CN114687864B - Precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge - Google Patents
Precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge Download PDFInfo
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- CN114687864B CN114687864B CN202210141973.1A CN202210141973A CN114687864B CN 114687864 B CN114687864 B CN 114687864B CN 202210141973 A CN202210141973 A CN 202210141973A CN 114687864 B CN114687864 B CN 114687864B
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- arc discharge
- plasma jet
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- 238000010891 electric arc Methods 0.000 title claims abstract description 34
- 238000000889 atomisation Methods 0.000 claims abstract description 84
- 239000000446 fuel Substances 0.000 claims abstract description 36
- 239000012212 insulator Substances 0.000 claims description 19
- 239000003921 oil Substances 0.000 abstract description 29
- 238000002485 combustion reaction Methods 0.000 abstract description 18
- 239000003350 kerosene Substances 0.000 abstract description 9
- 239000000295 fuel oil Substances 0.000 abstract description 8
- 239000002245 particle Substances 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 4
- 238000005507 spraying Methods 0.000 abstract description 2
- 210000002381 plasma Anatomy 0.000 description 40
- 230000000694 effects Effects 0.000 description 6
- 230000009471 action Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000010892 electric spark Methods 0.000 description 3
- 150000002500 ions Chemical class 0.000 description 3
- 238000002679 ablation Methods 0.000 description 2
- 230000004913 activation Effects 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000013543 active substance Substances 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 229920002521 macromolecule Polymers 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000010742 number 1 fuel oil Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 150000003384 small molecules Chemical class 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Classifications
-
- 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
-
- 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
-
- 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
- F02C7/22—Fuel supply systems
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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
The invention discloses a precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge, which comprises an oil delivery pipe, a primary atomizer, a secondary atomizer, a cathode and an anode, wherein a primary atomization cavity is arranged in the primary atomizer; a secondary atomization cavity is arranged in the secondary atomizer, the other end of the primary atomization cavity is communicated with one end of the secondary atomization cavity and is used for spraying fuel oil in the primary atomization cavity into the secondary atomization cavity, and an atomization hole used for communicating the outer side of the secondary atomizer with the secondary atomization cavity is formed in the side wall of the secondary atomizer; the cathode is provided with a mixed fuel channel, and the anode is arranged on the outer side of the cathode. The invention atomizes kerosene for many times through the primary atomizer and the secondary atomizer, which is beneficial to reducing the particle size of atomized fuel oil and can effectively improve the combustion efficiency and the ignition performance.
Description
Technical Field
The invention relates to the field of ignition of aero-engine combustion chambers, in particular to a precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge.
Background
With the continuous improvement of the flight performance of an aircraft, higher requirements are put forward on the working performance of an aircraft engine, and an efficient ignition mode and a wider ignition boundary become important design indexes of the aircraft.
Spark ignition is currently the common engine combustion chamber ignition method, but this ignition method has a number of disadvantages. The electric spark ignition energy is small, the mixed gas cannot be successfully ignited under many conditions, the ignition efficiency is low, in addition, the residence time of fuel in the ramjet engine is short, and the electric spark igniter is difficult to realize stable ignition. And the engine is easy to be in a flameout state under severe working conditions such as high altitude, high speed and the like, and the ignition mode is difficult to perform secondary ignition at high altitude. Therefore, the ignition boundary of the traditional ignition mode is far smaller than the flight envelope of the aircraft, so that a novel igniter is needed, and the air ignition boundary is effectively widened.
The plasma is also called plasma, and is ions, ion groups, active substances and the like which are generated by partial atoms, molecules, molecular groups and the like which are deprived of electrons or ionized, and the plasma presents excitation instability and has obvious high-energy characteristics and is in a low-entropy state. The current plasma generation technology mainly comprises sliding arc discharge, dielectric barrier discharge, microwave discharge, nanosecond pulse discharge, plasma jet and the like, wherein the sliding arc discharge generation device has a simple structure, small electrode ablation, and can generate a large amount of active particles, and has partial advantages of balanced plasma and unbalanced plasma. In recent years, plasma enhanced combustion becomes a hot spot in the combustion field, and the plasma can reduce the activation energy of chemical reactions in the combustion chamber through the thermal effect, the transport effect and the kinetic effect. The research on the non-equilibrium state plasma can also break the chemical bond of the fuel molecules by releasing electrons, ions and active groups, so that the fuel macromolecules are cracked into small molecules, the chemical reaction path of the fuel is changed, and the like, to realize the combustion supporting of the fuel. In the field of plasma enhanced combustion, the plasma jet ignition has the advantages of high ignition temperature, large range, short delay time and good effect, and is an important way for improving the high-altitude secondary ignition capability of an engine and widening the air ignition boundary.
