CN103104575A - Electric arc type discharging plasma vortex generator - Google Patents
Electric arc type discharging plasma vortex generator Download PDFInfo
- Publication number
- CN103104575A CN103104575A CN2013100195147A CN201310019514A CN103104575A CN 103104575 A CN103104575 A CN 103104575A CN 2013100195147 A CN2013100195147 A CN 2013100195147A CN 201310019514 A CN201310019514 A CN 201310019514A CN 103104575 A CN103104575 A CN 103104575A
- Authority
- CN
- China
- Prior art keywords
- vortex generator
- insulation cavity
- arc type
- aircraft
- electric arc
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Plasma Technology (AREA)
Abstract
The invention discloses an electric arc type discharging plasma vortex generator. The electric arc type discharging plasma vortex generator comprises an insulating heat-insulation cavity 3, wherein an opening is formed in the central position of the bottom of the insulating heat-insulation cavity 3, a jet flow outlet 1 is formed in the central position of the top of the insulating heat-insulation cavity 3, an inclination angle theta is formed between the jet flow outlet 1 and the horizontal direction, a circular-ring-shaped bare electrode 2 is laid on the upper surface of the top of the insulating heat-insulation cavity 3, the circle center of the circular-ring-shaped bare electrode 2 coincides with the jet flow outlet 1, and a needle-point-shaped electrode 4 is arranged at the bottom opening and extends into the insulating heat-insulation cavity 3 through the opening. According to the electric arc type discharging plasma vortex generator, the flowing of a boundary layer of an aircraft can be controlled, additional resistance is not generated at the same time, the performance of the aircraft is not affected, and meanwhile, an additional air source is not needed, and the weight of the aircraft is not increased.
Description
Technical field
The present invention relates to a kind of flow control apparatus, belong to the fluid control technology field, be applicable to aviation, vessel traffic, metallurgy and chemical field.
Background technique
Vortex generator has been widely used in the fields such as aviation, fluid machinery, chemical metallurgy, automobile boats and ships up till now since nineteen forty-seven is suggested first.Vortex generator is actually with a certain established angle and vertically is arranged on the little wing of low aspect ratio on body surface, so it is can produce wing tip whirlpool the same as conventional wing in windstream, because its aspect ratio is less, the intensity in wing tip whirlpool is relatively strong, after mix with the low-energy boundary layer air in its downstream is mobile in this high-octane wing tip whirlpool, just energy is passed to the boundary layer, make the boundary layer flow field that is in adverse pressure gradient obtain to continue to be attached to body surface and unlikely separation after additional-energy.
At present, vortex generator commonly used is divided into passive-type and active.Most widely used in passive-type is the vortex generator of solid type, this type of vortex generator is arranged on special position for delaying the separation of boundary layer under particular case, play the effect of lift-rising drag reduction, in the situation of flow separation, the passive type vortex generator can increase extra form drag but ought not exist, also may shine into other materials adheres to, as dust accretion, easier accumulated ice has significantly reduced the proper property of aircraft.
Active vortex generator is to be often referred to eddy current to penetrate pipe (vortex generator jet), easily producing a distance, flow separation regions the place ahead, the pipe of penetrating of specific caliber, specific yaw angle (and between main flow direction angle), particular pitch angle, specific effluxvelocity (with mainstream speed ratio) is installed, according to runnability, can regulate eddy current and penetrate pipe jet speed, reach the purpose of rationally utilizing vortex generator to control flow separation.
Compare with the solid vortex generator potentiality that the eddy spray pipe has the active Flow Control of realizing.Can be along with the variation of flowing state is in time adjusted, it is a kind of control strategy very flexibly, control the intensity of bringing out the whirlpool by regulating valve, under suitable flox condition, as long as control when separating stall that to close injection pipe when not needing to implement just passable.Adopt the eddy current jet pipe can not resemble and produce drag losses the solid vortex generator.Need to provide source of the gas but eddy current is penetrated pipe usually, increase undoubtedly the weight of aircraft or aircraft, reduce the useful load of aircraft.
