CN103277231B - A kind of aero-engine air rotational flow plasma igniter - Google Patents
A kind of aero-engine air rotational flow plasma igniter Download PDFInfo
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- CN103277231B CN103277231B CN201310084697.0A CN201310084697A CN103277231B CN 103277231 B CN103277231 B CN 103277231B CN 201310084697 A CN201310084697 A CN 201310084697A CN 103277231 B CN103277231 B CN 103277231B
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Abstract
A kind of aero-engine air rotational flow plasma igniter, insulating bush and supporting sleeve are installed in housing.Insulating bush is positioned at described housing internal partition side, and supporting sleeve is positioned at described housing, and forms air chamber between the outer surface of this supporting sleeve and the internal surface of housing.Anode jacket is sleeved on one end that housing has supporting sleeve.Cyclone separator is positioned at described anode jacket, and the end contact of the end face of this cyclone separator and supporting sleeve.Cathode installation base is positioned at insulating bush, and the end face of cathode installation base is contacted with the cathode terminal in concentric cable.Negative electrode be fixed in cathode installation base, from top to bottom successively through supporting sleeve and cyclone separator, and the arc end of this negative electrode stretches out the lower end surface of cyclone separator.The present invention does not change structure and the position of the original installation electric spark igniter of engine chamber, run through motor by-pass air duct, be installed vertically on outer wall of combustion chamber, improve the reliability of product, have that volume and weight is little, structure is simple, operation and maintenance feature easily.
Description
Technical field
The present invention relates to plasma igniting and the combustion intensification technology in aviation power field, plasma igniter take air as working medium, working medium forms Arc Discharge through high-voltage breakdown, penetrate from igniter spout with the form of high temp jet, form the high temperature tongues of fire, utilize be rich in active particle high temperature, high speed plasma jet to be to light the fuel-air mixture of aeroengine combustor buring indoor.
Background technique
Along with improving constantly of fighter performance, to the starting characteristic of aeroengine combustor buring room at height under motor-driven and aloft work condition with have higher requirement.At present, the high energy ignition unit that domestic and international aeroengine uses adopts semiconductor discharge plug usually, work in severe hot environment for a long time, its characteristic of semiconductor is aging gradually, sparking plug breakdown voltage is more and more higher, exceed the operating voltage of igniter gradually and lost efficacy, the low-frequency high-voltage pulse that ignition mechanism is exported cannot breakdown voltage semiconductor sparking plug, causes a whole set of electric fiery failure of apparatus.In addition, the ignition energy of conventional ignition device is lower, and the aero gas turbine engine of China exists the problem of the ignition limit deficiency in the little indicated airspeed situation in plateau, high/low temperature and high-altitude, conventional ignition system is difficult to meet the needs again started in high-altitude (particularly more than 20km and even near space) engine air.
Plasma-ignition technique has the features such as ignition energy is large, tongues of fire penetrating power is strong, be conducive to improving the reliability of lighting flow at high speed fuel/air mixture mixed gas under harsh environments (near space) condition, expand ignition range, improve the airstart performance of motor.Therefore, carry out the plasma-ignition technique research of aeroengine combustor buring room, be aeroengine development and improve in using its Security, functional reliability in the urgent need to, for the application of plasma-ignition technique in high thrust weight ratio turbofan engine, large power to weight ratio turboshaft engine firing chamber provides technological reserve.
The research of plasma-ignition technique just causes the extensive concern of various countries expert as far back as 20 century 70s.But owing to being subject to the restriction of technical specifications at that time, its research is only limitted to industrial combustion aspect.The mid-80, this technology starts to turn on ground combustion machine and Aero-Space power plant.Particularly along with kinetics of combustion and other high-tech development, plasma-ignition technique is subject to showing great attention to of Aero-Space power circle gradually with its intrinsic feature and significant advantage and payes attention to.In recent years, the large state of World Airways all starts the research carrying out the plasma-ignition technique be applicable in Aeronautics and Astronautics engine chamber and tail pipe burner.The aviation developed countries such as the U.S. and Russia have developed plasma igniter, and in aeroengine, carried out high-altitude ignition demonstration test, and a lot of key technologies of plasma igniting obtain larger development.
