CN113898974B - Aero-engine combustion chamber sliding arc plasma on-duty flame head - Google Patents
Aero-engine combustion chamber sliding arc plasma on-duty flame head Download PDFInfo
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- CN113898974B CN113898974B CN202111216787.1A CN202111216787A CN113898974B CN 113898974 B CN113898974 B CN 113898974B CN 202111216787 A CN202111216787 A CN 202111216787A CN 113898974 B CN113898974 B CN 113898974B
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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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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Abstract
A sliding arc plasma on-duty flame head of an aircraft engine combustion chamber is provided, and a fuel nozzle is positioned in a cathode sleeve. The primary cyclone is sleeved on the cathode sleeve; the anode venturi tube is sleeved on the primary swirler. A secondary swirler is arranged between the diversion sleeve and the venturi tube mounting seat. The first-stage cyclone swirl blades are uniformly distributed on the outer circumference of the inner cylinder, and the direction of the air outlet end of each first-stage cyclone swirl blade is opposite to that of the air outlet end of the second-stage cyclone swirl blade. The gas sources of the cyclones at all levels are combustion chamber inlet gas, and external air introduction is not needed; two-stage swirl blades with opposite air outlet end directions generate reverse swirl, fuel atomization is promoted, atomized and cracked fuel, air and active particles generated by plasma discharge are fully mixed, the combustion rate is improved, the outlet temperature field quality is improved, the service life of an aeroengine turbine is prolonged, and the two-stage swirl blades have the characteristics of simple structure and strong universality and can be completely matched and replaced with the original combustion chamber head of the aeroengine.
Description
Technical Field
The invention relates to a plasma combustion-supporting technology and a plasma liquid fuel cracking technology in the field of aviation power, and particularly provides a rotating sliding arc plasma on-duty flame head of an aero-engine combustion chamber.
Background
In recent years, the plasma combustion-supporting technology of the combustion chamber of the aero-engine is widely concerned at home and abroad. Plasma fuel cracking is a novel plasma combustion-supporting technology, namely plasma discharge (in the current forms of dielectric barrier discharge or sliding arc discharge and the like) is carried out in a flowing area of fuel, high-energy electrons collide with fuel molecules in the discharge process, and carbon chains of fuel macromolecules are broken into micromolecules and active particles with low carbon chains. On one hand, the uniformity of the fuel and air mixing can be improved; on the other hand, the speed of combustion reaction can be increased, and the propagation speed of flame is increased. From the current research results, the advantages of implementing plasma fuel cracking combustion supporting in the combustion chamber of the aeroengine are as follows: the combustion rate and the completeness of fuel combustion are improved, the flame stability is obviously enhanced, the ignition delay time is shortened, the ignition performance of the combustion chamber is effectively improved, the uniformity of an outlet of the combustion chamber can be improved, and the emission of pollutants in tail gas is reduced.
Sliding arc discharge, one of the important forms of plasma generation, has unique and significant advantages in enhancing combustion reactions. The sliding arc plasma on-duty flame head is applied to the field of combustion of aero-engines not only because the electrode is simple in structure and wide in adaptation to environmental conditions, but also can effectively improve the fuel combustion quality in a combustion chamber due to the cracking effect, the chemical effect, the temperature rise effect and the pneumatic effect in the discharging process.
Because the plasma ignition combustion-supporting has huge advantages and prospects, research work in relevant aspects has been carried out at home and abroad, and certain similar devices exist in the invention and comprise the following devices:
2016 Chengdu Brad science and technology Limited discloses a plasma generator (as shown in figure 1) based on the sliding arc discharge principle in the invention creation with the publication number CN105430863, which is used for preparing Babbitt alloy, enamel, ceramic and amorphous alloy materials on the surface of materials; the 2016 Gannan institute of academic and academic department of sciences and university of Jiangnan in the invention and creation of the publication No. CN106028616A discloses a patent of a sliding arc discharge plasma jet generation device and a method (as shown in figure 2), and the device is used for water body disinfection and sterilization and inactivation treatment of microorganisms. The two devices have simple structures and certain application value. But due to their large size and limited formation of active species during ionization, are not suitable for direct use in aircraft engine combustion chambers with harsh operating environments.
