CN104612879B - High-back-pressure plasma igniter - Google Patents
High-back-pressure plasma igniter Download PDFInfo
- Publication number
- CN104612879B CN104612879B CN201510025617.3A CN201510025617A CN104612879B CN 104612879 B CN104612879 B CN 104612879B CN 201510025617 A CN201510025617 A CN 201510025617A CN 104612879 B CN104612879 B CN 104612879B
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- China
- Prior art keywords
- negative electrode
- anode
- adjusting nut
- insulating sleeve
- pressure plasma
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- 239000003638 chemical reducing agent Substances 0.000 claims description 16
- 229910010293 ceramic material Inorganic materials 0.000 claims description 8
- 238000007599 discharging Methods 0.000 claims description 4
- 239000011148 porous material Substances 0.000 claims description 3
- 238000010030 laminating Methods 0.000 claims description 2
- 239000000919 ceramic Substances 0.000 claims 2
- 238000007789 sealing Methods 0.000 abstract description 5
- 238000009413 insulation Methods 0.000 abstract 3
- 238000002485 combustion reaction Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 description 3
- 239000003795 chemical substances by application Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02P—IGNITION, OTHER THAN COMPRESSION IGNITION, FOR INTERNAL-COMBUSTION ENGINES; TESTING OF IGNITION TIMING IN COMPRESSION-IGNITION ENGINES
- F02P23/00—Other ignition
- F02P23/04—Other physical ignition means, e.g. using laser rays
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
- Cyclones (AREA)
Abstract
The invention relates to a high-back-pressure plasma igniter. The problem that an existing igniter cannot work under the environment of high back pressure and variable back pressure is solved. According to the technical scheme, the high-back-pressure plasma igniter comprises a shell, a cathode, an anode, an air inlet, a binding post, a swirler, a sealing ring structure, an insulation sleeve structure, an adjusting nut, a spring, a restrictor and an inner nut. An air connecting hole in the restrictor is communicated with a through hole in the shell and the air inlet. External threads of the adjusting nut are meshed with internal threads on the shell. A boss arranged on the cathode is attached to a step structure of a second insulation sleeve, and the spring is compressed between the boss and a first insulation sleeve. The high-back-pressure plasma igniter has the advantages of being small in size, light, convenient to use, high in ignition capacity and capable of being started many times and running under high back pressure, and can be used as an ignition device of various heaters, combustion chambers, aero-engines and rocket engines.
Description
Technical field
The present invention relates to a kind of lighter, particularly to a kind of can be used as the high back pressure plasma of various high chamber pressure burners
Body lighter.
Background technology
At present, all kinds of heaters of rocket engine and Aero-engine testing platform, combustor, the igniter of thrust chamber
It mostly is electric detonator, igniting agent, spark plug.Electric detonator and igniting agent igniting have the shortcomings that poor stability, difficult realization repeatedly start,
Commonly electricity fire plug spark ignition have the shortcomings that ignition energy low, igniting reliability general.For realizing rocket engine, aeroplane engine
The multiple igniting of machine and reuse, plasma-ignition technique is a kind of effective approach.But usual plasma is lighted a fire
Device is in the case that high back pressure and back pressure steeply rise it is easy to power-off is stopped working.
Content of the invention
Present invention solves the technical problem that being: design a kind of high back pressure plasma igniter, overcome existing plasma
Firing technique in high back pressure and can not become the shortcoming and defect working in back pressure environment, provides one kind to can be used under high back pressure environment
The plasma igniter starting and running.
The technical scheme is that a kind of high back pressure plasma igniter of design, including housing 3, negative electrode 20, anode
1st, air inlet 7, binding post 13, cyclone 2, ring structure and tube form it is characterised in that: also include adjusting nut
12nd, spring 5, reducer 4 and interior nut 15；The inner chamber of described housing 3 is concave structure, and reducer 4 passes through support 17 and interior spiral shell
Cap 15 is fixed on bottom so that the pore that connects on reducer 4 is connected with the through hole on housing 3 and air inlet 7；The opening of housing 3
Mouth end is provided with has externally threaded adjusting nut 12, and the external screw thread of adjusting nut 12 is engaged with the female thread on housing 3；Adjust
The endoporus of section nut 12 is ledge structure, and the second insulating sleeve 11 being located between adjusting nut 12 and negative electrode 20 is provided with and adjusts
The ledge structure that the endoporus ledge structure of nut 12 matches, described negative electrode 20 is provided with boss, and boss place direction and the moon
The axis place direction of pole 20 is mutually perpendicular to, and boss is fitted with the ledge structure of the second insulating sleeve 11, and boss and first insulate
It is compressed with spring 5, the internal diameter of spring 5 is more than the external diameter of negative electrode 20, the external diameter of spring 5 is less than the first insulating sleeve between sleeve 18
18 external diameter；Described negative electrode 20 is to be provided with discharging gap between arc-shaped, and anode 1 with one end of anode 1；Described anode 1
Throat be coaxial through-hole, cyclone 2 be located between anode 1 and the first insulating sleeve 18, and the first insulating sleeve 18 not with housing 3
Contact.