1988, Britain RR fuel adding company combustion study room and department of mechanical engineering of University of Leeds utilize AIT altitude simulation unit in motor can annular type combustor, use spark plug boundling discharge plasma igniter successfully to test, and demonstrate feasibility and superior high-altitude reignition capability that this technology applies in aeroengine.1992, GE company of the U.S., motor Compak Systems Ltd. of Siemens, aviation plasma technology company were with the patent (Fig. 1) of aeroengine main combustion chamber or the tail pipe burner plasma igniting system that has been application application., U.S. AppliedPlasmaTechnologies(APT in 2004) IgorMatveev etc. of company carried out the plasma igniting test of 12Km high-altitude to developed plasma igniter, illustrates its good high-altitude ignition performance reliably.
The plasma igniting research of China is started late, technical foundation is weaker, plasma-ignition technique has certain application on civil boiler, ground and naval gas turbine, and the key technology applied in aeroengine combustor buring room need further research.Within 1998, Longyuan Electric Technology Co., Ltd., Yantai produces the industrial plasma ignition device of First DLZ-200 (Fig. 2), and when normal temperature powder feeding, successful ignition fugitive constituent is Zibo meager coal of 11%.Calendar year 2001, Harbin Engineering University assume responsibility for 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 naval gas turbine, and the volume and weight of plasma igniter is comparatively large, and striking mode is the arcing of electrode linear slide, is unsuitable for using in the high temperature and high pressure environment of aeroengine combustor buring room.2006, the Song Wenyan etc. of Northwestern Polytechnical University's power and energy institute cooperates (Fig. 3) with Chinese aerodynamic investigation in scramjet engine firing chamber, has carried out plasma igniting with centre of development, plasma igniter forms the tongues of fire light hydrogen in precombustion chamber after, thus at supersonic speed condition down-firing, achieve the reliable ignition of kerosene under supersonic speed condition and smooth combustion.This plasma igniter body sum weight is comparatively large, and electrode temperature is high, nothing cools, the life-span is short, and working environment pressure is low, is unsuitable for using in the high temperature and high pressure environment of aeroengine combustor buring room.
Summary of the invention
Larger for overcoming the volume and weight existed in prior art, electrode temperature is high, nothing cools, the life-span is short, and working environment pressure is low, be unsuitable for the deficiency used in the high temperature and high pressure environment of aeroengine combustor buring room, the present invention proposes a kind of aero-engine air rotational flow plasma igniter.
The present invention includes housing, suction tude, anode jacket, insulating bush, cathode installation base, supporting sleeve, negative electrode and cyclone separator.Wherein, insulating bush and supporting sleeve are installed in housing.Insulating bush is positioned at described housing internal partition side; Supporting sleeve is positioned at the opposite side of described housing internal partition, and forms air chamber between the outer surface of this supporting sleeve and the internal surface of housing.Anode jacket is sleeved on one 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 contact of the end face of this cyclone separator and supporting sleeve.Cathode installation base is positioned at insulating bush, and the end face of cathode installation base is contacted with the cathode terminal in concentric cable.The male end of described negative electrode is fixed in cathode installation base; Negative electrode is from top to bottom successively through supporting sleeve and cyclone separator, and the arc end of negative electrode stretches out the lower end surface of cyclone separator,
Described housing central section has the mounting hole of suction tude, suction tude one end and case weld, and is communicated with described air chamber; The other end of suction tude is connected with motor air feeder by screw thread, and keeps sealing.The axes 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.The end cap central of anode jacket has spout.The described length being positioned at anode jacket end cap central spout is 6 ~ 10mm, and the shape of spout or aperture are the isometrical hole of 2 ~ 6mm, or cone angle gamma is the taper diffusion hole of 20 ~ 50 °.
The internal face of described insulating bush and housing is fitted.The aperture of insulating bush endoporus is identical with the external diameter of cathode installation base, and makes interference fit between the two, the cathode terminal in concentric cable can be made to be arranged in this insulating bush simultaneously.The end cap central of insulating bush has the through hole of negative electrode.Have the mounting groove of supporting sleeve 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 cathode installation base smaller diameter end has the tapped blind hole for installing negative electrode.
One end of described supporting sleeve, through the center hole of internal partition, embeds in the groove of insulating bush end face.The other end contacts with 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 the cone angle beta of this cone of cone is 40 °.