The invention creation with publication number CN101463763A of the university of harbourne engineering in 2009 discloses a magnetically stable plasma jet ignition generator (as shown in fig. 3), which is used for plasma ignition of combustion chambers of ground gas turbines and marine gas turbines; the national people liberation military air force engineering university in 2017 discloses a combustion-supporting exciter of rotating sliding arc plasma of an aircraft engine combustion chamber in the invention creation of a publication number CN107420199A (as shown in figure 4), the two devices both adopt a jet ignition method, and the principle in the combustion-supporting aspect is to spray pre-generated active particles into the combustion chamber, and because the active particles exist for a short time, the jet ignition can reduce the utilization rate of the plasma and greatly reduce the combustion-supporting effect.
The national people's liberation military air force engineering university in 2018 discloses a rotary sliding arc plasma fuel oil cracking head of an aircraft engine combustion chamber in the invention creation of a publication number CN108180075A (as shown in figure 5), and the device can completely match and replace the head of the original combustion chamber without changing the structural characteristics of the original combustion chamber. However, the discharge area of the device is greatly influenced by the flow field, the device is weak in adapting to different incoming flows, and only under the condition of a large fuel oil atomization cone angle, certain fuel oil can pass through the device, so that the fuel oil cracking effect is not ideal.
The plasma ignition or combustion-supporting device provided by the invention has the advantages of less active particles generated during working, low utilization rate, weak capability of adapting to different incoming flows, incapability of cracking fuel or unsatisfactory cracking effect, and incapability of adapting to the high requirements of widening ignition boundary and stabilizing combustion range of the combustion chamber of a new generation of aeroengine.
It should be noted that the distinction between plasma ignition and plasma combustion-supporting devices has been achieved in the academic field both at home and abroad many years ago, and the difference of the application backgrounds of the two plasma technologies is also clarified in the academic publication (from aeronautical dynamics journal, volume 31, stage 7, and so on, and the subject is the current research progress of plasma intensified combustion) published in 2016 month 7 at home. Namely, the plasma ignition is that the working medium is rapidly heated by Joule heat generated by plasma discharge to form high-temperature jet flow of 3000-5000K, the temperature of combustible mixed gas in the area around the jet flow is rapidly increased in the ignition moment to form an activation center in a larger area, and the ignition process is accelerated; the plasma combustion supporting is to accelerate the rate of combustion chemical reaction by using active particles generated by non-equilibrium plasma discharge, so that the combustion performance of the fuel is improved. In summary, the plasma igniter and the plasma combustion-supporting exciter are two different combustion chamber devices, and the application backgrounds and the working principles of the two devices are different, which also causes the difference between the two devices in external shapes and structural features.
Disclosure of Invention
In order to overcome the defects that a discharge area is greatly influenced by a flow field, the device is suitable for different incoming flow conditions and has the advantages of being weak, few in active particle generation, unsatisfactory in fuel oil cracking effect and the like in the prior art, the invention provides a sliding arc plasma on-duty flame head of an aircraft engine combustion chamber.
The invention comprises a fuel nozzle, a cathode sleeve, a primary swirler, a venturi mounting seat, an anode venturi, a secondary swirler and a flow guide sleeve. The fuel nozzle is positioned in the cathode sleeve, and a fuel nozzle protection distance d is kept between the end face of the outlet end of the fuel nozzle and the end face of the discharge end of the cathode sleeve; the protection distance d =1 mm-3 mm of the fuel nozzle. The primary cyclone is sleeved on the conical surface of the cathode sleeve; the venturi installation seat is sleeved on the outer circumference of the primary cyclone. The anode venturi is located within the venturi mount. The flow guide sleeve is positioned at the outlet end of the anode venturi, a secondary cyclone is arranged between the inner end surface of the flow guide sleeve and the outer end surface of the venturi mounting seat, and two end surfaces of the secondary cyclone are respectively and tightly attached to the inner end surface of the flow guide sleeve and the outer end surface of the venturi mounting seat.