In the invention patent of CN104454290A, the Chinese people's air force engineering university discloses an elongated arc plasma jet igniter, but the invention does not introduce a fuel channel and implement precombustion, and has the defects of high electric power and insufficient jet stiffness. In the invention patent of CN109057972A, a precombustion type aeroengine plasma igniter is disclosed in the university of air force engineering of the liberation army of Chinese people. In the patent of CN107842427B, a precombustion type plasma igniter and ignition method are disclosed in the university of western security traffic, but the above-mentioned invention does not adopt plasma jet ignition, and the fuel oil is not fully mixed with air, so that the atomization effect is poor.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, and provides a precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge, which atomizes kerosene for multiple times through a primary atomizer and a secondary atomizer, thereby being beneficial to reducing the particle size of atomized fuel oil and effectively improving the combustion efficiency and ignition performance.
In order to achieve the above purpose, the invention adopts the following technical scheme: the precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge comprises an oil delivery pipe, a primary atomizer, a secondary atomizer, a cathode, an anode and a fuel nozzle, wherein a primary atomization cavity is arranged in the primary atomizer, the fuel nozzle is arranged in the primary atomization cavity, and an oil inlet of the fuel nozzle is communicated with the oil delivery pipe; a secondary atomization cavity is arranged in the secondary atomizer, the other end of the primary atomization cavity is communicated with one end of the secondary atomization cavity, fuel is sprayed into the secondary atomization cavity communicated with the primary atomization cavity from the primary atomization cavity through the fuel nozzle, and an atomization hole used for communicating the outer side of the secondary atomizer with the secondary atomization cavity is formed in the side wall of the secondary atomizer; the cathode is provided with a mixed fuel oil channel, and one end of the mixed fuel oil channel is communicated with the other end of the secondary atomization cavity; the anode is disposed outside the cathode.
The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge is characterized in that the diameter of the atomization holes is 1-3 mm, the center line of the atomization holes and the axial direction of the secondary atomizer form an included angle of 45-70 degrees, the center line of the atomization holes and the radial direction of the secondary atomizer form an included angle of 30-60 degrees, the number of the atomization holes is multiple, and the atomization holes are formed in the side wall of the secondary atomizer in a uniform array mode.
The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge is characterized in that the number of the atomization holes along the circumferential array of the secondary atomizer is 6-8, the number of the atomization holes along the axial array of the secondary atomizer is 3-6, and the distance between the center of the atomization hole on one side close to the upper surface of the secondary atomizer and the upper surface of the secondary atomizer is 10-15 mm.
The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge also comprises an insulator and a shell, wherein the insulator is sleeved on the outer side of the oil delivery pipe and is in threaded connection with the oil delivery pipe; one end of the shell is in threaded connection with the insulator, the primary atomizer and the secondary atomizer are both positioned in the shell, and the other end of the shell is in threaded connection with the anode.
The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge is characterized in that the shell is of a thin-wall rotary body structure with the same inner diameter, the thickness of the upper half section of the shell is larger than that of the lower half section of the shell, the length of the lower half section of the shell is 20-25 mm, an air inlet hole is formed in the upper half section of the shell and is used for being connected with an air quick plug, and the distance between the air inlet hole and the upper end face of the shell is 10-15 mm.
The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge is characterized in that the anode is of a hollow revolving body structure, external threads are arranged on the outer surface of the upper portion of the anode, internal threads are arranged on the inner wall of the lower portion of the shell, and the anode is adjustably arranged on the lower portion of the shell through the matching of the external threads arranged on the anode and the internal threads arranged on the shell.
The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge further comprises a cyclone, wherein the cyclone is arranged in the shell and is positioned on the outer side of the lower end of the secondary atomizer.
The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge is characterized in that swirl holes are formed in the cyclone, the diameter of each swirl hole is 1-3 mm, the included angle between the center line of each swirl hole and the center line of the cyclone is 30-60 degrees, and the number of the swirl holes is 10-20 and is uniformly distributed along the circumferential direction of the cyclone.
The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge is characterized in that the oil delivery pipe, the primary atomizer, the secondary atomizer, the cathode, the anode, the insulator, the shell and the cyclone are all coaxially arranged.
The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge is characterized in that the outer diameters of the oil conveying pipe, the primary atomizer, the secondary atomizer and the cathode are the same.
Compared with the prior art, the invention has the following advantages:
1. the invention atomizes kerosene for many times through the primary atomizer and the secondary atomizer, which is beneficial to reducing atomized particles of the kerosene and can effectively improve combustion efficiency and ignition performance.
2. The invention can regulate the relative position between the cathode and the anode, so the invention can control the ignition intensity and the ignition energy, the invention adopts an alternating current power supply to drive, the temperature rise of the electrode area caused by current is small, and the unbalanced plasma in the plasma generated by the breakdown of air by alternating current arc has large duty ratio.
3. The air and kerosene required for ignition in the invention can be obtained from the existing engine without providing additional devices, and has stronger practicability.
4. The flame jet channel has small diameter and strong jet rigidity, so that the generated flame is stable, is not easy to extinguish and has strong ignition capability.
