CN101463764A - High-energy plasma igniter of gas turbine - Google Patents
High-energy plasma igniter of gas turbine Download PDFInfo
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- CN101463764A CN101463764A CNA2009100712397A CN200910071239A CN101463764A CN 101463764 A CN101463764 A CN 101463764A CN A2009100712397 A CNA2009100712397 A CN A2009100712397A CN 200910071239 A CN200910071239 A CN 200910071239A CN 101463764 A CN101463764 A CN 101463764A
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Abstract
The invention provides a gas turbine high-energy plasma igniter. The plasma igniter comprises an ignition exciter unit and a matched plasma generator, wherein, the ignition exciter unit comprises a control relay, a transformation isolating circuit, an oscillating impulse circuit, an arc maintenance follow current module and a high voltage transformer; the plasma generator comprises a fitting seat, a centre shaft, an insulator, a cathode and an anode; in the invention, ignition efficiency is improved given the set plasma ignition energy and the electrode is fully cooled, thus prolonging the service life thereof. On the contrary, as the cooling effect is improved, plasma ignition energy can be increased, so that low grade fuel such as heavy oil and the like can be ignited under even worse conditions. Meanwhile, the position of a screw hole can be just adjusted to replace the previous igniter, and judging from the situation, the plasma igniter of the invention has numerous advantages and is more functional.
Description
(1) technical field
The present invention relates to the high-energy ignition equipment in a kind of heat energy and power field, particularly relate to a kind of high-energy plasma igniter that is applicable to gas turbine.
(2) background technique
Nowadays gas turbine is used widely and is developed at numerous areas such as aviation, boats and ships, generatings because its power is big, weight and size is little, the efficient advantages of higher.In the start-up course of gas turbine, igniting is crucial.The success rate of igniting will be directly connected to the safe and reliable operation of whole device.
At present, the method for igniting commonly used has spark ignition and semiconductor surface discharge igniting, and sparkover or Arc Discharge that the spark ignition utilization is opened between two electrodes in firing chamber come ignition mixture.The general ignition energy of the method is lower, and spark delay is long.The semiconductor surface discharge igniting is to clamp a semi-conducting material between centre electrode and lateral electrode, utilizes the ignition installation of the semi-conductive thermal effect discharge starting the arc.The semiconductor discharge has essential distinction with the Arc Discharge of gas.Can obtain bigger igniting power although it is so, but, directly influence the performance and the life-span of whole ignition mechanism owing to semi-conductive life problems.
Plasma ignition is a kind of New Type of Ignition System in recent years, utilizes arc excitation high-temperature plasma pilot fuel.Its advantage is to improve the success rate of igniting and the stability of burning, and its igniting power is big, the reliability height.But exist the problem of a contradiction: if require ignition energy big, then increase energy of plasma, electrode erosion aggravation then, the life-span reduces; And if will guarantee electrode life, ignition energy then is restricted.
More existing open reports about plasma ignition, for example number of patent application is 200620020007.0, name is called in the utility model patent file of " Pulse Plasma Igniter " disclosed technological scheme etc.Facts have proved that also there are many improvements that need in this technological scheme.
(3) summary of the invention
The object of the present invention is to provide a kind of igniting usefulness height, the high-energy plasma igniter of gas turbine of long service life.
The object of the present invention is achieved like this:
Comprise ignition exciter unit 1 and supporting plasma generator 2; The formation of ignition exciter unit 1 comprises control relay, transformation buffer circuit, oscillating impulse circuit, arc maintenance afterflow module and high-tension transformer; Control relay links to each other by Aviation Connector with control direct current supply with outside 220V Alternating Current Power Supply; The control relay output terminal is connected with transformation buffer circuit input end; Transformation buffer circuit output terminal connects oscillating impulse circuit and arc maintenance afterflow module; The oscillating impulse circuit output end connects high-tension transformer; The inner core output of one termination high-voltage ignition cable of high-tension transformer output terminal, the other end connects the negative pole of arc maintenance afterflow module output terminal; The positive contact fire actuator casing of arc maintenance afterflow module output terminal.The formation of plasma generator 2 comprises fitting seat 8, axis (3), insulator 4, negative electrode 5, anode 7; Fitting seat 8 is and anode 7 fastening installations, and the two becomes coaxial ring structure, and there is cylindrical cavity the centre; Offer the oil circuit interface in the fitting seat side, asphalt channel communicates with oilhole on the negative electrode 5; The head of negative electrode 5 becomes sharp cone distal, and the tip offers nozzle opening, is inlaid with the zirconium metallic material at pointed cone; Ceramics insulator 4 is housed between fitting seat 8 and negative electrode, and axis 3 is connected together with negative electrode 5, reinstalls in the ceramics insulator 4, and it is concentric that the three keeps.Ignition exciter unit 1 is connected with plasma generator 2 by high-voltage ignition cable, and the external metallization screen layer of high-voltage ignition cable connects the positive pole and plasma generator 2 fitting seats of ignition exciter unit 1; The inner core of high-voltage ignition cable connects the negative pole of ignition exciter unit 1 and the interior utmost point of plasma generator 2.The teflon insulation layer is arranged between the screen layer of high-voltage ignition cable and inner core, and the isolation layer average thickness is greater than 2mm.
