CN203081914U - Dielectric battier discharge plasma vortex generator - Google Patents
Dielectric battier discharge plasma vortex generator Download PDFInfo
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- CN203081914U CN203081914U CN2013200315197U CN201320031519U CN203081914U CN 203081914 U CN203081914 U CN 203081914U CN 2013200315197 U CN2013200315197 U CN 2013200315197U CN 201320031519 U CN201320031519 U CN 201320031519U CN 203081914 U CN203081914 U CN 203081914U
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- vortex generator
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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
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
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Abstract
The utility model relates to a dielectric barrier discharge plasma vortex generator. The vortex generator is composed of an insulation heat protection cavity body (4). Different electrodes are laid at the top and the bottom of the insulation heat protection cavity body (4) so that an exciter is formed. The electrodes at the bottom of the insulation heat protection cavity body (4) generate upward jet flows. When the jet flows penetrate through a jet flow outlet (1) at the top of the insulation heat protection cavity body (4), the electrodes at the top of the insulation heat protection cavity body (4) achieve secondary acceleration. According to the dielectric barrier discharge plasma vortex generator, flow of a boundary layer of an aircraft can be controlled and meanwhile, external resistance is not generated, performance of the aircraft is not influenced, additional air sources are not needed, and the weight of the aircraft is not increased.
Description
Technical field
The utility model relates to a kind of flow control apparatus, belongs to the fluid control technology field, is applicable to aviation, vessel traffic, metallurgy and chemical field.
Background technique
Vortex generator has been widely used in 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 installed in the little wing of low aspect ratio on the body surface, so it is the same with conventional wing in windstream to produce the wing tip whirlpool, because its aspect ratio is less, the intensity in wing tip whirlpool is stronger relatively, after mix with the low-energy boundary layer air in its downstream is mobile in this high-octane wing tip whirlpool, just give the boundary layer energy transfer, make the boundary layer flow field that is in the adverse pressure gradient obtain to continue to be attached to body surface and unlikely separation behind the additional-energy.
At present, Chang Yong vortex generator is divided into passive-type and active.Most widely used in the passive-type is the vortex generator of solid type, this type of vortex generator is installed in special position can well delay boundary layer down at particular case separation, play the effect of lift-rising drag reduction, the passive type vortex generator can increase extra form drag under the situation of flow separation 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 driftage 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 control flow separation.
Compare the eddy current jet pipe with the solid vortex generator and have the potentiality that realize active Flow Control.Can be along with the variation of flowing state is in time adjusted, it is a kind of control strategy very flexibly, bring out the intensity in whirlpool by regulating valve control, under suitable flox condition, as long as to close injection pipe when not needing to implement just passable when separating stall control.Adopt the eddy current jet pipe can not resemble and produce drag losses the solid vortex generator.Need provide source of the gas but eddy current is penetrated pipe usually, increase the weight of aircraft or aircraft undoubtedly, reduce the useful load of aircraft.
The model utility content
Technical problem to be solved in the utility model provide a kind of can be when the controlling aircraft boundary layer flows, do not produce extra resistance, do not influence the performance of aircraft, simultaneously do not need extra source of the gas, do not increase the dielectric barrier discharge plasma vortex generator of the weight of aircraft.
The utility model adopts following technological scheme to solve the problems of the technologies described above: the utility model has designed a kind of dielectric barrier discharge plasma vortex generator, described vortex generator is made of a heat insulation cavity 4 of insulation, the bottom center position of the heat insulation cavity 4 of described insulation has a circular open, the top center position has a jet exit 1, the top upper surface of the heat insulation cavity 4 of described insulation is equipped with two strip coated electrodes 2 and two strip bare electrodes 3, described strip coated electrode is the both sides that the center is set in parallel in jet exit with jet exit 1, described two strip bare electrodes 3 are the both sides that the center is symmetricly set on jet exit 1 respectively with jet exit 1, and these two strip bare electrodes 3 are positioned at the outside of two strip coated electrodes 2; The bottom opening position of the heat insulation cavity 4 of described insulation is provided with discoid coated electrode 6, and described discoid coated electrode 6 closely engages with bottom opening, the upper base surface of the heat insulation cavity 4 of described insulation is provided with circular bare electrode 5, and the described circular bare electrode 5 and discoid coated electrode 6 centers of circle overlap.
