CN112065591A - Electromagnetic drive formula ignition for aeroengine - Google Patents
Electromagnetic drive formula ignition for aeroengine Download PDFInfo
- Publication number
- CN112065591A CN112065591A CN202010952504.9A CN202010952504A CN112065591A CN 112065591 A CN112065591 A CN 112065591A CN 202010952504 A CN202010952504 A CN 202010952504A CN 112065591 A CN112065591 A CN 112065591A
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- ceramic ball
- hollow ceramic
- mounting arm
- electromagnetic wave
- combustion chamber
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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)
- Plasma Technology (AREA)
Abstract
An electromagnetic drive type ignition device for an aircraft engine comprises an electromagnetic wave generator and a plasma generating mechanism, wherein the electromagnetic wave generator is positioned outside a combustion chamber casing, and the plasma generating mechanism is positioned inside the combustion chamber casing; the plasma generating mechanism comprises a first hollow ceramic ball, a second hollow ceramic ball, a first mounting arm and a second mounting arm; one end of the first mounting arm is fixedly connected to the inner surface of the combustion chamber casing, and the first hollow ceramic ball is fixedly mounted at the other end of the first mounting arm; one end of a second mounting arm is hinged to the middle of the first mounting arm, a second hollow ceramic ball is fixedly mounted at the other end of the second mounting arm, and the second hollow ceramic ball is positioned right below the first hollow ceramic ball; the first hollow ceramic ball and the second hollow ceramic ball are filled with inorganic salt water solution; the electromagnetic wave transmitting direction of the electromagnetic wave generator faces the first hollow ceramic ball and the second hollow ceramic ball; the rotation amplitude of the second mounting arm around the hinge point is less than or equal to 1 degree; the first hollow ceramic ball and the second hollow ceramic ball are positioned right in front of the fuel nozzle.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to an electromagnetic drive type ignition device for an aero-engine.
Background
At present, all ignition devices adopted by aircraft engines are of a high-voltage discharge type, the voltage is increased by repeated action of induction coils until the voltage is increased from 30V to more than 3000V, and then a main combustion chamber or an afterburning chamber of the aircraft engine is ignited in an instantaneous discharge mode.
However, the conventional high-voltage discharge type ignition device is heavy in structure, and a lead shell is required to prevent radiation of radioactive substances, so that once the lead shell is damaged, serious damage is caused to a human body. Meanwhile, in the ignition process of the aircraft engine, a certain time is needed for accumulating voltage, so that the ignition time is prolonged. In addition, with the supporting fuel oil feeding system who uses of traditional high pressure discharge formula ignition, still need carry out the chronogenesis with ignition's electric energy accumulation to increased the complexity of avionics system to its control. In the actual ignition process, a certain proportion of unsuccessful ignition still exists, so that the safety, reliability and maintainability of the aircraft engine are greatly reduced.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides an electromagnetic drive type ignition device for an aircraft engine, which is simple in structure, can reduce the weight of the aircraft engine by 3-5 kg, does not need to open a hole on a combustion chamber casing during installation, does not need physical connection between the inside and the outside of the combustion chamber casing, simultaneously uses electromagnetic waves as an energy source to drive a plasma generating mechanism inside the combustion chamber casing to generate high-energy plasma jet so as to realize the ignition of the aircraft engine, reduces the ignition time by more than 30 seconds compared with the traditional high-voltage discharge type ignition device, and greatly improves the safety, the reliability and the maintainability of the aircraft engine.
