CN110886657A - Plasma ignition system of air-breathing engine - Google Patents
Plasma ignition system of air-breathing engine Download PDFInfo
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- CN110886657A CN110886657A CN201911042837.1A CN201911042837A CN110886657A CN 110886657 A CN110886657 A CN 110886657A CN 201911042837 A CN201911042837 A CN 201911042837A CN 110886657 A CN110886657 A CN 110886657A
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- voltage electrode
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The invention discloses a plasma ignition system of an air-breathing engine, belonging to the technical field of engine ignition and comprising: the ignition device comprises a gas leading pipeline, an oil supply pipeline, a power supply and an igniter shell; a high-voltage electrode and a low-voltage electrode are arranged in the igniter shell, the high-voltage electrode and the low-voltage electrode are both hollow cylinders, the low-voltage electrode is coaxially arranged outside the high-voltage electrode, and an annular cavity is formed between the high-voltage electrode and the low-voltage electrode; two ends of the oil supply pipeline are respectively communicated with an oil supply system of the engine and the annular cavity in the shell of the igniter; two ends of the bleed air pipeline are respectively communicated with an air inlet channel of the engine and an annular cavity in the shell of the igniter; the power supply is arranged in the engine shell and is respectively and electrically connected with the high-voltage electrode and the low-voltage electrode in the igniter shell through leads; the ignition system has the characteristics of high system integration level, wide ignition range and excellent comprehensive performance.
Description
Technical Field
The invention belongs to the technical field of engine ignition, and particularly relates to a plasma ignition system of an air-breathing engine.
Background
In order to meet the use requirements of a wide-range, long-range and high-mobility high-speed aircraft, when the engine is in a transition state, large-mobility flight state or the working state is greatly changed, instantaneous or continuous complex disturbance can be caused, so that the problem of engine working flameout is easily caused, and therefore the engine is required to have the capabilities of quick response, reliable and stable working and multiple ignition in a large airspace range.
At present, a smoke-fire igniter and a spark plug igniter are generally adopted as ignition devices in domestic and foreign air-breathing engines, wherein the smoke-fire igniter has the characteristics of good ignition performance and short ignition delay time, but the repeated ignition of the engine cannot be realized, and the ignition of the spark plug cannot meet the wide-area ignition requirement of the engine.
Disclosure of Invention
In view of the above, the invention provides an air-breathing engine plasma ignition system, which can realize reliable ignition of an engine in a wider flight Mach number range and a wider flight Mach number range, and has multiple ignition capability, so that an aircraft can better realize remote, high-speed and high-maneuvering flight, and the working performance and the viability of the aircraft are improved; on the other hand, the plasma ignition system adopts the incoming air of the engine and the fuel oil to mix to form combustible mixed gas, so that the system sharing can be effectively realized, and the weight and the size of the ignition system product are reduced by the integrated design of the ignition system and the engine; the ignition system has the characteristics of high system integration level, wide ignition range and excellent comprehensive performance.
The invention is realized by the following technical scheme:
an air breathing engine plasma ignition system comprising: the ignition device comprises a gas leading pipeline, an oil supply pipeline, a power supply and an igniter shell;
the gas outlet of the igniter shell is connected with the gas inlet of a combustion chamber of an engine, a high-voltage electrode and a low-voltage electrode are arranged in the igniter shell, the high-voltage electrode and the low-voltage electrode are both hollow cylinders, the low-voltage electrode is coaxially arranged outside the high-voltage electrode, and an annular cavity is formed between the high-voltage electrode and the low-voltage electrode;
two ends of the oil supply pipeline are respectively communicated with an oil supply system of the engine and the annular cavity in the shell of the igniter; the oil supply pipeline is used for introducing fuel oil in the oil supply system into the ignition system, and the introduced fuel oil is used as fuel and ionization working medium for the ignition system to work;
two ends of the bleed air pipeline are respectively communicated with an air inlet channel of the engine and an annular cavity in the shell of the igniter; the air guide pipeline is used for introducing air flow of the air inlet channel into the ignition system, mixing the air flow with fuel oil introduced by the engine oil supply system in an annular cavity in the shell of the ignition system to form combustible mixed gas, and taking the introduced air flow as an oxidant and an ionization working medium for the operation of the ignition system;
the power supply is arranged in the engine shell and is respectively and electrically connected with the high-voltage electrode and the low-voltage electrode in the igniter shell through leads; the power supply is used for providing discharge energy input for the high-voltage electrode and the low-voltage electrode under the control of an ignition control signal of the engine, a potential difference is formed between the high-voltage electrode and the low-voltage electrode, and a premixed part of combustible mixed gas in the shell of the igniter is ionized to form plasma.