At the through hole that the center of described cyclone separator has negative electrode to pass, be evenly equipped with 3 eddy flow grooves at the outer round surface of cyclone separator, when working medium is by producing eddy flow during eddy flow groove.Described eddy flow groove spiral shell revolve the axial distribution of shape along cyclone separator.The helix angle of eddy flow groove is 45 °.
In the present invention, housing and cathode installation base are connected respectively at the anode jacket of plasma igniter driving power, negative electrode by concentric cable, working medium holds gap breakdown between striking section and anode jacket to form electric arc under the cathode, high-temperature electric arc heats and ionizes the working medium passed through, and 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, both high temperature resistant arc erosion, have again stronger electron emissivity.Negative electrode head is taper, the other end adopts screw thread to be fixed in cathode installation base, discharging gap between conveniently adjusted negative electrode and positive electrode cover, change voltage and current during breakdown voltage and the work of plasma igniter, control the degree of ionization of arc stiffness and working medium, thus the high-temperature plasma tongues of fire special parameter (speed, length and temperature etc.) of point of adjustment firearm ejection, be also convenient to the replacing of negative electrode in addition.
Plasma igniter adopts side intake method, and be conducive to the vertical length of control point firearm, insulating bush lower end anti-backflow concave station coordinates with supporting sleeve, plays airtight effect to working medium; Insulating bush, supporting sleeve material are the insulating material being easy to process, and are used for isolating negative electrode and anode jacket, prevent from producing electric discharge between other parts, thus improve capacity usage ratio.
Cyclone separator material is high temperature resistant and the boron nitride of good insulation preformance, working medium produces eddy flow when passing through the eddy flow groove on cyclone separator outer surface, the centrifugal force produced defines low pressure area at whirlpool center, make arc column and cathode spot very stably remain on axial location, stability during igniter work can be improved.
Working medium of the present invention is air, and source of the gas is available air supply system on motor, can be plasma igniter air feed easily, not need extra air feeder.During plasma igniter work, working medium adopts the plenum system of " walking afterwards first ", and first gassy between anode jacket and negative electrode, is conducive to puncturing the starting the arc; After igniter driving power is closed, continue air feed a few second, contribute to 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 the size of the existing installation electric spark igniter in firing chamber and gabarit, run through motor by-pass air duct, be installed vertically on outer wall of combustion chamber, simplify while not changing firing chamber geometrical construction and dynamics like this and make and mounting process, and outer air-flow of containing can cool by plasma igniter.
Accompanying drawing explanation
Accompanying drawing 1 is plasma igniter disclosed in GE company of the U.S., 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 manufactures;
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 diagram of straight-through shape spout, and Fig. 6 b is the anode jacket schematic diagram of divergent contour spout;
Accompanying drawing 7 is schematic diagram of insulating bush;
Accompanying drawing 8 is schematic diagram of cathode installation base;
Accompanying drawing 9 is schematic diagram 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.
In figure:
1. housing 2. suction tude 3. anode jacket 4. insulating bush 5. cathode installation base
6. supporting sleeve 7. negative electrode 8. cyclone separator
Embodiment
Embodiment one
The present embodiment is a kind of aeroengine combustor buring room air swirl plasma jet igniter, comprises housing 1, suction tude 2, anode jacket 3, insulating bush 4, cathode installation base 5, supporting sleeve 6, negative electrode 7 and cyclone separator 8.Wherein, insulating bush 4 and supporting sleeve 6 are installed in housing 1.Described insulating bush 4 is positioned at the internal partition side of this housing, and interference fit between insulating bush 4 and 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, through the center hole of internal partition, embeds in the groove of insulating bush 4 end face.Anode jacket 3 is had 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 the end contact of this cyclone separator 8 one end end face and supporting sleeve 6 the other end.Cathode installation base 5 is positioned at insulating bush 4.Negative electrode 7 is arranged in supporting sleeve 6, and one end is fixed in cathode installation base 5, and the other end is positioned at cyclone separator 8.
Described anode jacket 3, insulating bush 4, cathode installation base 5, supporting sleeve 6, negative electrode 7 and cyclone separator 8 are coaxial.
Described housing 1 is hollow solid of rotation, adopts stainless steel to make.Internal partition is had at the middle part of housing 1.Through hole is had, for passing supporting sleeve 6 at the center of described internal partition.The outer surface of housing 1 is stepped, and wherein installing insulating cover end surface has the outside thread for being connected with concentric cable, is connected by housing 1 by this outside thread swivel nut with concentric cable; The end surface that housing 1 installs supporting sleeve 6 also has screw thread, is threaded connection with anode jacket 3.