The inner surface of the cathode sleeve is in close fit with the outer surface of the fuel nozzle. The outer circumferential surface of the cathode sleeve consists of a straight section and a conical section, and the conical degree of the conical section is equal to that of the straight sectionThe conicity of the inner conical surface of the primary cyclone is the same, and the inner matching surface of the primary cyclone is formed by the surface of the conical section. The discharge end face of the cathode sleeve is arc-shaped, and the radius of the arc is R 1 ；R 1 Is 1.5 mm-4 mm.
The first-stage swirler comprises an inner barrel and swirl vanes. Wherein, the diameter of the air inlet end of the inner cylinder is larger than that of the air outlet end, and a taper alpha is formed 1 Is a cone with the angle of 6-20 degrees. 14-24 swirl blades are uniformly distributed on the outer circumferential surface of the inner cylinder, and a swirl angle alpha is formed between the air inlet end and the air outlet end of each swirl blade 2 ，α 2 Is 30-60 °
The inner surface of the air inlet end of the venturi tube mounting seat is matched with the outer surface of the primary cyclone; the inner surface of the outlet end of the venturi installation seat is a matching surface of the anode venturi. The end face of the outlet end of the venturi tube mounting seat is provided with a second-stage swirler mounting plate which protrudes radially, and the outer edge of the second-stage swirler mounting plate is provided with a second-stage swirler clamping groove.
The air inlet end of the anode venturi is a connecting section, and the outer diameter of the connecting section is the same as the inner diameter of the equal-diameter section of the venturi mounting seat; the outer circumferential surface of the air outlet end of the anode Venturi tube is a cylindrical surface, the cylindrical surface and the connecting section are in transition through a conical surface, and the cylindrical surface and the conical surface jointly form a secondary rotational flow guide surface of the anode Venturi tube. The inner surface of the anode venturi is provided with a radius R 2 And the arc surface is 25-35 mm in length, and a convergence section is formed at the air inlet end of the anode venturi tube and an expansion section is formed at the air outlet end of the anode venturi tube respectively from the two ends of the arc surface.
In the invention, the gas sources of the first-stage cyclone and the second-stage cyclone for generating the rotational flow are combustion chamber inlet gas, and external air entraining is not needed. And the swirl blades of the primary swirler and the secondary swirler are designed in directions and angles to generate swirl in opposite directions, so that fuel atomization can be promoted, atomized and cracked fuel, air and active particles generated by plasma discharge can be fully mixed, the combustion rate can be increased, the outlet temperature field quality can be improved, and the service life of parts such as an aircraft engine turbine is prolonged.
The invention has the advantages of good discharge stability, good arc motion stability, low requirement on discharge power supply parameters and wide application range due to the fact that the sliding arc discharge is only driven by the first-stage strong rotational flow. FIG. 13 shows the A-G mode occupancy (A-G for steady arc sliding mode and B-G for concomitant breakdown sliding mode) for different air flow and input voltage conditions, and experimental data shows that the A-G discharge mode occupancy increases from 85.6% to 100% during an increase in input voltage from 140V to 240V at an air flow of 250L/min; the A-G mode duty ratio decreases from 100% to 62.1% during the air flow rate increase from 250L/min to 500L/min at an input voltage of 240V. The result shows that the proportion of the stable arc sliding mode (A-G) is larger in the wider current and voltage range when the arc discharge lamp works, and the better discharge stability is kept. FIG. 14 shows the average breakdown voltage for different air flow rates and input voltages, and experimental data show that the breakdown voltage decreases from 4.6kV to 4.15kV during the increase of the air flow rate at 250L/min and the input voltage from 140V to 240V, because the A-G mode ratio is always over 85.6% under this condition. The result shows that the invention has lower requirements on the parameters of the discharge power supply. FIG. 15 shows the average power at various air flow rates and input voltages, and experimental data show that at 240V input voltage, the discharge power increases from 117.7W to 125.7W before B-G mode occurs and decreases to 123.5W after B-G mode occurs when the air flow rate increases from 250L/min to 500L/min. The result shows that the breakdown voltage and the power of the invention are less influenced by the air flow, namely the invention has strong capability of being influenced by different incoming flow conditions.