In order to achieve the purpose, the invention adopts the following technical scheme: an electromagnetic drive type ignition device for an aircraft engine comprises an electromagnetic wave generator and a plasma generating mechanism, wherein the electromagnetic wave generator is arranged outside a combustion chamber casing, and the plasma generating mechanism is arranged inside the combustion chamber casing; the plasma generating mechanism comprises a first hollow ceramic ball, a second hollow ceramic ball, a first mounting arm and a second mounting arm; one end of the first mounting arm is fixedly connected to the inner surface of the combustion chamber casing, and the first hollow ceramic ball is fixedly mounted at the other end of the first mounting arm; one end of the second mounting arm is hinged to the middle of the first mounting arm, the second hollow ceramic ball is fixedly mounted at the other end of the second mounting arm, and the second hollow ceramic ball is positioned right below the first hollow ceramic ball; inorganic salt aqueous solution is hermetically filled in the first hollow ceramic ball and the second hollow ceramic ball; the electromagnetic wave emitting direction of the electromagnetic wave generator faces the first hollow ceramic ball and the second hollow ceramic ball.
The rotation amplitude of the second mounting arm around the hinge point is not more than 1 degree.
The first hollow ceramic ball and the second hollow ceramic ball are positioned right in front of the fuel nozzle.
The invention has the beneficial effects that:
the electromagnetic driving type ignition device for the aero-engine is simple in structure, the aero-engine can be lightened by 3-5 kg, holes do not need to be formed in a combustion chamber casing during installation, the combustion chamber casing does not need to be physically connected inside and outside, meanwhile, electromagnetic waves are used as an energy source to drive a plasma generating mechanism inside the combustion chamber casing to generate high-energy plasma jet so as to achieve ignition of the aero-engine, the ignition time is shortened by more than 30 seconds compared with that of a traditional high-voltage discharge type ignition device, and safety, reliability and maintainability of the aero-engine are greatly improved.
Drawings
Fig. 1 is a schematic structural diagram (before ignition) of an electromagnetic drive type ignition device for an aircraft engine according to the present invention;
fig. 2 is a schematic structural diagram (in ignition) of an electromagnetic drive type ignition device for an aircraft engine according to the present invention;
in the figure, 1-an electromagnetic wave generator, 2-a combustion chamber casing, 3-a first hollow ceramic ball, 4-a second hollow ceramic ball, 5-a first mounting arm, 6-a second mounting arm, and 7-a fuel nozzle.
Detailed Description
The invention is described in further detail below with reference to the figures and the specific embodiments.
As shown in fig. 1 and 2, an electromagnetic drive type ignition device for an aircraft engine comprises an electromagnetic wave generator 1 and a plasma generating mechanism, wherein the electromagnetic wave generator 1 is installed outside a combustion chamber casing 2, and the plasma generating mechanism is installed inside the combustion chamber casing 2; the plasma generating mechanism comprises a first hollow ceramic ball 3, a second hollow ceramic ball 4, a first mounting arm 5 and a second mounting arm 6; one end of the first mounting arm 5 is fixedly connected to the inner surface of the combustion chamber casing 2, and the first hollow ceramic ball 3 is fixedly mounted at the other end of the first mounting arm 5; one end of the second mounting arm 6 is hinged to the middle of the first mounting arm 5, the second hollow ceramic ball 4 is fixedly mounted at the other end of the second mounting arm 6, and the second hollow ceramic ball 4 is positioned under the first hollow ceramic ball 3; inorganic salt aqueous solution is hermetically filled in the first hollow ceramic ball 3 and the second hollow ceramic ball 4; the electromagnetic wave emitting direction of the electromagnetic wave generator 1 faces the first hollow ceramic balls 3 and the second hollow ceramic balls 4.
The second mounting arm 6 has a rotation amplitude around the hinge point of not more than 1 deg..
The first hollow ceramic ball 3 and the second hollow ceramic ball 4 are located right in front of the fuel nozzle 7.