Furthermore, the number of the air introducing pipelines is two, and one air introducing pipeline introduces air flow into an annular cavity in the shell of the igniter along the radial direction of the low-voltage electrode; the other air guide pipeline guides the air flow into the hollow part of the high-voltage electrode along the axial direction of the high-voltage electrode.
Furthermore, the number of the oil supply pipelines is two, and one oil supply pipeline introduces fuel oil into the annular cavity of the igniter shell along the radial direction of the low-voltage electrode; the other oil supply line introduces the fuel oil into the hollow portion of the high voltage electrode in the axial direction of the high voltage electrode.
Has the advantages that:
(1) the incoming air is introduced into the air inlet channel of the engine and is mixed with the fuel oil introduced by the oil supply system to form combustible mixed gas, the combustible mixed gas is ionized to form plasma in the process of flowing through the annular cavity formed between the high-voltage electrode and the low-voltage electrode, and after the plasma ignites the combustible mixed gas, high-temperature fuel gas is generated and is sprayed into high-speed airflow of a combustion chamber of the engine to ignite the engine, so that the high integration of the ignition system and the engine is realized, the complexity of the system is reduced, and the practicability of the ignition system is improved; the ignition system can work for a long time, the energy of the ignition system can be injected into a combustion chamber of the engine to expand the working airspace of the engine and improve the maneuvering performance of the engine, and meanwhile, the ignition system can be started for multiple times by repeatedly supplying power and fuel oil and air, so that the problems of multiple starting of the engine and maneuvering flight flameout are effectively solved.
(2) The air-entraining pipeline introduces air flow to the hollow part of the high-voltage electrode along the axial direction of the igniter shell, and the air flow has high flow velocity, so that the penetrability of combustible mixed gas and high-temperature fuel gas after the combustible mixed gas is combusted can be improved, and the working boundary of an ignition system is further enhanced.
(3) Compared with a spark plug type igniter, the plasma ignition system has a wide working range; the ignition cost-efficiency ratio is higher than 40%; the energy designability of the ignition system is strong, and the air intake quantity and the fuel flow of the ignition system can be designed according to the working range and the size of the engine, so that the energy and the capacity of the ignition system are designed.
(4) Compared with a firework igniter, the igniter can realize multiple times of ignition, the working time of an ignition system is long, and the working time of the ignition system can be expanded from the second level to the minute level of the traditional igniter, so that the functions of supporting combustion and widening the boundary of an engine can be realized.