The plasma discharge part of the invention is closer to the fuel nozzle, and the first-stage strong rotational flow makes the electric arc rotate and move and simultaneously elongates the electric arc to the central area of fuel atomization, as the figure 16 (a) is the discharge diagram of the invention, and compared with the existing device discharging as the figure 16 (b), the discharge electric arc of the invention is densely distributed at the center of the fuel nozzle, which can effectively improve the probability of the fuel passing through the over-discharge area, thereby improving the efficiency of plasma discharge cracking fuel, and finally achieving the effects of improving the combustion rate and the combustion completeness and reducing the emission of pollutants in the tail gas.
The invention directly carries out plasma discharge in the combustion chamber to generate a large amount of active particles, and the discharge part is on the necessary path of fuel oil, thereby effectively improving the reaction of the active particles and the fuel oil, enhancing the combustion stability, widening the stable combustion range of the combustion chamber, improving the combustion efficiency of the combustion chamber of the aeroengine and improving the outlet uniformity of the combustion chamber.
The discharge part (the anode venturi tube) is simple and convenient to disassemble and process, and is convenient to replace in time after the discharge part is corroded and damaged without replacing the whole head.
The invention has simple structure and strong universality, can completely match and replace the head part of the original combustion chamber of the aero-engine, and does not change the structural characteristics of the original combustion chamber.
Drawings
FIG. 1 is a plasma generator based on the sliding arc discharge principle developed by Chengdu Brad technologies, inc.;
FIG. 2 is a sliding arc discharge plasma jet generator developed by the university institute of Gannan province;
FIG. 3 is a magnetically stable plasma ignition generator developed at Harbin engineering university;
FIG. 4 is a rotary sliding arc plasma combustion-supporting exciter of an aircraft engine combustion chamber developed by the university of air force engineering;
FIG. 5 is a rotary sliding arc plasma fuel cracking head for an aircraft engine combustion chamber developed by the university of air force engineering;
FIG. 6 is a schematic structural view of the present invention;
FIG. 7 is a schematic view of a fuel nozzle and anode sleeve configuration;
FIG. 8 is a schematic view of the construction of a primary cyclone; wherein FIG. 8a is a partial cross-sectional view of a primary cyclone, FIG. 8b is a left side view of FIG. 8a, and FIG. 8c is a cross-sectional view of FIG. 8 a;
FIG. 9 is a schematic view of the venturi mount and the anode venturi;
FIG. 10 is a schematic structural view of a secondary cyclone;
FIG. 11 is a schematic view of a flow sleeve configuration;
FIG. 12 is a schematic structural view of a cable;
FIG. 13 is the A-G mode ratio for different air flow and input voltage conditions;
FIG. 14 is the average breakdown voltage for different air flow and input voltage conditions;
FIG. 15 is the average power at different air flow and input voltage conditions;
FIG. 16 is a graph comparing an inventive discharge and a prior art discharge; wherein, fig. 16a is a discharge diagram of the present invention, and fig. 16b is a discharge diagram of the prior art.