The utility model has also designed a kind of dielectric barrier discharge plasma vortex generator, described vortex generator is made of a heat insulation cavity 4 of insulation, the bottom center position of the heat insulation cavity 4 of described insulation has a circular open, the top center position has a jet exit 1, the bottom opening position of the heat insulation cavity 4 of described insulation is provided with discoid coated electrode 6, and described discoid coated electrode 6 closely engages with bottom opening, the upper base surface of the heat insulation cavity 4 of described insulation is provided with the first circular bare electrode, the described first circular bare electrode and discoid coated electrode 6 centers of circle overlap, the top upper surface of the heat insulation cavity of described insulation is equipped with the second circular bare electrode, the center of circle of the described second circular bare electrode overlaps with jet exit 1, the inboard of the described second circular bare electrode is equipped with circular coated electrode 7, the described second circular bare electrode and circular coated electrode 7 centers of circle overlap, and the internal diameter of the second circular bare electrode is greater than the external diameter of circular coated electrode 7.
The utility model compared with prior art has following advantage:
1. the utility model adopts the plasma generation more high efficiency jet of three-dimensional plasma-vortex generator than two dimension, thereby the control effect of stream field is also stronger;
2. the utility model can not produce extra resistance in the controlling aircraft boundary layer, does not influence the performance of aircraft yet, nor needs extra source of the gas, does not increase the weight of aircraft;
3. the utility model using plasma vortex generator can be in place, the suitable time, realizes the ACTIVE CONTROL to boundary layer.
Description of drawings
Fig. 1 is the designed dielectric barrier discharge plasma vortex generator performance parameter of the utility model;
Fig. 2 a is the top plan of H type end face O type bottom surface dielectric barrier discharge vortex generator;
Fig. 2 b is the side view of H type end face O type bottom surface dielectric barrier discharge vortex generator;
Fig. 2 c is the bottom worm's eye view of H type end face O type bottom surface dielectric barrier discharge vortex generator;
Fig. 3 a is the top plan of O type end face O type bottom surface dielectric barrier discharge vortex generator;
Fig. 3 b is the side view of O type end face O type bottom surface dielectric barrier discharge vortex generator;
Fig. 3 c is the bottom worm's eye view of O type end face O type bottom surface dielectric barrier discharge vortex generator.
1-jet exit, 2-strip coated electrode, 3-strip bare electrode, the 4-heat insulation cavity that insulate, the circular bare electrode of 5-, the discoid coated electrode of 6-, the circular coated electrode of 7-.
Embodiment
The utility model is described in further detail below in conjunction with accompanying drawing:
As shown in Figure 2, the utility model adopts following technological scheme to solve the problems of the technologies described above: the utility model has designed a kind of dielectric barrier discharge plasma vortex generator, described vortex generator is made of a heat insulation cavity 4 of insulation, the bottom center position of the heat insulation cavity 4 of described insulation has a circular open, the top center position has a jet exit 1, the top upper surface of the heat insulation cavity 4 of described insulation is equipped with two strip coated electrodes 2 and two strip bare electrodes 3, described strip coated electrode is the both sides that the center is set in parallel in jet exit with jet exit 1, described two strip bare electrodes 3 are the both sides that the center is symmetricly set on jet exit 1 respectively with jet exit 1, and these two strip bare electrodes 3 are positioned at the outside of two strip coated electrodes 2; The bottom opening position of the heat insulation cavity 4 of described insulation is provided with discoid coated electrode 6, and described discoid coated electrode 6 closely engages with bottom opening, the upper base surface of the heat insulation cavity 4 of described insulation is provided with circular bare electrode 5, and the described circular bare electrode 5 and discoid coated electrode 6 centers of circle overlap.
As shown in Figure 3, the utility model has also designed a kind of dielectric barrier discharge plasma vortex generator, described vortex generator is made of a heat insulation cavity 4 of insulation, the bottom center position of the heat insulation cavity 4 of described insulation has a circular open, the top center position has a jet exit 1, the bottom opening position of the heat insulation cavity 4 of described insulation is provided with discoid coated electrode 6, and described discoid coated electrode 6 closely engages with bottom opening, the upper base surface of the heat insulation cavity 4 of described insulation is provided with the first circular bare electrode 5, the described first circular bare electrode 5 and discoid coated electrode 6 centers of circle overlap, the top upper surface of the heat insulation cavity of described insulation is equipped with the second circular bare electrode 5, the center of circle of the described second circular bare electrode 5 overlaps with jet exit 1, the inboard of the described second circular bare electrode 5 is equipped with circular coated electrode 7, the described second circular bare electrode 5 and circular coated electrode 7 centers of circle overlap, and the internal diameter of the second circular bare electrode 5 is greater than the external diameter of circular coated electrode 7.