Drawings
FIG. 1 is a schematic structural composition of the present invention;
FIG. 2 is a schematic view of the bleed air line;
FIG. 3 is a left side view of FIG. 2;
the device comprises a gas drainage pipeline 1, an oil supply pipeline 2, a power supply 3, a low-voltage electrode 4 and a high-voltage electrode 5.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The present embodiment provides a plasma ignition system for an air breathing engine, see fig. 1, comprising: the ignition device comprises a gas leading pipeline 1, an oil supply pipeline 2, a power supply 3 and an igniter shell;
an opening at one end of the igniter shell serves as an air outlet and is connected with an air inlet of a combustion chamber of an engine, a high-voltage electrode 5, a low-voltage electrode 4 and an insulating ring are arranged in the igniter shell, the high-voltage electrode 5 and the low-voltage electrode 4 are both hollow cylinders, the low-voltage electrode 4 is coaxially arranged outside the high-voltage electrode 5, an annular cavity is formed between the high-voltage electrode 5 and the low-voltage electrode 4, and the insulating ring is arranged at one end of the annular cavity to realize the insulating isolation between the high-voltage electrode 5 and the low-voltage;
the oil supply pipeline 2 is arranged between an oil supply system of the engine and an igniter shell, and two ends of the oil supply pipeline 2 are respectively communicated with the oil supply system and an annular cavity between the high-voltage electrode 5 and the low-voltage electrode 4; the oil supply pipeline 2 is used for introducing fuel oil in the oil supply system into the ignition system, and the introduced fuel oil is used as fuel and ionization working medium for the ignition system to work; one or two oil supply pipelines 2 are provided, when one oil supply pipeline 2 is provided, one end of the oil supply pipeline 2 is communicated with an oil supply system, and the other end of the oil supply pipeline 2 extends into the annular cavity of the igniter shell along the radial direction of the low-voltage electrode 4 and is communicated with the annular cavity; when the number of the oil supply pipelines 2 is two, one oil supply pipeline 2 extends into the annular cavity of the igniter shell along the radial direction of the low-voltage electrode 4 and is communicated with the annular cavity; one end of the other oil supply pipeline 2 is communicated with an oil supply system, and the other end of the other oil supply pipeline extends into the hollow part of the high-voltage electrode 5 along the axial direction of the high-voltage electrode 5 and is communicated with the hollow part;
referring to fig. 2 and fig. 3, two bleed air pipes 1 are both installed between an air inlet channel of an engine and an igniter housing, wherein one end of one bleed air pipe 1 is communicated with the air inlet channel, and the other end of the bleed air pipe 1 extends into an annular cavity of the igniter housing along the radial direction of a low-voltage electrode 4 and is communicated with the annular cavity; one end of the other bleed pipeline 1 is communicated with the air inlet channel, and the other end of the bleed pipeline extends into the hollow part of the high-voltage electrode 5 along the axial direction of the high-voltage electrode 5 and is communicated with the hollow part; the gas-leading pipeline 1 is used for leading high-temperature and high-speed air flow of an air inlet channel into an ignition system, mixing the air flow with fuel oil led in by an engine oil supply system in an annular cavity in an igniter shell to form combustible mixed gas, taking the led air flow as an oxidant and an ionization working medium for the work of the ignition system, and leading the led air flow into the ignition system along two modes, namely the axial direction and the radial direction of a high-voltage electrode 5; the air flow which is introduced into the annular cavity along the radial direction is mixed with fuel oil to form combustible mixed gas, and then the combustible mixed gas can be ionized in the annular cavity; the air flow introduced into the hollow part of the high-voltage electrode 5 along the axial direction has high flow velocity, so that the penetration capacity of combustible mixed gas and high-temperature fuel gas after the combustible mixed gas is combusted can be improved, and the working boundary of an ignition system is further enhanced; after entering the ignition system, the two air flows can strengthen the mixing of the air flow and the fuel oil, thereby providing favorable conditions for ignition and combustion of the ignition system;
the power supply 3 is arranged in the engine shell and is respectively and electrically connected with the high-voltage electrode 5 and the low-voltage electrode 4 in the igniter shell through leads; the power supply 3 is used for providing high-frequency discharge energy input for the high-voltage electrode 5 and the low-voltage electrode 4 under the control of an ignition control signal of the engine, and a high potential difference is formed between the high-voltage electrode 5 and the low-voltage electrode 4, so that part of premixed combustible mixed gas in the annular cavity of the igniter shell is ionized, and plasma with high activity is formed.
