CN115218222B - Rotary sliding arc plasma intensified combustion cyclone device - Google Patents
Rotary sliding arc plasma intensified combustion cyclone device Download PDFInfo
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- CN115218222B CN115218222B CN202210693987.4A CN202210693987A CN115218222B CN 115218222 B CN115218222 B CN 115218222B CN 202210693987 A CN202210693987 A CN 202210693987A CN 115218222 B CN115218222 B CN 115218222B
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- Prior art keywords
- cyclone
- sleeve
- guide vane
- arc plasma
- sliding arc
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00008—Combustion techniques using plasma gas
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a rotary sliding arc plasma enhanced combustion cyclone device, which comprises a fuel nozzle, an insulating sleeve and a cyclone; the cyclone is of an integrated structure and comprises a primary cyclone and a secondary cyclone, the primary cyclone comprises a primary cyclone inner sleeve, a primary cyclone guide vane, a primary cyclone outer sleeve and a venturi, one end of the primary cyclone guide vane is fixedly connected with the outer side wall surface of the primary cyclone inner sleeve, the other end of the primary cyclone guide vane is fixedly connected with the inner side wall surface of the primary cyclone outer sleeve, and a pipe orifice at the air flow inlet end of the venturi is in butt joint with a pipe orifice at the air flow outlet end of the primary cyclone outer sleeve; wherein, the one-level swirler inner skleeve suit is in insulating sleeve's outside and with insulating sleeve fixed connection. The invention promotes the atomization and pyrolysis of the fuel and the full mixing of the active ingredient and the atomized fuel, simplifies the structure of the combustion chamber cyclone based on plasma excitation, and enhances the strength of the cyclone.
Description
Technical Field
The invention belongs to the technical field of gas turbine engines, and particularly relates to a rotary sliding arc plasma enhanced combustion cyclone device.
Background
The existing aeroengine combustion chamber has the significant practical problems of poor high-altitude fuel atomization quality, low combustion efficiency and insufficient ignition/flameout envelope, and the sliding arc plasma has obvious advantages in the aspects of improving the ignition capability of the aeroengine, widening the stable combustion range of the aeroengine and the like. As shown in fig. 1, the university of the air force engineering of the liberation army of Chinese people in 2018 discloses a rotary sliding arc plasma fuel oil cracking head of an aeroengine combustion chamber in the invention creation of publication number CN108180075a, and the device does not change the structural characteristics of the original combustion chamber, can improve the uniformity of mixing fuel and air, and generates active particles capable of accelerating combustion chemical reaction; however, the discharge area of the device is greatly influenced by the flow field, the adaptability to different incoming flows is weak, and certain fuel can pass only under the condition of large fuel atomization cone angle, so that the fuel cracking effect is not ideal. Meanwhile, the cyclone main body is formed by processing an Al2O3 ceramic material, the ceramic material has good high temperature resistance and insulativity, but the characteristics of high brittleness, low impact resistance and fragility are difficult to meet the strength requirement of the aeroengine in actual use, the cyclone main body is easy to vibrate and damage in flying, and the working reliability is poor.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, and provides a rotary sliding arc plasma enhanced combustion cyclone device which promotes the atomization cracking of fuel oil and the full mixing of active ingredients and atomized fuel oil under the action of a cyclone, and the cyclone adopts an integrated structure, so that the structure of an electrode arranged on the cyclone is avoided, the structure of the cyclone is simplified, the strength of the cyclone is enhanced, and the problems that the existing combustion chamber ceramic cyclone based on plasma excitation is difficult to meet the strength requirement of an aeroengine in actual use, is easily damaged due to vibration during flight and has poor working reliability are solved.