In the figure: 1. a fuel nozzle; 2. a cathode sleeve; 3. a primary swirler; 4. a venturi mounting base; 5. an anode venturi; 6. a secondary cyclone; 7. a flow sleeve; 8. a cable; 9. the A-G mode ratio is obtained when the air flow is 200L/min; 10. the A-G mode ratio is determined when the air flow is 250L/min; 11. the A-G mode ratio is obtained when the air flow is 300L/min; 12. the A-G mode ratio is determined when the air flow is 350L/min; 13. the A-G mode ratio is when the air flow is 400L/min; 14. the A-G mode ratio is when the air flow is 450L/min; 15. the A-G mode ratio is set when the air flow is 500L/min; 16. the average breakdown voltage when the input voltage is 140V; 17. the average breakdown voltage when the input voltage is 160V; 18. average breakdown voltage when the input voltage is 180V; 19. the average breakdown voltage when the input voltage is 200V; 20. average breakdown voltage when the input voltage is 2200V; 21. the average breakdown voltage when the input voltage is 240V; 22. average discharge power when the input voltage is 140V; 23. average discharge power when the input voltage is 160V; 24. average discharge power when the input voltage is 180V; 25. average discharge power when the input voltage is 200V; 26. average discharge power when the input voltage is 220V; 27. average discharge power when the input voltage is 240V; 28. the inner matching surface of the primary cyclone; 29. the inner matching surface of the primary cyclone; 30. an anode venturi fitting surface; 31. a secondary cyclone clamping groove; 32. and connecting a cable with the hole.
Detailed Description
The embodiment is a flame head on duty of sliding arc plasma of an aircraft engine combustion chamber, and the flame head on duty comprises a fuel nozzle 1, a cathode sleeve 2, a primary swirler 3, a venturi mounting seat 4, an anode venturi 5, a secondary swirler 6, a flow guide sleeve 7 and a cable 8. The fuel nozzle 1 is positioned in the cathode sleeve, and a distance d is kept between the end face of the outlet end of the fuel nozzle and the end face of the discharge end of the cathode sleeve, so that a protection distance for the fuel nozzle is formed; d =1mm to 3mm. The inlet end of the fuel nozzle is connected to the fuel reservoir. The primary cyclone is sleeved on the conical surface of the cathode sleeve; the venturi installation seat 4 is sleeved on the outer circumference of the outer cylinder of the primary cyclone. The anode venturi is located within the venturi mount. The guide sleeve 7 is positioned at the outlet end of the anode venturi, a secondary cyclone 6 is arranged between the inner end surface of the guide sleeve and the outer end surface of the venturi mounting seat, and two end surfaces of the secondary cyclone are respectively and tightly attached to the inner end surface of the guide sleeve and the outer end surface of the venturi mounting seat. A radial through cable hole is formed in the circumference of the venturi tube mounting seat 4 and used for mounting a cable 8; one end of the cable passes through the venturi installation seat 4 and is communicated with an anode venturi 5.
The fuel nozzle 1, the cathode sleeve 2, the primary cyclone 3, the venturi mounting seat 4, the anode venturi 5, the secondary cyclone 6 and the flow guide sleeve 7 are all coaxial.
The cathode sleeve 2 is made of high-temperature alloy materials, the inner diameter of the cathode sleeve is the same as the outer diameter of the fuel nozzle 1, and the cathode sleeve and the fuel nozzle are in close fit. The outer circumferential surface of the cathode sleeve consists of a straight section and a conical section, the taper of the conical section is the same as that of the inner conical surface of the primary cyclone 3, and the surface of the conical section forms a primary cyclone inner matching surface 28. The end surface of the discharge end of the cathode sleeve is arc-shaped, and the radius of the arc is R 1 ，R 1 Is 1.5 mm-4 mm.
The fuel nozzle 1 is of the prior art.