The working principle is as follows: the ignition system is characterized in that the air guide pipeline 1 introduces high-temperature and high-speed air of an air inlet passage of the engine into the ignition system, the oil supply pipeline 2 is used for introducing fuel oil in the oil supply system into the ignition system, the air and the fuel oil are mixed in an annular cavity of an igniter shell to form combustible mixed gas, the combustible mixed gas is ionized to form plasma in the process of flowing through the annular cavity formed between the high-voltage electrode 5 and the low-voltage electrode 4, the plasma directly generates or generates a large amount of active free radicals through chemical reaction, the chemical reaction strength is directly enhanced, or the chemical reaction temperature is reduced, the plasma and the active free radicals ignite the combustible mixed gas which is not ionized, the fuel oil and the air reach a set proportion, the combustible mixed gas is combusted to form high-temperature fuel gas, the high-speed gas flow which is sprayed into a combustion chamber of the engine is used for igniting the, and the purpose of ignition or stable combustion and combustion supporting is achieved. When the high-temperature fuel gas is sprayed into a combustion chamber of the engine, the high-temperature fuel gas is subjected to axial impulse force of air flow along the axial direction or combustible mixed gas formed by the air flow and fuel oil, so that the penetration capacity of the combustible mixed gas and the high-temperature fuel gas after the combustible mixed gas is combusted can be improved, and the working boundary of an ignition system is further enhanced; because the ignition system can work for a long time, the energy of the ignition system can be injected into the engine combustion chamber to expand the working airspace of the engine and improve the maneuvering performance of the engine, and meanwhile, the ignition system can be started for many times by repeatedly supplying power and fuel oil and air, thereby effectively solving the problems of repeated starting of the engine and maneuvering flight flameout.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. An induction engine plasma ignition system, comprising: the igniter comprises a gas guiding pipeline (1), an oil supply pipeline (2), a power supply (3) and an igniter shell;
the gas outlet of the igniter shell is connected with the gas inlet of a combustion chamber of an engine, a high-voltage electrode (5) and a low-voltage electrode (4) are arranged in the igniter shell, the high-voltage electrode (5) and the low-voltage electrode (4) are both hollow cylinders, the low-voltage electrode (4) is coaxially arranged outside the high-voltage electrode (5), and an annular cavity is formed between the high-voltage electrode (5) and the low-voltage electrode (4);
two ends of the oil supply pipeline (2) are respectively communicated with an oil supply system of the engine and an annular cavity in the shell of the igniter; the oil supply pipeline (2) is used for introducing fuel oil in the oil supply system into the ignition system, and the introduced fuel oil is used as fuel and ionization working medium for the ignition system to work;
two ends of the bleed air pipeline (1) are respectively communicated with an air inlet channel of the engine and an annular cavity in the shell of the igniter; the air guide pipeline (1) is used for introducing air flow of an air inlet channel into an ignition system, mixing the air flow with fuel oil introduced by an engine oil supply system in an annular cavity in an igniter shell to form combustible mixed gas, and taking the introduced air flow as an oxidant and an ionization working medium for the ignition system to work;
the power supply (3) is arranged in the engine shell and is respectively and electrically connected with the high-voltage electrode (5) and the low-voltage electrode (4) in the igniter shell through leads; the power supply (3) is used for providing discharge energy input for the high-voltage electrode (5) and the low-voltage electrode (4) under the control of an ignition control signal of the engine, a potential difference is formed between the high-voltage electrode (5) and the low-voltage electrode (4), and a premixed part of combustible mixed gas in the igniter shell is ionized to form plasma.
2. An aspirated engine plasma ignition system according to claim 1, characterized in that said bleed air lines (1) are two, one bleed air line (1) introducing the air flow radially along the low voltage electrode (4) into the annular cavity inside the igniter housing; the other air-bleed pipeline (1) introduces air flow into the hollow part of the high-voltage electrode (5) along the axial direction of the high-voltage electrode (5).