In order to achieve the above purpose, the invention adopts the following technical scheme: the rotary sliding arc plasma enhanced combustion cyclone device is characterized by comprising a fuel nozzle, an insulating sleeve and a cyclone, wherein the insulating sleeve is sleeved on the outer side of the fuel nozzle and is in clearance fit with the fuel nozzle; the cyclone is of an integrated structure and comprises a first-stage cyclone and a second-stage cyclone, the second-stage cyclone is arranged on the outer side of the first-stage cyclone, the first-stage cyclone comprises a first-stage cyclone inner sleeve, a first-stage cyclone guide vane, a first-stage cyclone outer sleeve and a venturi, one end of the first-stage cyclone guide vane is fixedly connected with the outer side wall surface of the first-stage cyclone inner sleeve, the other end of the first-stage cyclone guide vane is fixedly connected with the inner side wall surface of the first-stage cyclone outer sleeve, and a pipe orifice at the air flow inlet end of the venturi is in butt joint with a pipe orifice at the air flow outlet end of the first-stage cyclone outer sleeve; the primary cyclone inner sleeve is sleeved on the outer side of the insulating sleeve and fixedly connected with the insulating sleeve.
The rotary sliding arc plasma enhanced combustion cyclone device is characterized in that the cyclone is made of conductive metal materials and is connected with an anode high-voltage cable.
The rotary sliding arc plasma enhanced combustion cyclone device is characterized in that the insulating sleeve is a high-temperature-resistant ceramic insulating sleeve and is arranged between the cyclone and the fuel nozzle, so that the fuel nozzle and the cyclone are insulated, and sliding arc plasma is generated by discharging when high voltage is applied.
The rotary sliding arc plasma enhanced combustion cyclone device is characterized in that the insulating sleeve is fixedly connected with the primary cyclone inner sleeve in a cementing mode.
The rotary sliding arc plasma enhanced combustion cyclone device is characterized in that the secondary cyclone comprises a secondary cyclone guide vane, a secondary cyclone outer sleeve and a horn mouth, one end of the secondary cyclone guide vane is connected with the outer side wall surface of the primary cyclone outer sleeve, the other end of the secondary cyclone guide vane is connected with the inner side wall surface of the secondary cyclone outer sleeve, a pipe orifice at the gas inflow end of the horn mouth is in butt joint with a pipe orifice at the gas flow outlet end of the secondary cyclone outer sleeve, and the direction of the gas outlet end of the secondary cyclone guide vane is opposite to that of the gas outlet end of the primary cyclone guide vane.
The rotary sliding arc plasma enhanced combustion swirling device is characterized in that an outlet of the fuel nozzle is positioned at an inlet end of the venturi tube, and an inlet of the fuel nozzle connecting oil tube is arranged on an aircraft engine combustion chamber outer casing.
The rotary sliding arc plasma enhanced combustion cyclone device is characterized in that the fuel nozzle, the first-stage cyclone of the insulating sleeve and the second-stage cyclone are coaxially arranged.
The rotary sliding arc plasma enhanced combustion cyclone device is characterized in that the inner surface of the venturi tube is an arc-shaped surface, and the arc-shaped surface forms a converging section at the air inlet end of the venturi tube and an expanding section at the air outlet end of the venturi tube respectively.
Compared with the prior art, the invention has the following advantages:
1. according to the invention, on one hand, atomization cracking of fuel oil and full mixing of active ingredients and atomized fuel oil under the action of the cyclone are promoted, on the other hand, the cyclone adopts an integrated structure, so that the structure of an electrode arranged on the cyclone is avoided, the structure of the cyclone is simplified, the strength of the cyclone is enhanced, and the problems that the existing combustion chamber ceramic cyclone based on plasma excitation is difficult to meet the strength requirement of an aeroengine in actual use, is easy to damage due to vibration during flight and has poor working reliability are solved.
2. The plasma discharge part is closer to the fuel nozzle, the arc is rotationally stretched through the primary rotational flow, the discharge efficiency is improved, and the discharge part is on the necessary path for injecting fuel into the combustion chamber, so that the combustion stability is improved, the stable working range of the combustion chamber is widened, and the combustion efficiency of the combustion chamber of the aeroengine is improved.
3. The invention can be based on the metal cyclone adopted by the current engine cyclone combustion chamber, and does not change the original structure and parameters, thereby being easier to realize, reliable in work and long in service life.
4. According to the problems existing in the prior art, the cyclone and the combustion chamber head are integrally designed, the ceramic insulating sleeve is added, and the cyclone and the combustion chamber head are designed and reformed for multiple times, and are proved to be practical and have practical values through multiple tests.