The present invention can also comprise:
The cooling of plasma generator 2 electrodes comprises fuel cools and air cooling, and air is entered by the cavity between fitting seat 8 and the anode 5, and antianode 5 cooling backs are by the ejection of the gap between anode 5 and the negative electrode 7, and anticathode 7 outer surfaces also produce cooling action simultaneously; Fuel oil produces cooling action by the inside of negative electrode 7 inner ejection anticathodes 7.
The present invention is according to the problem that exists in the prior art, and the mode that adopts plasma ignition and little oily small oil gun to organically combine has designed this plasma ignition device.Design and improvement repeatedly passed through in this invention, and through test of many times, proves that it is practical and have use value.
The present invention can be implemented under the given plasma ignition energy, has improved igniting usefulness, and electrode has obtained sufficient cooling simultaneously, has prolonged the working life of electrode.Otherwise,, make and can under worse condition, light as low grade fuels such as heavy oil because the raising of cooling effect can strengthen the plasma ignition energy.Simultaneously, 8 of fitting seats need to adjust the screw hole position just can directly substitute original igniter, this shows that the present invention has plurality of advantages, and is suitable for practicality more.
Be 200620020007.0 with number of patent application, name is called in the utility model patent file of " Pulse Plasma Igniter " disclosed technological scheme and compares, the difference of the two is mainly reflected in: the plasma generator of at first former technological scheme itself is not to be with the oil nozzle structure, and the present invention organically combines plasma generator 2 and little oily small oil gun, with the oil nozzle 6 of small oil gun anode 5 as plasma generator 2, after ignition exciter unit 1 quits work, this generator still can be stablized the little torch of generation, and is combustion-supporting to the firing chamber.Secondly, type of cooling difference is owing to added little oil return line, the present invention is fuel oil and air dual-cooled mode for the electrode employing, when having prolonged electrode life, also there is pre-heat effect in fuel oil, supplying with under the lower situation of oil temperature, flameholding had very big effect.Therefore, the two is all completely different on working principle and the enforcement structure in design concept.
(4) description of drawings
Fig. 1 is the connection diagram of high-energy plasma igniter of gas turbine of the present invention.
Fig. 2 is the ignition exciter unit internal structure module diagram of high-energy plasma igniter of gas turbine of the present invention.
Fig. 3 is the plasma generator structural representation of high-energy plasma igniter of gas turbine of the present invention.
Fig. 4 is the ignition exciter unit circuit theory diagrams of high-energy plasma igniter of gas turbine of the present invention.
(5) embodiment
For example the present invention is done description in more detail below in conjunction with accompanying drawing:
Fig. 1 is the connection diagram of high-energy plasma igniter of gas turbine of the present invention.High-energy plasma igniter of gas turbine of the present invention, it mainly comprises: an ignition exciter unit 1, and supporting plasma generator 2 and high-voltage ignition cable.Can determine the incendiary source number according to factors such as combustion turbine power, fuel.The incendiary source number both had been the number of plasma generator 2.According to plasma generator 2 numbers, can expand ignition exciter unit 1 module, be 2 tunnel outputs such as ignition exciter unit 1 of design, if need 4 incendiary sources, then be equipped with two ignition exciter units 1 and 4 cover plasma generator 2 and high-voltage ignition cables.
Fig. 2 is the ignition exciter unit 1 internal structure module diagram of high-energy plasma igniter of gas turbine of the present invention.Ignition exciter unit 1 adopts modularization to form, and can freely select single channel output and two-way output, and what adopt in the present embodiment is two-way output.Control relay can select suitable control relay to control the break-make that 220V exchanges input according to the control signal size.
The major function of transformation buffer circuit is that working circuit and 220V electrical network are kept apart, and has both avoided the interference of electrical network clutter to working circuit, and also avoiding working circuit chance failure in a single day to occur influences electrical network.Simultaneously, isolating transformer also improves the 220V alternating voltage, increases igniter output energy.The transformer output voltage of Cai Yonging is that 400V/50Hz exchanges in the present embodiment.