The one-time use process of the present invention is described below with reference to the accompanying drawings:
before ignition, the second hollow ceramic ball 4 will automatically be in the lower limit position under the action of gravity, and at this time, an initial gap is formed between the second hollow ceramic ball 4 and the first hollow ceramic ball 3 above without contact. When the engine is started, the second hollow ceramic ball 4 is blown up under the action of air flow and is contacted with the first hollow ceramic ball 3, the electromagnetic wave generator 1 outside the combustion chamber casing 2 is started, the electromagnetic wave generator 1 generates electromagnetic waves with the vibration frequency of 2450MHz per second, after the electromagnetic waves irradiate the first hollow ceramic ball 3 and the second hollow ceramic ball 4, the electromagnetic waves and the inorganic salt water solution react to form resonance in the two ceramic balls, a high-energy electromagnetic field is generated at the contact position of the first hollow ceramic ball 3 and the second hollow ceramic ball 4, high-energy plasma jet is generated at the contact position of the two ceramic balls, and when an oil-gas mixture formed by fuel oil and air flow sprayed from the fuel nozzle 7 passes through a high-energy plasma jet point, the oil-gas mixture is ignited, and finally the ignition of the aeroengine is realized.
The embodiments are not intended to limit the scope of the present invention, and all equivalent implementations or modifications without departing from the scope of the present invention are intended to be included in the scope of the present invention.
Claims (3)
1. An electromagnetic drive formula ignition for aeroengine which characterized in that: the plasma generator comprises an electromagnetic wave generator and a plasma generating mechanism, wherein the electromagnetic wave generator is arranged outside a combustion chamber casing, and the plasma generating mechanism is arranged inside the combustion chamber casing; the plasma generating mechanism comprises a first hollow ceramic ball, a second hollow ceramic ball, a first mounting arm and a second mounting arm; one end of the first mounting arm is fixedly connected to the inner surface of the combustion chamber casing, and the first hollow ceramic ball is fixedly mounted at the other end of the first mounting arm; one end of the second mounting arm is hinged to the middle of the first mounting arm, the second hollow ceramic ball is fixedly mounted at the other end of the second mounting arm, and the second hollow ceramic ball is positioned right below the first hollow ceramic ball; inorganic salt aqueous solution is hermetically filled in the first hollow ceramic ball and the second hollow ceramic ball; the electromagnetic wave emitting direction of the electromagnetic wave generator faces the first hollow ceramic ball and the second hollow ceramic ball.
2. An electromagnetic drive type ignition device for an aircraft engine according to claim 1, characterized in that: the rotation amplitude of the second mounting arm around the hinge point is not more than 1 degree.
3. An electromagnetic drive type ignition device for an aircraft engine according to claim 1, characterized in that: the first hollow ceramic ball and the second hollow ceramic ball are positioned right in front of the fuel nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010952504.9A CN112065591B (en) | 2020-09-11 | 2020-09-11 | Electromagnetic drive formula ignition for aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010952504.9A CN112065591B (en) | 2020-09-11 | 2020-09-11 | Electromagnetic drive formula ignition for aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112065591A true CN112065591A (en) | 2020-12-11 |
| CN112065591B CN112065591B (en) | 2021-08-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010952504.9A Active CN112065591B (en) | 2020-09-11 | 2020-09-11 | Electromagnetic drive formula ignition for aeroengine |
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| Country | Link |