The invention is described in further detail below with reference to the drawings and examples.
Drawings
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is a cross-sectional view of the present invention.
Fig. 3 is a schematic front view of the present invention.
Reference numerals illustrate:
10-a fuel nozzle; 20-an insulating sleeve; 30-a cyclone; 31-a primary cyclone inner sleeve; 32-primary cyclone guide vanes; 33-primary cyclone outer sleeve; 34-venturi; 35-a secondary cyclone guide vane; 36-a secondary cyclone outer sleeve; 37-flare.
Detailed Description
Embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. While the invention is susceptible of embodiment in the drawings, it is to be understood that the invention may be embodied in various forms and should not be construed as limited to the embodiments set forth herein, but rather are provided to provide a more thorough and complete understanding of the invention. It should be understood that the drawings and embodiments of the invention are for illustration purposes only and are not intended to limit the scope of the present invention.
As shown in fig. 1 to 3, the invention discloses a rotary sliding arc plasma enhanced combustion swirling device, which comprises a fuel nozzle 10, an insulating sleeve 20 and a swirler 30, wherein the insulating sleeve 20 is sleeved on the outer side of the fuel nozzle 10 and is in clearance fit with the fuel nozzle 10; the cyclone 30 is of an integrated structure and comprises a primary cyclone and a secondary cyclone, the secondary cyclone is arranged on the outer side of the primary cyclone, the primary cyclone comprises a primary cyclone inner sleeve 31, a primary cyclone guide vane 32, a primary cyclone outer sleeve 33 and a venturi 34, one end of the primary cyclone guide vane 32 is fixedly connected with the outer side wall surface of the primary cyclone inner sleeve 31, the other end of the primary cyclone guide vane 32 is fixedly connected with the inner side wall surface of the primary cyclone outer sleeve 33, and a nozzle at the air flow inlet end of the venturi 34 is in butt joint with a nozzle at the air flow outlet end of the primary cyclone outer sleeve 33; wherein, the first-stage cyclone inner sleeve 31 is sleeved outside the insulating sleeve 20 and fixedly connected with the insulating sleeve 20.
In this embodiment, the fuel nozzle 10 is connected to the fuel pipeline of the engine and commonly grounded, the cyclone 30 is used as the cathode of the exciter, the cathode and the anode are separated by the insulating sleeve 20, a plasma arc is generated between the cathode and the anode under the excitation of a strong electric field, and a rotary sliding arc discharge is formed under the driving of the rotary airflow of the cyclone. On one hand, the sliding arc plasma promotes the atomization and cracking of the fuel oil, and on the other hand, active components generated by the sliding arc discharge are fully mixed with the atomized fuel oil under the action of the cyclone, and meanwhile, the ignition and combustion supporting of the aeroengine combustion chamber are completed under the action of the temperature rise of the sliding arc plasma discharge. The cyclone 30 adopts an integrated structure, reduces the installation of the cyclone 30 and the electrode, enhances the strength of the cyclone, and solves the problems that the existing ceramic cyclone with a combustion chamber based on plasma excitation is difficult to meet the strength requirement of an aeroengine in actual use, is easy to be damaged due to vibration during flight and has poor working reliability.
In this embodiment, the cyclone 30 is made of conductive metal material and is connected to the anode high-voltage cable.
In this embodiment, the insulating sleeve 20 is a high temperature resistant ceramic insulating sleeve, and is disposed between the swirler 30 and the fuel nozzle 10, so that the fuel nozzle is insulated from the swirler 30, and a sliding arc is generated by discharging when a voltage is applied.
In this embodiment, the insulating sleeve 20 is fixedly connected to the primary cyclone inner sleeve 31 by an adhesive bonding manner.