The primary swirler 3 is an axial-flow swirler and is annular and made of ceramic materials. The primary cyclone comprises an inner cylinder, an outer cylinder and cyclone blades, wherein the inner cylinder is positioned in the outer cylinder, and the cyclone blades are positioned between the inner cylinder and the outer cylinder and are arranged on the outer circumferential surface of the inner cylinder. The diameter of the air inlet end of the inner cylinder is larger than that of the air outlet endForming a cone with a taper alpha 1 Is 6 to 20 degrees. The number of the swirl blades is 14-24, and the direction of the air outlet end of each swirl blade is opposite to that of the air outlet end of the secondary cyclone; in this embodiment, the air outlet end of the first-stage cyclone swirl blade deflects counterclockwise, and the air outlet end of the second-stage cyclone swirl blade deflects clockwise. A rotational flow angle alpha is formed between the air inlet end and the air outlet end of each rotational flow blade 2 ，α 2 Is 30-60 degrees. The swirl vanes adopt the prior art and are parallelogram plates.
The venturi mounting seat 4 is processed by ceramics. The venturi tube mounting seat is a hollow revolving body, the inner surface of the air inlet end of the venturi tube mounting seat is a conical surface, and the conical surface is an outer matching surface 29 of the primary cyclone; the inner surface of the venturi mount outlet end is the anode venturi mating surface 30.
The outer circumferential surface of the venturi tube mounting seat is a stepped surface, and plays a pneumatic role; the end face of the outlet end of the venturi tube mounting seat is provided with a second-stage swirler mounting plate which protrudes radially, and the outer edge of the second-stage swirler mounting plate is provided with a second-stage swirler clamping groove 31. A radial through hole is formed in the outer circumferential surface of the venturi mounting seat, and the through hole is a cable connecting hole 32.
The anode venturi 5 is a hollow rotary body. The air inlet end of the anode venturi is a connecting section, and the outer diameter of the connecting section is the same as the inner diameter of the equal-diameter section of the venturi mounting seat; the outer circumferential surface of the air outlet end of the anode venturi tube is a cylindrical surface, the cylindrical surface and the connecting section are transited through a conical surface, and the cylindrical surface and the conical surface jointly form a secondary rotational flow diversion surface of the anode venturi tube 5; the second-stage rotational flow guide surface is the same as the prior art. The inner surface of the anode venturi 5 is a convex cambered surface, a convergent section is formed at the air inlet end of the anode venturi, and an expansion section is formed at the air outlet end of the anode venturi; radius R of the convex arc surface 2 Is 25 mm-35 mm.
The secondary swirler 6 and the flow sleeve 7 are prior art. The secondary cyclone adopts a centrifugal type, and the air outlet end of the cyclone blade deflects clockwise; one end surface of the secondary cyclone is a connecting surface connected with the secondary cyclone mounting plate on the venturi mounting seat, and the other end surface of the secondary cyclone is a connecting surface connected with the secondary cyclone mounting plate on the flow guide sleeve. The secondary cyclone is arranged in a secondary cyclone clamping groove 31 of a secondary cyclone mounting plate on the guide sleeve, and the secondary cyclone mounting plate on the guide sleeve 7 is positioned on the end surface of the air inlet end of the guide sleeve.
The technical scheme of the invention is specifically illustrated by three embodiments. The structure of each embodiment is the same, and the difference lies in the technical parameters. See table 1 for details.