Summary of the invention
Technical problem to be solved by this invention be to provide a kind of can be when controlling the aircraft boundary layer and flowing, do not produce extra resistance, do not affect the performance of aircraft, do not need extra source of the gas simultaneously, do not increase the arc type discharge plasma vortex generator of the weight of aircraft.
the present invention adopts following technological scheme to solve the problems of the technologies described above: the present invention has designed a kind of arc type discharge plasma vortex generator, described vortex generator is made of a heat insulation cavity 3 of insulation, the bottom center position of the heat insulation cavity 3 of described insulation has an opening, the top center position of the heat insulation cavity 3 of described insulation has one and is the jet exit 1 of tilt angle theta with substantially horizontal, the top upper surface of the heat insulation cavity 3 of described insulation is equipped with circular bare electrode 2, the center of circle of described circular bare electrode 2 overlaps with jet exit 1, described bottom opening is provided with needlepoint shape electrode 4, described needlepoint shape electrode 4 is stretched in the heat insulation cavity 3 of insulation by opening part.
As a kind of optimizing structure of the present invention: described jet exit 1 is 30 ° to 90 ° with the tilt angle theta of substantially horizontal.
The present invention compared with prior art has following advantage:
1. the present invention by the compression to air in cavity, produces periodically jet, and three-dimensional Plasma Vortex flow-generator is than the more high efficiency jet of plasma generation of two dimension, thereby the control effect of stream field is also stronger;
2. the present invention can not produce extra resistance when controlling the aircraft boundary layer, does not affect the performance of aircraft yet, nor needs extra source of the gas, does not increase the weight of aircraft;
3. using plasma vortex generator of the present invention can be in place, the suitable time, realizes the ACTIVE CONTROL to boundary layer.
Description of drawings
Fig. 1 is the designed arc type discharge plasma vortex generator performance parameter schematic diagram of the present invention;
Fig. 2 is the top plan of the designed arc type discharge plasma vortex generator of the present invention;
Fig. 3 is the side sectional view of the designed arc type discharge plasma vortex generator of the present invention.
1-jet exit, the circular bare electrode of 2-, the 3-heat insulation cavity that insulate, 4-needlepoint shape electrode.
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing:
as shown in Figure 2, the present invention has designed a kind of arc type discharge plasma vortex generator, described vortex generator is made of a heat insulation cavity 3 of insulation, the bottom center position of the heat insulation cavity 3 of described insulation has an opening, the top center position of the heat insulation cavity 3 of described insulation has one and is the jet exit 1 of tilt angle theta with substantially horizontal, the top upper surface of the heat insulation cavity 3 of described insulation is equipped with circular bare electrode 2, the center of circle of described circular bare electrode 2 overlaps with jet exit 1, described bottom opening is provided with needlepoint shape electrode 4, described needlepoint shape electrode 4 is stretched in the heat insulation cavity 3 of insulation by opening part.
working principle of the present invention is: the heat insulation cavity 3 bottoms laying needlepoint shape electrodes 4 that insulate are as anode, circular bare electrode 2 is laid as negative electrode in the top, the top center position has one and is the jet exit 1 of tilt angle theta with substantially horizontal, the tilt angle theta here affects eddy current to the control effect of boundary layer, its size can make the boundary layer thickness attenuate of the required scope in downstream be as the criterion with the intensity that produces the whirlpool, the whirlpool of the too large generation of inclination angle [theta] is with very fast fragmentation, can not facilitate the main flow of whole control area and the Momentum Transfer of boundary layer inner fluid, and main flow is disturbed strengthened, the strength of vortex of the too little generation of inclination angle [theta] is inadequate, can not play due effect,
Pore size also will affect the control effect, if the aperture not only needs very strong energy to produce plasma jet too greatly, the aperture is too little, and is inadequate on the impact of boundary layer again.
add pulse or ac high voltage source between negative electrode and anode electrode, when voltage rises to the breakdown voltage of gas, cloudy, form Arc Discharge between positive electrode, electric arc is to the gas rapid heating in the heat insulation cavity 3 that insulate, and follow temperature to raise, heat insulation cavity 3 internal pressures that insulate sharply increase, thereby force the gas in the heat insulation cavity 3 of insulation to spray at a high speed, can produce high-intensity jet, the interior air pressure of heat insulation cavity 3 that insulate afterwards reduces, thereby suction ambient air, begin the next jet cycle, by controlling size and the angle of inclination in aperture, form vortex generating means, the Plasma Vortex flow-generator can be when control aircraft boundary layer flows, do not produce extra resistance, do not affect the performance of aircraft yet, nor need extra source of the gas, do not increase the weight of aircraft, the using plasma vortex generator, can be in place, time, the ACTIVE CONTROL that realization is flowed to boundary layer.