As shown in fig. 1 to 3, the secondary cyclone comprises a secondary cyclone guide vane 35, a secondary cyclone outer sleeve 36 and a flare 37, one end of the secondary cyclone guide vane 35 is connected with the outer side wall surface of the primary cyclone outer sleeve 33, the other end of the secondary cyclone guide vane 35 is connected with the inner side wall surface of the secondary cyclone outer sleeve 36, the nozzle at the air inlet end of the flare 37 is in butt joint with the nozzle at the air outlet end of the secondary cyclone outer sleeve 36, and the direction of the air outlet end of the secondary cyclone guide vane 35 is opposite to that of the primary cyclone guide vane 32.
In this embodiment, the outlet of the fuel nozzle 10 is located at the inlet end of the venturi 34, and the inlet of the fuel nozzle 10 connecting oil pipe is installed on the combustion chamber casing of the aero-engine.
As shown in fig. 2, the fuel nozzle 10, the primary cyclone and the secondary cyclone of the insulating sleeve 20 are coaxially arranged.
As shown in fig. 2, the inner surface of the venturi 34 is an arc surface, and the arc surface forms a converging section at the air inlet end of the venturi 34 and an expanding section at the air outlet end of the venturi 34.
In this embodiment, the inner surface of the venturi 344 is of a convex arc structure, and two ends of the arc form a converging section at the air inlet end of the venturi 34 and a diverging section at the air outlet end of the venturi 34. The outer circumferential surface of the venturi 34 is a stepped surface, wherein the outer diameter at the rear end of the venturi 34 is smaller than the outer diameter at the front end. The venturi 34 is located within the combustor basket. The cable passes through the cable mounting hole of the flame tube of the combustion chamber of the aeroengine, is connected to the wall surface of the cyclone, and the other end is connected with high-voltage alternating current. The venturi 34 on the cyclone and the fuel nozzle 10 generate plasma discharge arc under the excitation of strong electric field, and the rotating sliding arc discharge is formed under the driving of the rotating airflow of the cyclone. On one hand, the sliding arc plasma promotes the atomization and cracking of the fuel oil, and on the other hand, active components generated by the sliding arc discharge are fully mixed with the atomized fuel oil under the action of the cyclone, and meanwhile, the ignition and combustion regulation of the combustion chamber are completed under the high temperature action of the sliding arc discharge plasma.
The foregoing description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and any simple modification, variation and equivalent structural transformation of the above embodiment according to the technical substance of the present invention still fall within the scope of the technical solution of the present invention.
Claims (7)
1. A rotary sliding arc plasma enhanced combustion swirling device, comprising:
a fuel nozzle (10);
the insulation sleeve (20) is sleeved on the outer side of the fuel nozzle (10) and is in clearance fit with the fuel nozzle (10);
the cyclone (30), cyclone (30) is an integral structure and comprises a first-stage cyclone and a second-stage cyclone, the second-stage cyclone is arranged on the outer side of the first-stage cyclone, the first-stage cyclone comprises a first-stage cyclone inner sleeve (31), a first-stage cyclone guide vane (32), a first-stage cyclone outer sleeve (33) and a venturi (34), one end of the first-stage cyclone guide vane (32) is fixedly connected with the outer side wall surface of the first-stage cyclone inner sleeve (31), the other end of the first-stage cyclone guide vane (32) is fixedly connected with the inner side wall surface of the first-stage cyclone outer sleeve (33), and a nozzle at the air flow inlet end of the venturi (34) is in butt joint with a nozzle at the air flow outlet end of the first-stage cyclone outer sleeve (33);
wherein, the first-stage cyclone inner sleeve (31) is sleeved outside the insulating sleeve (20) and is fixedly connected with the insulating sleeve (20);
the cyclone (30) is made of conductive metal material and is connected with the anode high-voltage cable.
2. A rotary sliding arc plasma enhanced combustion cyclone apparatus as claimed in claim 1, wherein the insulating sleeve (20) is a high temperature resistant ceramic insulating sleeve and is arranged between the cyclone (30) and the fuel nozzle (10) to insulate the fuel nozzle from the cyclone (30), and the sliding arc plasma is generated by discharging when a high voltage is applied.
3. A rotary sliding arc plasma enhanced combustion cyclone apparatus as in claim 1, wherein the insulating sleeve (20) is fixedly connected with the primary cyclone inner sleeve (31) by means of cementing.