The further technical scheme of the present invention is: described first insulating sleeve 18 adopts ceramic material.
The further technical scheme of the present invention is: described second insulating sleeve 11 adopts ceramic material.
The further technical scheme of the present invention is: described support 17 adopts ceramic material.
The operation principle of the present invention is: the binding post of negative electrode accesses the negative electrode of external power source, one end of the binding post of anode
Access the anode of external power source, external power source realizes power supply for lighter.Working medium gas from air inlet entrance after, through in housing
Through hole enters reducer；Through after the Working medium gas that reducer obtains constant flow rate, through the hole on support, enter the first insulating sleeve
Gap location and housing between；Formed through cyclone after swirling eddy, enter the gap location between anode and negative electrode；In rotary pneumatic
While stream is through anode hole, anode is discharged with the head of negative electrode, forms plasma jet, that is, realize igniting, finally through anode
Spout sprays.
Invention effect
The method have technical effect that: the present invention have small volume, lightweight, easy to use, ignition ability strong, can be many
Secondary startup, the advantage that can run under high back pressure, can be used as various heaters, combustor and aero-engine, rocket motor
The igniter of machine.
Brief description
Fig. 1 is present configuration schematic diagram
Fig. 2 is anode construction schematic diagram of the present invention
Fig. 3 is negative electrode in the present embodiment and one end structural representation at anode cooperation
Fig. 4 is that in the present embodiment, the negative electrode other end carries adjusting nut structural representation
Fig. 5 is the structural representation of reducer in the present embodiment
Description of reference numerals: 1- anode；2- cyclone；3- housing；4- reducer；5- spring；6- first sealing ring；7- enters
QI KOU；8- second sealing ring；9- the 3rd sealing ring；10- nut；11- second insulating sleeve；12- adjusting nut；13- binding post；
14- first pad；Nut in 15-；16- the 4th sealing ring；17- support；18- first insulating sleeve；19- second pad；20- is cloudy
Pole.
Specific embodiment
With reference to being embodied as example, technical solution of the present invention is further illustrated.
1., referring to Fig. 1 and Fig. 4, design a kind of high back pressure plasma igniter, including housing 3, negative electrode 20, anode 1, enter
QI KOU 7, binding post 13, cyclone 2, ring structure and tube form, adjusting nut 12, spring 5, support 17, throttling
Device 4 and interior nut 15, wherein insulating sleeve adopt ceramic material, and support is also adopted by ceramic material.
The inner chamber of described housing 3 is concave structure, and reducer 4 passes through support 17 and interior nut 15 is fixed on bottom, interior spiral shell
The female thread of the external screw thread of cap and housing 3 engages each other so that reducer 4 and support 17 is stuck is fixed in housing.Reducer 4
On the hole diameter that connects be 0.5mm, make air-flow flow rate stable using orifice restriction, it is steady that stable air-flow is beneficial to arc discharge
Fixed.
The pore that connects of reducer 4 is connected with the through hole on housing 3 and air inlet 7, and support 17 is provided with hole；Housing 3
Opening is provided with has externally threaded adjusting nut 12, and the external screw thread of adjusting nut 12 is engaged with the female thread on housing 3；
The endoporus of adjusting nut 12 is ledge structure, and the second insulating sleeve 11 being located between adjusting nut 12 and negative electrode 20 is provided with and adjusts
Ledge structure, the boss that described negative electrode 20 is provided with and the second insulating sleeve 11 that the endoporus ledge structure of section nut 12 matches
Ledge structure laminating, and between the second insulating sleeve 11 and boss, be provided with the first pad 14.