3. A plasma ignition system for an air-breathing engine according to claim 2, characterised in that said oil supply lines (2) are two, one oil supply line (2) introducing fuel into the annular cavity of the igniter housing in the radial direction of the low-voltage electrode (4); the other oil supply line (2) introduces fuel into the hollow portion of the high voltage electrode (5) in the axial direction of the high voltage electrode (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911042837.1A CN110886657A (en) | 2019-10-30 | 2019-10-30 | Plasma ignition system of air-breathing engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911042837.1A CN110886657A (en) | 2019-10-30 | 2019-10-30 | Plasma ignition system of air-breathing engine |
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| Publication Number | Publication Date |
|---|---|
| CN110886657A true CN110886657A (en) | 2020-03-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911042837.1A Pending CN110886657A (en) | 2019-10-30 | 2019-10-30 | Plasma ignition system of air-breathing engine |
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| CN (1) | CN110886657A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112761819A (en) * | 2021-01-15 | 2021-05-07 | 北京动力机械研究所 | Microminiature intelligent adjustable ignition system and adjusting method |
| CN113217196A (en) * | 2021-03-03 | 2021-08-06 | 中国人民解放军空军工程大学 | Self-air-entraining sliding arc plasma jet igniter of concave cavity flame stabilizer and ignition method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5449966A (en) * | 1991-04-26 | 1995-09-12 | Wojciech Marian Turkowski | Double sliding spark plug - thunder II |
| CN104879780A (en) * | 2014-02-28 | 2015-09-02 | 北京大学 | Multichannel plasma area igniting burner |
| CN105910134A (en) * | 2016-04-14 | 2016-08-31 | 北京大学 | Plasma ignition combustion-supporting system |
| US20160356501A1 (en) * | 2014-05-08 | 2016-12-08 | Fgc Plasma Solutions Llc | Method and apparatus for assisting with the combustion of fuel |
| CN107816387A (en) * | 2017-10-24 | 2018-03-20 | 哈尔滨工业大学 | A kind of three electrode is expanded discharge channel size device and is expanded the method for discharge channel size using the device |
| CN109611214A (en) * | 2018-11-07 | 2019-04-12 | 中国人民解放军空军工程大学 | Swipe plasma jet igniter |
-
2019
- 2019-10-30 CN CN201911042837.1A patent/CN110886657A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5449966A (en) * | 1991-04-26 | 1995-09-12 | Wojciech Marian Turkowski | Double sliding spark plug - thunder II |
| CN104879780A (en) * | 2014-02-28 | 2015-09-02 | 北京大学 | Multichannel plasma area igniting burner |
| US20160356501A1 (en) * | 2014-05-08 | 2016-12-08 | Fgc Plasma Solutions Llc | Method and apparatus for assisting with the combustion of fuel |
| CN105910134A (en) * | 2016-04-14 | 2016-08-31 | 北京大学 | Plasma ignition combustion-supporting system |
| CN107816387A (en) * | 2017-10-24 | 2018-03-20 | 哈尔滨工业大学 | A kind of three electrode is expanded discharge channel size device and is expanded the method for discharge channel size using the device |
| CN109611214A (en) * | 2018-11-07 | 2019-04-12 | 中国人民解放军空军工程大学 | Swipe plasma jet igniter |
Non-Patent Citations (1)
| Title |
|---|
| 雷向东等: "等离子点火系统点火试验研究", 《中国航天第三专业信息网第三十八届技术交流会暨第二届空天动力联合会议》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112761819A (en) * | 2021-01-15 | 2021-05-07 | 北京动力机械研究所 | Microminiature intelligent adjustable ignition system and adjusting method |
| CN113217196A (en) * | 2021-03-03 | 2021-08-06 | 中国人民解放军空军工程大学 | Self-air-entraining sliding arc plasma jet igniter of concave cavity flame stabilizer and ignition method |
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