4. A rotary sliding arc plasma enhanced combustion cyclone device as claimed in claim 1, wherein the secondary cyclone comprises a secondary cyclone guide vane (35), a secondary cyclone outer sleeve (36) and a flare (37), one end of the secondary cyclone guide vane (35) is connected with the outer side wall surface of the primary cyclone outer sleeve (33), the other end of the secondary cyclone guide vane (35) is connected with the inner side wall surface of the secondary cyclone outer sleeve (36), the nozzle at the air flow inlet end of the flare (37) is in butt joint with the nozzle at the air flow outlet end of the secondary cyclone outer sleeve (36), and the air outlet end direction of the secondary cyclone guide vane (35) is opposite to the air outlet end direction of the primary cyclone guide vane (32).
5. A rotary sliding arc plasma enhanced combustion cyclone apparatus as claimed in claim 4, wherein the outlet of the fuel nozzle (10) is located at the inlet end of the venturi tube (34), and the inlet of the fuel nozzle (10) connecting oil pipe is installed on the combustion chamber casing of the aeroengine.
6. A rotary sliding arc plasma enhanced combustion cyclone apparatus as claimed in claim 4, wherein the fuel nozzle (10), the insulating sleeve (20) primary cyclone and the secondary cyclone are coaxially arranged.
7. A rotary sliding arc plasma enhanced combustion cyclone apparatus as claimed in claim 4, wherein the inner surface of the venturi tube (34) is an arc surface, and the arc surface forms a converging section at the air inlet end of the venturi tube (34) and an expanding section at the air outlet end of the venturi tube (34), respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210693987.4A CN115218222B (en) | 2022-06-19 | 2022-06-19 | Rotary sliding arc plasma intensified combustion cyclone device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210693987.4A CN115218222B (en) | 2022-06-19 | 2022-06-19 | Rotary sliding arc plasma intensified combustion cyclone device |
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| Publication Number | Publication Date |
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| CN115218222A CN115218222A (en) | 2022-10-21 |
| CN115218222B true CN115218222B (en) | 2023-09-19 |
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| CN202210693987.4A Active CN115218222B (en) | 2022-06-19 | 2022-06-19 | Rotary sliding arc plasma intensified combustion cyclone device |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107182249B (en) * | 2010-12-02 | 2014-02-12 | 哈尔滨东安发动机（集团）有限公司 | Twin-stage radial vortex atomising device |
| CN108180075A (en) * | 2017-12-15 | 2018-06-19 | 中国人民解放军空军工程大学 | The rotational slide arc plasma fuel oil splitting decomposition head of aeroengine combustor buring room |
| CN113864822A (en) * | 2021-10-13 | 2021-12-31 | 西北工业大学 | Machining ring type prefilming swirler |
| CN113898974A (en) * | 2021-10-19 | 2022-01-07 | 中国人民解放军空军工程大学 | Aeroengine combustion chamber sliding arc plasma on-duty flame head |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6865889B2 (en) * | 2002-02-01 | 2005-03-15 | General Electric Company | Method and apparatus to decrease combustor emissions |
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2022
- 2022-06-19 CN CN202210693987.4A patent/CN115218222B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107182249B (en) * | 2010-12-02 | 2014-02-12 | 哈尔滨东安发动机（集团）有限公司 | Twin-stage radial vortex atomising device |
| CN108180075A (en) * | 2017-12-15 | 2018-06-19 | 中国人民解放军空军工程大学 | The rotational slide arc plasma fuel oil splitting decomposition head of aeroengine combustor buring room |
| CN113864822A (en) * | 2021-10-13 | 2021-12-31 | 西北工业大学 | Machining ring type prefilming swirler |
| CN113898974A (en) * | 2021-10-19 | 2022-01-07 | 中国人民解放军空军工程大学 | Aeroengine combustion chamber sliding arc plasma on-duty flame head |
Non-Patent Citations (1)
| Title |
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| 滑动弧等离子体强化燃烧技术在航空发动机中的研究进展;于锦禄，赵兵兵等;航空发动机;第48卷(第3期);52-58 * |
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| CN115218222A (en) | 2022-10-21 |
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