Working principle of the present utility model is: the electrode of heat insulation cavity 4 bottoms of insulating produces jet upwards, and jet is during through the jet exit 1 at the heat insulation cavity of insulation 4 tops, and the electrode secondary that is positioned at the heat insulation cavity of insulation 4 tops quickens.
In specific embodiment, between nose-circle ring-type bare electrode 2 and bottom needlepoint shape electrode 4, apply high-tension electricities such as high frequency direct current, interchange, pulse, if energizing voltage is to exchange or pulsed voltage, then the energizing voltage phase place is
U is the energizing voltage amplitude in the formula, and κ is a correction factor, and ρ, ε are constant, and L is the height of cavity.The cycle of pulse discharge can be from psec (pm) to millisecond (ms), and voltage magnitude is greater than 2000 volts;
Jet exit (1) is set according to actual conditions with the angle [alpha] of substantially horizontal, generally between 30 °～90 °; The β angle also can be adjustable as required, and scope is between 0 °～90 °.
Claims (2)
1. dielectric barrier discharge plasma vortex generator, it is characterized in that, described vortex generator is made of a heat insulation cavity of insulation (4), the bottom center position of the heat insulation cavity of described insulation (4) has a circular open, the top center position has a jet exit (1), the top upper surface of the heat insulation cavity of described insulation (4) is equipped with two strip coated electrodes (2) and two strip bare electrodes (3), described strip coated electrode is the both sides that the center is set in parallel in jet exit with jet exit (1), described two strip bare electrodes (3) are the both sides that the center is symmetricly set on jet exit (1) respectively with jet exit (1), and these two strip bare electrodes (3) are positioned at the outside of two strip coated electrodes (2); The bottom opening position of the heat insulation cavity of described insulation (4) is provided with discoid coated electrode (6), and described discoid coated electrode (6) closely engages with bottom opening, the upper base surface of the heat insulation cavity of described insulation (4) is provided with circular bare electrode (5), and the described circular bare electrode (5) and discoid coated electrode (6) center of circle overlap.
2. dielectric barrier discharge plasma vortex generator, it is characterized in that, described vortex generator is made of a heat insulation cavity of insulation (4), the bottom center position of the heat insulation cavity of described insulation (4) has a circular open, the top center position has a jet exit (1), the bottom opening position of the heat insulation cavity of described insulation (4) is provided with discoid coated electrode (6), and described discoid coated electrode (6) closely engages with bottom opening, the upper base surface of the heat insulation cavity of described insulation (4) is provided with the first circular bare electrode, the described first circular bare electrode and discoid coated electrode (6) center of circle overlap, the top upper surface of the heat insulation cavity of described insulation is equipped with the second circular bare electrode, the center of circle of the described second circular bare electrode overlaps with jet exit (1), the inboard of the described second circular bare electrode is equipped with circular coated electrode (7), the described second circular bare electrode and circular coated electrode (7) center of circle overlap, and the internal diameter of the second circular bare electrode is greater than the external diameter of circular coated electrode (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013200315197U CN203081914U (en) | 2013-01-21 | 2013-01-21 | Dielectric battier discharge plasma vortex generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013200315197U CN203081914U (en) | 2013-01-21 | 2013-01-21 | Dielectric battier discharge plasma vortex generator |
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| Publication Number | Publication Date |
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| CN203081914U true CN203081914U (en) | 2013-07-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2013200315197U Expired - Fee Related CN203081914U (en) | 2013-01-21 | 2013-01-21 | Dielectric battier discharge plasma vortex generator |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089760A (en) * | 2013-01-21 | 2013-05-08 | 南京航空航天大学 | Dielectric barrier discharge plasma body vortex generator |
| CN106553754A (en) * | 2015-09-24 | 2017-04-05 | 波音公司 | For the embedded-type electric dielectric structure of active flow control plasma source |
| CN111577561A (en) * | 2020-04-24 | 2020-08-25 | 南京理工大学 | Device for improving jet intensity of annular electrode exciter and working method thereof |
-
2013
- 2013-01-21 CN CN2013200315197U patent/CN203081914U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089760A (en) * | 2013-01-21 | 2013-05-08 | 南京航空航天大学 | Dielectric barrier discharge plasma body vortex generator |
| CN106553754A (en) * | 2015-09-24 | 2017-04-05 | 波音公司 | For the embedded-type electric dielectric structure of active flow control plasma source |
| CN111577561A (en) * | 2020-04-24 | 2020-08-25 | 南京理工大学 | Device for improving jet intensity of annular electrode exciter and working method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130724 Termination date: 20150121 |
|
| EXPY | Termination of patent right or utility model |