite of processibility to make.Described insulating bush 4 is sleeved in the housing 1 and with the internal face of housing and fits.The aperture of insulating bush 4 endoporus is identical with the external diameter of negative electrode fitting seat 5, and makes interference fit between the two, simultaneously the cathode terminal in the concentric cable is installed in this insulating bush 4.There is the through hole of negative electrode 7 at the end cap center of insulating bush 4.The mounting groove that supporting sleeve 6 is arranged at the center, exterior edge face of described insulating bush end cap, the diameter of this mounting groove is identical with the external diameter of supporting sleeve 6, is used for mounting support cover 6 on the one hand, prevents that by this mounting groove the air-flow that suction tude 2 enters from upwards flowing on the other hand.
Negative electrode fitting seat 5 is cylindrical body, makes with tungsten-copper alloy.The outer round surface of described negative electrode fitting seat 5 is stepped shaft, and its enlarged diameter section is identical with the internal diameter of insulating bush 4.Negative electrode fitting seat 5 is installed in the insulating bush 4, the end face of negative electrode fitting seat 5 is contacted with cathode terminal in the concentric cable, and by the spring compression on the cathode terminal that is sleeved on cathode cable.Negative electrode fitting seat 5 smaller diameter end are useful on the tapped blind hole that negative electrode 7 is installed.
Supporting sleeve 6 is hollow tubular, makes with teflon.Described supporting sleeve 6 one ends cooperate with the supporting section mounting groove at center, insulating bush end cap exterior edge face, and the other end contacts with the cyclone separator upper surface.The external diameter of supporting sleeve 6 is 8mm, and internal diameter is identical with the external diameter of negative electrode 7.
Claims (9)
1. an aeroengine air swirl plasma igniter is characterized in that, comprises housing (1), suction tude (2), anode jacket (3), insulating bush (4), negative electrode fitting seat (5), supporting sleeve (6), negative electrode (7) and cyclone separator (8); Wherein, insulating bush (4) and supporting sleeve (6) are installed in the housing (1); Insulating bush (4) is positioned at described housing internal partition one side; Supporting sleeve (6) is positioned at the opposite side of described housing internal partition, and forms air chamber between the internal surface of the outer surface of this supporting sleeve (6) and housing (1); Anode jacket (3) is sleeved on the end that housing (1) has supporting sleeve; The endoporus of described anode jacket (3) is divided into linkage section, cyclone separator construction section and contraction section; Cyclone separator (8) is positioned at described anode jacket (3), and the end face of this cyclone separator (8) contacts with the end face of supporting sleeve (6); Negative electrode fitting seat (5) is positioned at insulating bush (4), and the end face of negative electrode fitting seat (5) is contacted with cathode terminal in the concentric cable; The male end of described negative electrode (7) is fixed in the negative electrode fitting seat (5); Negative electrode (7) passes supporting sleeve (6) and cyclone separator (8) from top to bottom successively, and the arc end of negative electrode stretches out the lower end surface of cyclone separator (8).
2. a kind of aeroengine air swirl plasma igniter according to claim 1 is characterized in that, there is the mounting hole of suction tude (2) at housing (1) middle part, and suction tude one end welds with housing (1), and is communicated with described air chamber; The other end of suction tude is connected with the motor air feeder by screw thread, and keeps sealing; The axis of the axis normal of suction tude (2) and housing (1).
3. a kind of aeroengine air swirl plasma igniter according to claim 1 is characterized in that the linkage section of described anode jacket (3) is positioned at the open-mouth end of anode jacket (3), and the internal surface of this connecting end has screw thread; The contraction section of anode jacket (3) is positioned at the other end of this anode jacket, is taper; The axial length of described anode jacket contraction section is 4～8mm, and cone angle is 60～90 °; Described cyclone separator construction section is between linkage section and contraction section; There is spout at the end cap center of anode jacket (3).
4. a kind of aeroengine air swirl plasma igniter according to claim 1 is characterized in that, described insulating bush (4) is fitted with the internal face of housing; The aperture of insulating bush (4) endoporus is identical with the external diameter of negative electrode fitting seat (5), and makes interference fit between the two, simultaneously the cathode terminal in the concentric cable is installed in this insulating bush (4); There is the through hole of negative electrode (7) at the end cap center of insulating bush (4); The mounting groove that supporting sleeve (6) are arranged at the center, exterior edge face of described insulating bush end cap, the diameter of this mounting groove is identical with the external diameter of supporting sleeve (6);
5. a kind of aeroengine air swirl plasma igniter according to claim 1 is characterized in that, negative electrode fitting seat (5) smaller diameter end is useful on the tapped blind hole that negative electrode (7) is installed.
6. a kind of aeroengine air swirl plasma igniter according to claim 1 is characterized in that an end of described supporting sleeve (6) passes the center hole of internal partition, embeds in the groove of insulating bush (4) end face; The other end contacts with the cyclone separator upper surface; The internal diameter of supporting sleeve (6) is identical with the external diameter of negative electrode (7).
7. a kind of aeroengine air swirl plasma igniter according to claim 1 is characterized in that the arc end of described negative electrode (7) is that the cone angle beta of this cone of cone is 40 °.
8. a kind of aeroengine air swirl plasma igniter according to claim 1, it is characterized in that, the through hole that has negative electrode (7) to pass at the center of described cyclone separator (8), outer round surface at cyclone separator (8) is evenly equipped with 3 eddy flow grooves, produces eddy flow when working medium passes through the eddy flow groove; Described eddy flow groove spiral shell revolve shape along the axial distribution of cyclone separator (8); The helix angle of eddy flow groove is 45 °.
9. as a kind of aeroengine air swirl plasma igniter as described in the claim 3, it is characterized in that, the described length that is positioned at anode jacket (3) end cap center nozzle is 6～10mm, the shape of spout or aperture are the isometrical hole of 2～6mm, or cone angle gamma is 20～50 ° taper diffusion hole.
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| CN103533737A (en) * | 2013-10-21 | 2014-01-22 | 芜湖鼎恒材料技术有限公司 | Cathode head of plasma spray gun |
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