The oscillating impulse circuit comprises oscillation module and high pressure resonance modules.Oscillation module can adopt controllable silicon or MOSFET pipe as switching tube, can adopt triode to produce oscillating impulse, also can adopt special-purpose pulsing chip.High pressure resonance modules and oscillation module parallel operation insert the high pressure resonance modules with the two ends of switching tube, and when the switching tube conducting, high pressure resonance modules resonance produces high pressure output.
Seeing also shown in Figure 3ly, is plasma generator 2 structural representations of high-energy plasma igniter of gas turbine of the present invention.Axis 3 connects the utmost point and negative electrode 5 in the high-voltage ignition cable.Offer oil supply gallery at fitting seat 8 middle parts, outside pipeline road links to each other micro-fuel oil on negative electrode 5 through this passage with oil nozzle 6 perforate flows to oil nozzle 6 atomizing ejections.Negative electrode 5 is made up of oil nozzle 6 and the protective material that is embedded in its cross cut end (of a beam), and this protective material can adopt the high temperature resistant alloy materials of anti-ablation the such as zirconium, hafnium, with 5 working lifes of prolongation negative electrode.Between axis 3, negative electrode 5 and fitting seat 8, be filled with high-temperature insulation body 4 to guarantee insulation effect, can select stupalith for use.Between fitting seat 8 and anode 7, take two-tube nested mode, pressurized air is fed by the annular pass between the two, from ejection between anode 7 and the negative electrode 5, play the effect of cooling electrode again.The working method of this plasma generator 2 is to produce high energy electric arc by ignition exciter unit 1 between anode 7 and negative electrode 5, pressurized air is ionized when being sprayed by the two and excites high-temperature plasma, this plasma is because air push arrives oil nozzle 6 the place aheads, thereby the vaporific fuel oil of oil nozzle 6 ejections and air mixture are lighted the formation small oil gun by this high-temperature plasma.After heat power equipment was started smoothly, ignition exciter unit quit work, and that this plasma generator can continue to supply with little oil is combustion-supporting to main combustion chamber with the burning of keeping small oil gun.
Claims (5)
1, a kind of high-energy plasma igniter of gas turbine comprises ignition exciter unit (1) and supporting plasma generator (2); It is characterized in that: the formation of ignition exciter unit (1) comprises control relay, transformation buffer circuit, oscillating impulse circuit, arc maintenance afterflow module and high-tension transformer; Control relay links to each other by Aviation Connector with control direct current supply with outside 220V Alternating Current Power Supply; The control relay output terminal is connected with transformation buffer circuit input end; Transformation buffer circuit output terminal connects oscillating impulse circuit and arc maintenance afterflow module; The oscillating impulse circuit output end connects high-tension transformer; The inner core output of one termination high-voltage ignition cable of high-tension transformer output terminal, the other end connects the negative pole of arc maintenance afterflow module output terminal; The positive contact fire actuator casing of arc maintenance afterflow module output terminal; The formation of plasma generator (2) comprises fitting seat (8), axis (3), insulator (4), negative electrode (5), anode (7); Fitting seat (8) is and the fastening installation of anode (7), and the two becomes coaxial ring structure, and there is cylindrical cavity the centre; Offer the oil circuit interface in the fitting seat side, asphalt channel communicates with oilhole on the negative electrode (5); The head of negative electrode (5) becomes sharp cone distal, and the tip offers nozzle opening; Ceramics insulator (4) is housed between fitting seat (8) and negative electrode, and axis (3) is connected together with negative electrode (5), reinstalls in the ceramics insulator (4); Ignition exciter unit (1) is connected with plasma generator (2) by high-voltage ignition cable, and the external metallization screen layer of high-voltage ignition cable connects the positive pole and plasma generator (2) fitting seat of ignition exciter unit (1); The inner core of high-voltage ignition cable connects the negative pole of ignition exciter unit (1) and the interior utmost point of plasma generator (2).
2, high-energy plasma igniter of gas turbine according to claim 1, it is characterized in that: the cooling of plasma generator (2) electrode comprises fuel cools and air cooling, air is entered by the cavity between fitting seat (8) and the anode (5), and antianode (5) cooling back is sprayed by the gap between anode (5) and the negative electrode (7); Fuel oil is by the inner ejection of negative electrode (7).
3, high-energy plasma igniter of gas turbine according to claim 1 and 2 is characterized in that: the teflon insulation layer is arranged between the screen layer of high-voltage ignition cable and inner core, and the isolation layer average thickness is greater than 2mm.
4, high-energy plasma igniter of gas turbine according to claim 1 and 2 is characterized in that: the pointed cone of the head of negative electrode (5) is inlaid with the zirconium metallic material.