It is compressed with spring 5, the internal diameter of spring 5 is more than the external diameter of negative electrode 20, spring 5 between boss and the first insulating sleeve 18
External diameter be less than the first insulating sleeve 18 external diameter.By rotating adjusting nut 12, under spring 5 drives, negative electrode 20 carries out axial direction
Motion, thus adjust the discharging gap being formed between negative electrode 20 and anode 1, when Spark gap adjustment is to 0.2mm, using 30kv's
High-voltage pulse, realizes reliable under 5mpa environment startup.I.e. the discharging gap between adjustment the two poles of the earth is it is achieved that under high back pressure environment
Startup and operation.Cyclone 2 is located between anode 1 and the first insulating sleeve 18, between cyclone 2 and the first insulating sleeve 18
It is provided with the second pad, and the first insulating sleeve 18 is not contacted with housing 3, form gap between the two.
2., referring to Fig. 2, the throat of anode 1 is coaxial through-hole, and the size of coaxial through-hole is respectively φ 1 and φ 6, both
Intersection, air-flow forms backflow, and speed is low, the electric-force gradient intersection in aperture and macropore so that anode arc speckle falls greatly.
3., referring to Fig. 3, described negative electrode 20 is arc-shaped with one end of anode 1, and the radius of arc end is 5mm so that putting
Electric area is big, and radiating rate is fast, effectively reduces negative electrode head temperature, slows down Recession rate, improve negative electrode service life.
4th, referring to Fig. 5, the hole diameter that connects of described reducer 4 is 0.5mm, is provided with throttle orifice inside reducer 4, its outlet
When being less than critical pressure ratio with entrance pressure ratio, that is,Flow rate is definite value.I.e. outlet pressure pout＜ βγpinIn the case of, work
The flow rate of matter gas keeps stable.It should be noted that the critical pressure ratio of gas is 0.53.
Claims (4)
1. a kind of high back pressure plasma igniter, including housing (3), negative electrode (20), anode (1), air inlet (7), binding post
(13), cyclone (2), ring structure and tube form it is characterised in that: also include adjusting nut (12), spring
(5), reducer (4) and interior nut (15)；The inner chamber of described housing (3) be concave structure, reducer (4) pass through support (17) and
Interior nut (15) is fixed on bottom so that the through hole connecing on pore and housing (3) on reducer (4) and air inlet (7) connect
Logical；The opening of housing (3) is provided with has externally threaded adjusting nut (12), the external screw thread of adjusting nut (12) and housing (3)
On female thread be engaged；The endoporus of adjusting nut (12) is ledge structure, be located at adjusting nut (12) and negative electrode (20) it
Between the second insulating sleeve (11) be provided with the ledge structure matching with the endoporus ledge structure of adjusting nut (12), described negative electrode
(20) it is provided with boss, and the axis place direction of boss place direction and negative electrode (20) is mutually perpendicular to, boss and second insulate
The ledge structure laminating of sleeve (11), is compressed with spring (5), the internal diameter of spring (5) between boss and the first insulating sleeve (18)
More than the external diameter of negative electrode (20), the external diameter of spring (5) is less than the external diameter of the first insulating sleeve (18)；Described negative electrode (20) and anode
(1) relative one end is to be provided with discharging gap between arc-shaped, and anode (1)；The throat of described anode (1) is coaxial through-hole,
Cyclone (2) is located between anode (1) and the first insulating sleeve (18).
2. as claimed in claim 1 a kind of high back pressure plasma igniter it is characterised in that described first insulating sleeve
(18) it is the ceramic sleeve made using ceramic material.
3. as claimed in claim 1 a kind of high back pressure plasma igniter it is characterised in that described second insulating sleeve
(11) it is the ceramic sleeve made using ceramic material.