Have the mounting hole of suction tude 2 in the middle part of housing 1, suction tude one end is welded with housing 1, and is communicated with by the air chamber formed between supporting sleeve 6 with housing 1; The other end of suction tude is connected with motor air feeder by screw thread, and keeps sealing.The axes normal of suction tude 2 and the axis of housing 1.
Anode jacket 3 is made with tungsten-copper alloy, for there is the hollow solid of rotation of end cap one end.The endoporus of anode jacket 3 is divided into construction section and the contraction section of linkage section, cyclone separator.Described linkage section is positioned at the open-mouth end of anode jacket 3, and the internal surface of this connecting end has screw thread, for by described anode jacket 3 and being threaded on housing 1.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 °.In the present embodiment, the axial length of anode jacket 3 contraction section is 4mm, and cone angle is 76 °.The construction section of described cyclone separator is between linkage section and contraction section.The end cap central of anode jacket 3 one end has clear opening, and this clear opening defines the spout of anode jacket 3.The diameter of this spout is 2 ~ 6mm, and length is 6 ~ 10mm.In the present embodiment, the nozzle diameter of anode jacket 3 is 4mm, and length is 8mm.
Insulating bush 4 has the hollow tubular of end cap for one end, adopts insulating property and the good teflon of processibility to make.Described insulating bush 4 is set with within the case 1 and fits with the internal face of housing.The aperture of insulating bush 4 endoporus is identical with the external diameter of cathode installation base 5, and makes interference fit between the two, the cathode terminal in concentric cable can be made to be arranged in this insulating bush 4 simultaneously.The end cap central of insulating bush 4 has the through hole of negative electrode 7.Have the mounting groove of supporting sleeve 6 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, and on the one hand for installing supporting sleeve 6, the air-flow preventing suction tude 2 from entering by this mounting groove on the other hand upwards flows.
Cathode installation base 5 is cylindrical body, is made of copper.The outer round surface of described cathode installation base 5 is stepped shaft, and its enlarged diameter section is identical with the internal diameter of insulating bush 4.Cathode installation base 5 is arranged in insulating bush 4, the end face of cathode installation base 5 is contacted with the cathode terminal in concentric cable, and by being sleeved on the spring compression on the cathode terminal of cathode cable.Cathode installation base 5 smaller diameter end has the tapped blind hole for installing negative electrode 7.
Supporting sleeve 6 is hollow tubular, makes with teflon.Described supporting sleeve 6 one end coordinates with the supporting section mounting groove at center, insulating bush end cap exterior edge face, and the other end contacts with 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.
Negative electrode 7 is shaft-like, makes with tungsten.One end of described negative electrode 7 has length to be the screw thread of 20mm, and the other end head is cone, is the arc end of negative electrode, and the cone angle beta of this cone is 40 °.Negative electrode 7 is from top to bottom successively through supporting sleeve 6, cyclone separator 8, and arc end stretches out in the lower end surface of cyclone separator 8, and the length of stretching out adjusts by the screw thread of negative electrode 7 the other end.Space between negative electrode arc end and anode jacket contraction section internal surface is discharging gap, when working medium is by this space, produces electric discharge through high-voltage breakdown.
Cyclone separator 8 is solid of rotation, adopts high temperature resistant, insulating property good and the boron nitride of processibility excellence is made.At the through hole that the center of described cyclone separator 8 has negative electrode 7 to pass, be evenly equipped with 3 eddy flow grooves at the outer round surface of cyclone separator 8, when working medium is by producing eddy flow during eddy flow groove.Described eddy flow groove spiral shell revolve the axial distribution of shape along cyclone separator 8.The helix angle of eddy flow groove is 45 °.
Embodiment two
The present embodiment is a kind of aeroengine combustor buring room air swirl plasma jet igniter, comprises housing 1, suction tude 2, anode jacket 3, insulating bush 4, cathode installation base 5, supporting sleeve 6, negative electrode 7 and cyclone separator 8.Wherein, insulating bush 4 and supporting sleeve 6 are installed in housing 1.Described insulating bush 4 is positioned at the internal partition side of this housing, and interference fit between insulating bush 4 and 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, through the center hole of internal partition, embeds in the groove of insulating bush 4 end face.Anode jacket 3 is had 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 the end contact of this cyclone separator 8 one end end face and supporting sleeve 6 the other end.Cathode installation base 5 is positioned at insulating bush 4.Negative electrode 7 is arranged in supporting sleeve 6, and one end is fixed in cathode installation base 5, and the other end is positioned at cyclone separator 8.