5, high-energy plasma igniter of gas turbine according to claim 3 is characterized in that: the pointed cone of the head of negative electrode (5) is inlaid with the zirconium metallic material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100712397A CN101463764B (en) | 2009-01-09 | 2009-01-09 | High-energy plasma igniter of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100712397A CN101463764B (en) | 2009-01-09 | 2009-01-09 | High-energy plasma igniter of gas turbine |
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| CN101463764A true CN101463764A (en) | 2009-06-24 |
| CN101463764B CN101463764B (en) | 2010-09-08 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102720589A (en) * | 2012-07-10 | 2012-10-10 | 烟台龙源电力技术股份有限公司 | Plasma body igniter and gas turbine |
| CN102980209A (en) * | 2012-11-27 | 2013-03-20 | 哈尔滨工程大学 | Plasma catalysis ignition integrated nozzle |
| CN102980204A (en) * | 2012-11-27 | 2013-03-20 | 哈尔滨工程大学 | Fuel-atomizing integrated igniter |
| CN109618482A (en) * | 2019-01-16 | 2019-04-12 | 烟台龙源电力技术股份有限公司 | Pulsating arc plasma generator, burner and combustion apparatus |
| CN109630279A (en) * | 2019-01-17 | 2019-04-16 | 中国人民解放军空军工程大学 | Porous atomizing plasma body fuel nozzle |
| CN112796892A (en) * | 2020-10-27 | 2021-05-14 | 中国船舶重工集团公司第七0三研究所 | Gas turbine plasma igniter with array type suspension electrode structure |
| CN114109614A (en) * | 2021-11-05 | 2022-03-01 | 苏州凯德航空科技有限公司 | Rapid ignition system and ignition method of micro turbojet engine |
| CN115856397A (en) * | 2022-12-09 | 2023-03-28 | 哈尔滨工程大学 | Discharge voltage measurement auxiliary tool of plasma ignition system |
| CN114109614B (en) * | 2021-11-05 | 2024-06-07 | 苏州凯德航空科技有限公司 | Rapid ignition system and ignition method for miniature turbojet engine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4161937A (en) * | 1976-07-21 | 1979-07-24 | Gerry Martin E | Igniter with magnetic activation |
| US4264844A (en) * | 1978-09-29 | 1981-04-28 | Axe Gavin C H | Electrical igniters |
| CN1230660A (en) * | 1998-03-31 | 1999-10-06 | 烟台开发区龙源电力燃烧控制工程有限公司 | Emitting gun for plasma ignitor |
| CN2883947Y (en) * | 2006-01-06 | 2007-03-28 | 哈尔滨工程大学 | Pulse plasma ignitor |
| CN2927444Y (en) * | 2006-04-10 | 2007-07-25 | 徐州燃烧控制研究院有限公司 | Large-power plasma ignition switch power supply |
-
2009
- 2009-01-09 CN CN2009100712397A patent/CN101463764B/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102720589A (en) * | 2012-07-10 | 2012-10-10 | 烟台龙源电力技术股份有限公司 | Plasma body igniter and gas turbine |
| CN102980209A (en) * | 2012-11-27 | 2013-03-20 | 哈尔滨工程大学 | Plasma catalysis ignition integrated nozzle |
| CN102980204A (en) * | 2012-11-27 | 2013-03-20 | 哈尔滨工程大学 | Fuel-atomizing integrated igniter |
| CN102980209B (en) * | 2012-11-27 | 2015-02-25 | 哈尔滨工程大学 | Plasma catalysis ignition integrated nozzle |
| CN109618482A (en) * | 2019-01-16 | 2019-04-12 | 烟台龙源电力技术股份有限公司 | Pulsating arc plasma generator, burner and combustion apparatus |
| CN109630279A (en) * | 2019-01-17 | 2019-04-16 | 中国人民解放军空军工程大学 | Porous atomizing plasma body fuel nozzle |
| CN112796892A (en) * | 2020-10-27 | 2021-05-14 | 中国船舶重工集团公司第七0三研究所 | Gas turbine plasma igniter with array type suspension electrode structure |
| CN114109614A (en) * | 2021-11-05 | 2022-03-01 | 苏州凯德航空科技有限公司 | Rapid ignition system and ignition method of micro turbojet engine |
| CN114109614B (en) * | 2021-11-05 | 2024-06-07 | 苏州凯德航空科技有限公司 | Rapid ignition system and ignition method for miniature turbojet engine |
| CN115856397A (en) * | 2022-12-09 | 2023-03-28 | 哈尔滨工程大学 | Discharge voltage measurement auxiliary tool of plasma ignition system |
| CN115856397B (en) * | 2022-12-09 | 2023-08-25 | 哈尔滨工程大学 | Discharge voltage measurement auxiliary tool of plasma ignition system |
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| CN101463764B (en) | 2010-09-08 |
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Granted publication date: 20100908 Termination date: 20170109 |