In specific embodiment, apply the high-tension electricities such as high-frequency direct-current, interchange, pulse between nose-circle ring-type bare electrode 2 and bottom needlepoint shape electrode 4, the cycle of pulse discharge can be from psec (pm) to millisecond (ms), and voltage magnitude is greater than 2000 volts.
Be illustrated in figure 1 as the designed arc type discharge plasma vortex generator performance parameter schematic diagram of the present invention, in specific embodiment, the angle θ of jet exit (1) and substantially horizontal sets according to actual conditions, generally (θ=α) herein between 30 °～90 °; The β angle also can be adjustable as required, and scope is between 0 °～90 °.
Claims (2)
1. arc type discharge plasma vortex generator, it is characterized in that: described vortex generator is made of a heat insulation cavity of insulation (3), the bottom center position of the heat insulation cavity of described insulation (3) has an opening, the top center position of the heat insulation cavity of described insulation (3) has one and is the jet exit (1) of angle of inclination (θ) with substantially horizontal, the top upper surface of the heat insulation cavity of described insulation (3) is equipped with circular bare electrode (2), the center of circle of described circular bare electrode (2) overlaps with jet exit (1), described bottom opening is provided with needlepoint shape electrode (4), described needlepoint shape electrode (4) is stretched in the heat insulation cavity of insulation (3) by opening part.
2. arc type discharge plasma vortex generator according to claim 1 is characterized in that: described jet exit (1) is 30 ° to 90 ° with the angle of inclination (θ) of substantially horizontal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013100195147A CN103104575A (en) | 2013-01-21 | 2013-01-21 | Electric arc type discharging plasma vortex generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013100195147A CN103104575A (en) | 2013-01-21 | 2013-01-21 | Electric arc type discharging plasma vortex generator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103104575A true CN103104575A (en) | 2013-05-15 |
Family
ID=48312690
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013100195147A Pending CN103104575A (en) | 2013-01-21 | 2013-01-21 | Electric arc type discharging plasma vortex generator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103104575A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103501572A (en) * | 2013-10-11 | 2014-01-08 | 中国航空工业集团公司哈尔滨空气动力研究所 | Jet-type plasma actuator and flow control method thereof |
| CN104202898A (en) * | 2014-07-09 | 2014-12-10 | 中国人民解放军国防科学技术大学 | Hypersonic speed flowing energy utilization based zero-energy-consumption zero-mass synthetic jet device |
| CN106394875A (en) * | 2016-10-10 | 2017-02-15 | 南京航空航天大学 | Spark synthesized jet flow exciter based on electromagnetic valve and control method thereof |
| CN111790334A (en) * | 2016-01-05 | 2020-10-20 | 螺旋株式会社 | Vortex flow generator, water plasma generating device, and decomposition processing device |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4764656A (en) * | 1987-05-15 | 1988-08-16 | Browning James A | Transferred-arc plasma apparatus and process with gas heating in excess of anode heating at the workpiece |
| JPH04262398A (en) * | 1991-02-18 | 1992-09-17 | Mitsubishi Heavy Ind Ltd | Arc moving type heat plasma jet generating device |
| CN101754562A (en) * | 2008-12-01 | 2010-06-23 | 财团法人工业技术研究院 | Atmospheric plasma generating device with function of electric arc control |
| CN201635775U (en) * | 2009-10-21 | 2010-11-17 | 南京航空航天大学 | Reverse vortex generator capable of suppressing airflow leakage of impeller tip |
| CN102063103A (en) * | 2009-11-17 | 2011-05-18 | 泰勒斯公司 | Device for monitoring the correct operation of a plurality of devices, in particular actuators |
| WO2011092429A1 (en) * | 2010-01-27 | 2011-08-04 | Centre National De La Recherche Scientifique - Cnrs | Method and device for adjusting the mass flow rate of a gas stream |
| CN102625557A (en) * | 2012-03-30 | 2012-08-01 | 大连理工大学 | Generating device for atmospheric bare electrode cold plasma jet |
-
2013
- 2013-01-21 CN CN2013100195147A patent/CN103104575A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4764656A (en) * | 1987-05-15 | 1988-08-16 | Browning James A | Transferred-arc plasma apparatus and process with gas heating in excess of anode heating at the workpiece |