TABLE 1
Claims (8)
1. A flame head on duty of sliding arc plasma of a combustion chamber of an aircraft engine is characterized by comprising a fuel nozzle, a cathode sleeve, a primary swirler, a venturi mounting seat, an anode venturi, a secondary swirler and a flow guide sleeve; the fuel nozzle is positioned in the cathode sleeve, and a fuel nozzle protection distance d is kept between the end face of the outlet end of the fuel nozzle and the end face of the discharge end of the cathode sleeve; the primary cyclone is sleeved on the conical surface of the cathode sleeve; the venturi tube mounting seat is sleeved on the outer circumference of the outer cylinder of the primary cyclone; the anode venturi is positioned in the venturi mounting seat; the guide sleeve is positioned at the outlet end of the anode venturi, a secondary cyclone is arranged between the inner end surface of the guide sleeve and the outer end surface of the venturi mounting seat, and two end surfaces of the secondary cyclone are respectively and tightly attached to the inner end surface of the guide sleeve and the outer end surface of the venturi mounting seat; and a plurality of cyclone blades are uniformly distributed and installed on the outer circumferential surface of the inner cylinder of the primary cyclone, and the direction of the air outlet end of each cyclone blade of the primary cyclone is opposite to that of the air outlet end of each cyclone blade of the secondary cyclone.
2. The aircraft engine combustion chamber sliding arc plasma on-duty flame head as in claim 1, wherein said fuel nozzle protection distance d =1 mm-3 mm.
3. The aircraft engine combustor sliding arc plasma on-duty flame head as in claim 1, wherein an inner surface of said cathode sleeve mates with an outer surface of a fuel nozzle; the outer circumferential surface of the cathode sleeve consists of a straight cylinder section and a conical section, the taper of the conical section is the same as that of the inner conical surface of the primary cyclone, and the surface of the conical section forms the inner matching surface of the primary cyclone.
4. The aircraft engine combustor sliding arc plasma on-duty flame head as claimed in claim 3, wherein said cathode sleeve discharge end face is circular arc shaped with radius R 1 ；R 1 Is 1.5 mm-4 mm.
5. The aircraft engine combustor sliding arc plasma on-duty flame head as in claim 1, wherein said primary swirler comprises an inner barrel, an outer barrel and swirl vanes, wherein said inner barrel is located within said outer barrel and said swirl vanes are located between said inner and outer barrels; the diameter of the air inlet end of the inner cylinder is larger than that of the air outlet end of the inner cylinder, and a taper angle alpha is formed 1 A cone with an angle of 6-20 degrees; the number of the swirl blades is 14-24; a rotational flow angle alpha is formed between the air inlet end and the air outlet end of each rotational flow blade 2 ，α 2 Is 30-60 degrees.
6. An aircraft engine combustion chamber sliding arc plasma on-duty flame head as defined in claim 1, wherein the inner surface of the inlet end of said venturi mount engages the outer surface of the primary swirler; the inner surface of the outlet end of the venturi installation seat is a matching surface of the anode venturi.
7. An aircraft engine combustor sliding arc plasma on-duty flame head as defined in claim 1, wherein the end face of the venturi mount outlet end has a radially projecting secondary swirler mounting plate with a secondary swirler catch at the outer edge.
8. The aircraft engine combustor sliding arc plasma on-duty flame head as defined in claim 1, wherein the air inlet end of said anode venturi is a connecting section having an outer diameter equal to an inner diameter of an equal diameter section of said venturi mount; the outer circumferential surface of the air outlet end of the anode Venturi tube is a cylindrical surface, the cylindrical surface and the connecting section are in transition through a conical surface, and a secondary rotational flow guide surface of the anode Venturi tube is formed by the cylindrical surface and the conical surface; the inner surface of the anode venturi is provided with a radius R 2 And the arc surface is 25-35 mm, and a convergent section is formed at the air inlet end of the anode Venturi tube and an expansion section is formed at the air outlet end of the anode Venturi tube respectively from two ends of the arc surface.
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| CN115218221B (en) * | 2022-06-19 | 2023-08-11 | 中国人民解放军空军工程大学 | Rotary sliding arc plasma regulation and control combustion device |
| CN115218222B (en) * | 2022-06-19 | 2023-09-19 | 中国人民解放军空军工程大学 | Rotary sliding arc plasma intensified combustion cyclone device |
| CN116557147B (en) * | 2023-07-10 | 2023-09-12 | 中国人民解放军空军工程大学 | Plasma detonation device, rotary detonation engine and detonation method |
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