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| CN (1) | CN112065591B (en) |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB637286A (en) * | 1947-05-29 | 1950-05-17 | British Thomson Houston Co Ltd | Improvements relating to ignition means for combustion chambers |
| FR1203516A (en) * | 1957-01-30 | 1960-01-19 | Bristol Aero Engines Ltd | Improvements to igniter devices for continuous internal combustion type drive trains |
| US5689949A (en) * | 1995-06-05 | 1997-11-25 | Simmonds Precision Engine Systems, Inc. | Ignition methods and apparatus using microwave energy |
| US5845480A (en) * | 1996-03-13 | 1998-12-08 | Unison Industries Limited Partnership | Ignition methods and apparatus using microwave and laser energy |
| US20030052011A1 (en) * | 2000-11-08 | 2003-03-20 | Zhuping Chen | Plasma electroplating |
| CN102121447A (en) * | 2011-01-21 | 2011-07-13 | 电子科技大学 | Magnetic coupling microwave plasma igniter for automobile engine |
| CN202001172U (en) * | 2011-01-21 | 2011-10-05 | 电子科技大学 | Microwave plasma automobile engine igniter |
| CN105611838A (en) * | 2013-07-19 | 2016-05-25 | 普罗赛索斯耐趣尔斯威尔库有限公司 | Accelerated freeze-drying of produce using microwaves |
| US9441546B2 (en) * | 2013-02-26 | 2016-09-13 | Pratt & Whitney Canada Corp. | Laser-ignition combustor for gas turbine engine |
| CN106907741A (en) * | 2017-02-16 | 2017-06-30 | 中国航发沈阳发动机研究所 | A kind of chamber structure |
| CN206442573U (en) * | 2017-02-16 | 2017-08-25 | 浙江全世科技有限公司 | A kind of microwave plasma torch device of automatic ignition |
| CN109905955A (en) * | 2019-03-13 | 2019-06-18 | 中国科学院微电子研究所 | Atomic state plasma forms device and its application |
| CN111006241A (en) * | 2019-12-03 | 2020-04-14 | 哈尔滨工程大学 | Plasma ignition and combustion-supporting combustion chamber for burning low-calorific-value gas fuel |
| US10899625B2 (en) * | 2015-07-21 | 2021-01-26 | Halliburton Energy Services, Inc. | Purifying diamond powder |
-
2020
- 2020-09-11 CN CN202010952504.9A patent/CN112065591B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB637286A (en) * | 1947-05-29 | 1950-05-17 | British Thomson Houston Co Ltd | Improvements relating to ignition means for combustion chambers |
| FR1203516A (en) * | 1957-01-30 | 1960-01-19 | Bristol Aero Engines Ltd | Improvements to igniter devices for continuous internal combustion type drive trains |
| US5689949A (en) * | 1995-06-05 | 1997-11-25 | Simmonds Precision Engine Systems, Inc. | Ignition methods and apparatus using microwave energy |
| US5845480A (en) * | 1996-03-13 | 1998-12-08 | Unison Industries Limited Partnership | Ignition methods and apparatus using microwave and laser energy |
| US20030052011A1 (en) * | 2000-11-08 | 2003-03-20 | Zhuping Chen | Plasma electroplating |
| CN202001172U (en) * | 2011-01-21 | 2011-10-05 | 电子科技大学 | Microwave plasma automobile engine igniter |
| CN102121447A (en) * | 2011-01-21 | 2011-07-13 | 电子科技大学 | Magnetic coupling microwave plasma igniter for automobile engine |
| US9441546B2 (en) * | 2013-02-26 | 2016-09-13 | Pratt & Whitney Canada Corp. | Laser-ignition combustor for gas turbine engine |
| CN105611838A (en) * | 2013-07-19 | 2016-05-25 | 普罗赛索斯耐趣尔斯威尔库有限公司 | Accelerated freeze-drying of produce using microwaves |
| US10899625B2 (en) * | 2015-07-21 | 2021-01-26 | Halliburton Energy Services, Inc. | Purifying diamond powder |
| CN106907741A (en) * | 2017-02-16 | 2017-06-30 | 中国航发沈阳发动机研究所 | A kind of chamber structure |
| CN206442573U (en) * | 2017-02-16 | 2017-08-25 | 浙江全世科技有限公司 | A kind of microwave plasma torch device of automatic ignition |
| CN109905955A (en) * | 2019-03-13 | 2019-06-18 | 中国科学院微电子研究所 | Atomic state plasma forms device and its application |
| CN111006241A (en) * | 2019-12-03 | 2020-04-14 | 哈尔滨工程大学 | Plasma ignition and combustion-supporting combustion chamber for burning low-calorific-value gas fuel |
Non-Patent Citations (1)
| Title |
|---|
| [英]理查德•布洛克利，[美]史维主编，毛军逵等译: "《航空航天科技出版工程.2.推进与动力》", 30 June 2016, 北京理工大学出版社 * |
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| CN112065591B (en) | 2021-08-03 |
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