| JPH04262398A (en) * | 1991-02-18 | 1992-09-17 | Mitsubishi Heavy Ind Ltd | Arc moving type heat plasma jet generating device |
| CN101754562A (en) * | 2008-12-01 | 2010-06-23 | 财团法人工业技术研究院 | Atmospheric plasma generating device with function of electric arc control |
| CN201635775U (en) * | 2009-10-21 | 2010-11-17 | 南京航空航天大学 | Reverse vortex generator capable of suppressing airflow leakage of impeller tip |
| CN102063103A (en) * | 2009-11-17 | 2011-05-18 | 泰勒斯公司 | Device for monitoring the correct operation of a plurality of devices, in particular actuators |
| WO2011092429A1 (en) * | 2010-01-27 | 2011-08-04 | Centre National De La Recherche Scientifique - Cnrs | Method and device for adjusting the mass flow rate of a gas stream |
| CN102625557A (en) * | 2012-03-30 | 2012-08-01 | 大连理工大学 | Generating device for atmospheric bare electrode cold plasma jet |
Non-Patent Citations (1)
| Title |
|---|
| 史志伟等: "《不同结构等离子体激励器的流场特性实验研究》", 《航空学报》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103501572A (en) * | 2013-10-11 | 2014-01-08 | 中国航空工业集团公司哈尔滨空气动力研究所 | Jet-type plasma actuator and flow control method thereof |
| CN103501572B (en) * | 2013-10-11 | 2017-04-19 | 中国航空工业集团公司哈尔滨空气动力研究所 | Jet-type plasma actuator and flow control method thereof |
| CN104202898A (en) * | 2014-07-09 | 2014-12-10 | 中国人民解放军国防科学技术大学 | Hypersonic speed flowing energy utilization based zero-energy-consumption zero-mass synthetic jet device |
| CN104202898B (en) * | 2014-07-09 | 2016-05-11 | 中国人民解放军国防科学技术大学 | The zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy |
| CN111790334A (en) * | 2016-01-05 | 2020-10-20 | 螺旋株式会社 | Vortex flow generator, water plasma generating device, and decomposition processing device |
| CN111790334B (en) * | 2016-01-05 | 2021-12-03 | 螺旋株式会社 | Vortex flow generator, water plasma generating device, and decomposition processing device |
| CN106394875A (en) * | 2016-10-10 | 2017-02-15 | 南京航空航天大学 | Spark synthesized jet flow exciter based on electromagnetic valve and control method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2016127932A1 (en) | Thermal protection and drag reduction method and system for ultra high-speed aircraft | |
| CN103104575A (en) | Electric arc type discharging plasma vortex generator | |
| CN109665093B (en) | Wing profile capable of delaying flow separation and exciter arranged on wing profile | |
| CN103482055B (en) | Device for active control method for aerofoil drag reduction | |
| CN107914865B (en) | Plasma virtual dynamic bionic device and method for wing leading edge | |
| CN104330519B (en) | A kind of particle pneumatic floating laser ignition experimental provision | |
| CN103089760A (en) | Dielectric barrier discharge plasma body vortex generator | |
| CN203081914U (en) | Dielectric battier discharge plasma vortex generator | |
| CN103661929A (en) | Plasma unmanned aerial vehicle | |
| CN103437911B (en) | Band dividing plate fluid controls dual vector jet pipe and vectored thrust produces and controlling method | |
| CN103501572B (en) | Jet-type plasma actuator and flow control method thereof | |
| CN103523208A (en) | Method for controlling plasma flow of wing lift-rising apparatus | |
| CN106640568A (en) | Bipolar solid ablation type plasma accelerator | |
| CN102943751A (en) | Quick-response direct force generating device | |
| CN109618481A (en) | The plasma synthesis jet-flow excitor of low reynolds number condition | |
| CN108811289A (en) | A kind of dynamic pressure type plasma synthesis fluidic generator | |
| CN102660784B (en) | Bubble electrostatic spinning device | |
| CN101913426B (en) | Device and method for suppressing wingtip vortex | |
| CN117326045A (en) | Heat reducing structure and heat reducing method for supersonic or hypersonic aircraft | |
| CN208029170U (en) | Bilateral sliding pulse Plasma Actuator | |
| CN109413831B (en) | Plasma synthesis jet generator capable of controlling temperature in cavity and application thereof | |
| JP2014214851A (en) | Surface flow control system and surface flow control method | |
| CN203830730U (en) | Atomizer for preparing zinc powder | |
| CN114110664B (en) | Plasma synthetic jet combustion chamber | |
| CN206171797U (en) | Spark type synthetic jet energizer based on solenoid valve |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130515 |