Described anode jacket 3, insulating bush 4, cathode installation base 5, supporting sleeve 6, negative electrode 7 and cyclone separator 8 are coaxial.
Described housing 1 is hollow solid of rotation, adopts stainless steel to make.Internal partition is had at the middle part of housing 1.Through hole is had, for passing supporting sleeve 6 at the center of described internal partition.The outer surface of housing 1 is stepped, and wherein installing insulating cover end surface has the outside thread for being connected with concentric cable, is connected by housing 1 by this outside thread swivel nut with concentric cable; The end surface that housing 1 installs supporting sleeve 6 also has screw thread, is threaded connection with anode jacket 3.
Have the mounting hole of suction tude 2 in the middle part of housing 1, suction tude one end is welded with housing 1, and is communicated with by the air chamber formed between supporting sleeve 6 with housing 1; The other end of suction tude is connected with motor air feeder by screw thread, and keeps sealing.The axes normal of suction tude 2 and the axis of housing 1.
Anode jacket 3 is made with tungsten-molybdenum alloy, for there is the hollow solid of rotation of end cap one end.The endoporus of anode jacket 3 is divided into construction section and the contraction section of linkage section, cyclone separator.Described linkage section is positioned at the open-mouth end of anode jacket 3, and the internal surface of this connecting end has screw thread, for by described anode jacket 3 and being threaded on housing 1.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 °.In the present embodiment, the axial length of anode jacket 3 contraction section is 6mm, and cone angle is 85 °.The construction section of described cyclone separator is between linkage section and contraction section.The end cap central of anode jacket 3 one end has taper diffusion hole, and this taper diffusion hole defines the spout of anode jacket 3.The axial length of this spout is 6 ~ 10mm, and cone angle gamma is 20 ~ 50 °.In the present embodiment, the axial length of the spout of anode jacket 3 is 10mm, and cone angle gamma is 30 °.
Insulating bush 4 has end cap hollow tubular for one end, adopts insulating property and the good bakelite of processibility to make.Described insulating bush 4 is set with within the case 1 and fits with the internal face of housing.The aperture of insulating bush 4 endoporus is identical with the external diameter of cathode installation base 5, and makes interference fit between the two, the cathode terminal in concentric cable can be made to be arranged in this insulating bush 4 simultaneously.The end cap central of insulating bush 4 has the through hole of negative electrode 7.Have the mounting groove of supporting sleeve 6 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, and on the one hand for installing supporting sleeve 6, the air-flow preventing suction tude 2 from entering by this mounting groove on the other hand upwards flows.
Cathode installation base 5 is cylindrical body, makes with tungsten-copper alloy.The outer round surface of described cathode installation base 5 is stepped shaft, and its enlarged diameter section is identical with the internal diameter of insulating bush 4.Cathode installation base 5 is arranged in insulating bush 4, the end face of cathode installation base 5 is contacted with the cathode terminal in concentric cable, and by being sleeved on the spring compression on the cathode terminal of cathode cable.Cathode installation base 5 smaller diameter end has the tapped blind hole for installing negative electrode 7.
Supporting sleeve 6 is hollow tubular, makes with teflon.Described supporting sleeve 6 one end coordinates with the supporting section mounting groove at center, insulating bush end cap exterior edge face, and the other end contacts with 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.
Negative electrode 7 is shaft-like, makes with tungsten.One end of described negative electrode 7 has length to be the screw thread of 20mm, and the other end head is cone, is the arc end of negative electrode, and the cone angle beta of this cone is 40 °.Negative electrode 7 is from top to bottom successively through supporting sleeve 6, cyclone separator 8, and arc end stretches out in the lower end surface of cyclone separator 8, and the length of stretching out adjusts by the screw thread of negative electrode 7 the other end.Space between negative electrode arc end and anode jacket contraction section internal surface is discharging gap, when working medium is by this space, produces electric discharge through high-voltage breakdown.