4. as claimed in claim 1 a kind of high back pressure plasma igniter it is characterised in that described support (17) is employing
The support that ceramic material is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510025617.3A CN104612879B (en) | 2015-01-19 | 2015-01-19 | High-back-pressure plasma igniter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510025617.3A CN104612879B (en) | 2015-01-19 | 2015-01-19 | High-back-pressure plasma igniter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104612879A CN104612879A (en) | 2015-05-13 |
| CN104612879B true CN104612879B (en) | 2017-02-01 |
Family
ID=53147486
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510025617.3A Expired - Fee Related CN104612879B (en) | 2015-01-19 | 2015-01-19 | High-back-pressure plasma igniter |
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| Country | Link |
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| CN (1) | CN104612879B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109268191A (en) * | 2018-10-26 | 2019-01-25 | 大连民族大学 | A kind of double discharge plasma igniters with double air inlet bias anode constructions |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105449526B (en) * | 2015-12-20 | 2017-07-07 | 西安航天动力研究所 | Small-sized non-cooled plasma jet igniter |
| CN106304593B (en) * | 2016-09-29 | 2019-12-13 | 四川金虹等离子技术有限公司 | non-impact self-adaptive trigger ignition device utilizing laminar plasma system |
| CN107061100B (en) * | 2017-05-27 | 2018-10-12 | 蚌埠泰欣电子科技有限公司 | A kind of igniter for automobile for the wiring mechanism that stretches with internal thread |
| CN108194943B (en) * | 2017-12-29 | 2020-03-03 | 西安航天动力研究所 | Plasma ignition device of high-pressure high-flow liquid oxygen kerosene engine |
| CN109268190A (en) * | 2018-10-26 | 2019-01-25 | 大连民族大学 | A kind of plasma igniter with the double discharge modes of double air inlets |
| CN109185005A (en) * | 2018-10-26 | 2019-01-11 | 大连民族大学 | A kind of plasma igniter application method with fuel channel |
| CN109209726A (en) * | 2018-10-26 | 2019-01-15 | 大连民族大学 | The ignition method of double discharge mode plasma igniters with eccentric Double-positive-pole structure |
| CN112179664B (en) * | 2020-08-29 | 2021-07-23 | 西北工业大学 | Adjustable low-pressure ignition experimental system for researching sub-super mixed flow |
| CN113357114B (en) * | 2021-07-19 | 2022-05-06 | 哈尔滨工业大学 | Main cathode assembly structure applied to thruster and assembly method thereof |
| CN116717398A (en) * | 2023-05-11 | 2023-09-08 | 遨天科技(北京)有限公司 | Rocket engine plasma igniter |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4264844A (en) * | 1978-09-29 | 1981-04-28 | Axe Gavin C H | Electrical igniters |
| US6918366B2 (en) * | 2002-08-28 | 2005-07-19 | Robert Bosch Gmbh | Device for igniting an air-fuel mixture in an internal combustion engine |
| DE102004018201A1 (en) * | 2004-04-15 | 2005-11-10 | Robert Bosch Gmbh | Device for igniting air-fuel mixture in internal combustion engine has end of coaxial waveguide structure forming ignition pin so free-standing plasma can be produced in air-fuel mixture by field structure protruding into combustion chamber |
| CN202718760U (en) * | 2012-05-29 | 2013-02-06 | 哈尔滨工程大学 | Plasma ignitor with reusable cathode |
| CN103277231A (en) * | 2013-03-18 | 2013-09-04 | 中国人民解放军空军工程大学 | Aero-engine air rotational flow plasma igniter |
| CN103925116A (en) * | 2014-04-28 | 2014-07-16 | 中国航天空气动力技术研究院 | Sliding arc ignition device |
-
2015
- 2015-01-19 CN CN201510025617.3A patent/CN104612879B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4264844A (en) * | 1978-09-29 | 1981-04-28 | Axe Gavin C H | Electrical igniters |
| US6918366B2 (en) * | 2002-08-28 | 2005-07-19 | Robert Bosch Gmbh | Device for igniting an air-fuel mixture in an internal combustion engine |
| DE102004018201A1 (en) * | 2004-04-15 | 2005-11-10 | Robert Bosch Gmbh | Device for igniting air-fuel mixture in internal combustion engine has end of coaxial waveguide structure forming ignition pin so free-standing plasma can be produced in air-fuel mixture by field structure protruding into combustion chamber |
| CN202718760U (en) * | 2012-05-29 | 2013-02-06 | 哈尔滨工程大学 | Plasma ignitor with reusable cathode |
| CN103277231A (en) * | 2013-03-18 | 2013-09-04 | 中国人民解放军空军工程大学 | Aero-engine air rotational flow plasma igniter |
| CN103925116A (en) * | 2014-04-28 | 2014-07-16 | 中国航天空气动力技术研究院 | Sliding arc ignition device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109268191A (en) * | 2018-10-26 | 2019-01-25 | 大连民族大学 | A kind of double discharge plasma igniters with double air inlet bias anode constructions |
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| Publication number | Publication date |
|---|---|
| CN104612879A (en) | 2015-05-13 |
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Granted publication date: 20170201 |