Cyclone separator 8 is solid of rotation, adopts high temperature resistant, insulating property good and the boron nitride of processibility excellence is made.At the through hole that the center of described cyclone separator 8 has negative electrode 7 to pass, be evenly equipped with 3 eddy flow grooves at the outer round surface of cyclone separator 8, when working medium is by producing eddy flow during eddy flow groove.Described eddy flow groove spiral shell revolve the axial distribution of shape along cyclone separator 8.The helix angle of eddy flow groove is 45 °.
Claims (7)
1. an aero-engine air rotational flow plasma igniter, it is characterized in that, comprise housing (1), suction tude (2), anode jacket (3), insulating bush (4), cathode installation base (5), supporting sleeve (6), negative electrode (7) and cyclone separator (8); Wherein, insulating bush (4) and supporting sleeve (6) are installed in housing (1); Insulating bush (4) is positioned at described housing internal partition 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 one 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 contact of the end face of this cyclone separator (8) and supporting sleeve (6); 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; The end cap central of anode jacket (3) has spout, and the shape of spout or aperture are the isometrical hole of 2 ~ 6mm, or cone angle gamma is the taper diffusion hole of 20 ~ 50 °;
Cathode installation base (5) is positioned at insulating bush (4), and the end face of cathode installation base (5) is contacted with the cathode terminal in concentric cable; The male end of described negative electrode (7) is fixed in cathode installation base (5); Negative electrode (7) is from top to bottom successively through supporting sleeve (6) and cyclone separator (8), and the arc end of negative electrode stretches out the lower end surface of cyclone separator (8); The arc end of described negative electrode (7) is the cone angle beta of this cone of cone is 40 °;
The eddy flow groove that 3 helix angles are 45 ° is evenly equipped with, when working medium is by producing eddy flow during eddy flow groove at the outer round surface of described cyclone separator (8); Described eddy flow groove spiral shell revolve the axial distribution of shape along cyclone separator (8).
2. a kind of aero-engine air rotational flow plasma igniter as claimed in claim 1, it is characterized in that, there is the mounting hole of suction tude (2) at housing (1) middle part, and suction tude one end is welded with housing (1), and is communicated with described air chamber; The other end of suction tude is connected with motor air feeder by screw thread, and keeps sealing; The axes normal of suction tude (2) and the axis of housing (1).
3. a kind of aero-engine air rotational flow plasma igniter as claimed in 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 cathode installation base (5), and makes interference fit between the two, the cathode terminal in concentric cable can be made to be arranged in this insulating bush (4) simultaneously; The end cap central of insulating bush (4) has the through hole of negative electrode (7); Have the mounting groove of supporting sleeve (6) 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).
4. a kind of aero-engine air rotational flow plasma igniter as claimed in claim 1, it is characterized in that, cathode installation base (5) smaller diameter end has the tapped blind hole for installing negative electrode (7).
5. a kind of aero-engine air rotational flow plasma igniter as claimed in claim 1, is characterized in that, one end of described supporting sleeve (6), through the center hole of internal partition, embeds in the groove of insulating bush (4) end face; The other end contacts with cyclone separator upper surface; The internal diameter of supporting sleeve (6) is identical with the external diameter of negative electrode (7).
6. a kind of aero-engine air rotational flow plasma igniter as claimed in claim 1, is characterized in that, the through hole having negative electrode (7) to pass at the center of described cyclone separator (8).
7. a kind of aero-engine air rotational flow plasma igniter as claimed in claim 1, is characterized in that, described in be positioned at anode jacket (3) end cap central spout length be 6 ~ 10mm.
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| CN201310084697.0A CN103277231B (en) | 2013-03-18 | 2013-03-18 | A kind of aero-engine air rotational flow plasma igniter |
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| CN110145400B (en) * | 2019-05-21 | 2022-12-13 | 大连民族大学 | Dual-mode plasma igniter |
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| GB1131042A (en) * | 1965-01-21 | 1968-10-16 | Ass Elect Ind | Improvements in or relating to ignition torches |
| US4692584A (en) * | 1985-11-29 | 1987-09-08 | Caneer Jr Clifford | Gas control system for a plasma arc welding apparatus |
| WO1992020913A1 (en) * | 1991-05-15 | 1992-11-26 | Olin Corporation | Plasma ignition apparatus and method for enhanced combustion and flameholding in engine combustion chambers |
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| CN103277231A (en) | 2013-09-04 |
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