5. Compared with an igniter without pre-burning, the invention has the advantages that the area of an ignition area is larger, the ignition reliability is improved, and the invention is favorable for widening the high-altitude ignition envelope.
6. The invention adopts sliding arc plasma ignition, the electric arc is not concentrated at one place, the degree of electrode ablation is reduced, and meanwhile, the cooling effect of air flow is beneficial to protecting the electrode.
7. The invention comprehensively considers various factors such as practicality, processability and the like, designs on the basis of the structure and the size of the existing combustion chamber, can be directly interchanged with the traditional electric spark igniter, and has the advantages of simple and attractive structure, strong practicability and convenient processing.
The invention is described in further detail below with reference to the drawings and examples.
Drawings
Fig. 1 is a cross-sectional view of the present invention.
Fig. 2 is a schematic perspective view of the present invention.
Fig. 3 is a perspective cross-sectional view of the secondary atomizer of the present invention.
Fig. 4 is a schematic perspective view of a cyclone of the present invention.
Fig. 5 is a view showing the operation of the electrode of the present invention.
Reference numerals illustrate:
10-an oil delivery pipe; 20-primary atomizer; 21-a primary atomizing chamber;
30-a secondary atomizer; 31-a secondary atomizing chamber; 32-atomizing holes;
40-cathode; 41-a mixed fuel passage; 50-anode;
60-insulator; 70-a housing; 71-an air inlet hole;
80-a cyclone; 81-swirl holes; 90-fuel nozzle.
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.
It should be noted that references to "one", "a plurality" and "a plurality" in this disclosure are intended to be illustrative rather than limiting, and those skilled in the art will appreciate that "one or more" is intended to be construed as "one or more" unless the context clearly indicates otherwise.
As shown in fig. 1 and 2, a precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge comprises an oil delivery pipe 10, a primary atomizer 20, a secondary atomizer 30, a cathode 40, an anode 50 and a fuel nozzle 90, wherein a primary atomization cavity 21 is arranged in the primary atomizer 20, an oil outlet of the oil delivery pipe 10 is communicated with one end of the primary atomization cavity 21, and the fuel nozzle 90 is arranged in the primary atomization cavity 21 and connected with the oil delivery pipe 10 and is used for spraying fuel oil into a secondary atomization cavity 31 communicated with the primary atomization cavity 21 through the primary atomization cavity 21; the secondary atomization cavity 31 is disposed in the secondary atomizer 30, and an atomization hole 32 for communicating the outside of the secondary atomizer 30 with the secondary atomization cavity 31 is formed in the side wall of the secondary atomizer 30; the cathode 40 is provided with a mixed fuel channel 41, and one end of the mixed fuel channel 41 is communicated with the other end of the secondary atomization cavity 31; the anode 50 is disposed outside the cathode 40.
In this embodiment, fuel is sprayed into the primary atomization cavity 21 through the oil delivery pipe 10, the primary atomization cavity 21 is subjected to primary atomization, the primary atomized fuel is sprayed into the secondary atomization cavity 31 from the primary atomization cavity 21, the primary atomized fuel in the secondary atomization cavity 31 is atomized again and mixed with air entering the secondary atomization cavity 31 from the atomization hole 32, and the primary atomizer 20 and the secondary atomizer 30 atomize the fuel for multiple times, so that the fuel atomization particles are reduced, and the combustion efficiency and the ignition performance can be effectively improved. In an aeroengine the fuel is kerosene.
As shown in fig. 1 and fig. 2, the secondary atomizer 30 is of a thin-wall shell structure, an internal thread is disposed on an inner wall of an upper portion of the secondary atomizer 30, an external thread matched with the internal thread of the upper portion of the secondary atomizer 30 is disposed on an outer side of a lower portion of the primary atomizer 20, the primary atomizer 20 and the secondary atomizer 30 are fixedly connected through the mutual matching of the internal thread and the external thread, the atomization holes 32 are inclined straight through holes formed in a side wall of the secondary atomizer 30, the diameter of the atomization holes 32 is 1 mm-3 mm, an included angle of 45 degrees-70 degrees is formed between a center line of the atomization holes 32 and an axial direction of the secondary atomizer 30, an included angle of 30 degrees-60 degrees is formed between the center line of the atomization holes 32 and a radial direction of the secondary atomizer 30, the number of the atomization holes 32 is multiple, the atomization holes 32 are formed in a side wall of the secondary atomizer 30 in a uniform array mode, the number of the atomization holes 32 in a circumferential array of the secondary atomizer 30 is 6-8, the number of the atomization holes 32 in the axial direction of the secondary atomizer 30 in the array is 3-6, and the distance between the uppermost surface of the atomization holes 32 and the surface of the secondary atomizer 30 mm is 15mm.
As shown in fig. 1 and 2, the pre-burning type plasma jet igniter based on three-dimensional rotary sliding arc discharge further comprises an insulator 60 and a shell 70, wherein the insulator 60 is sleeved on the outer side of the oil delivery pipe 10 and is in threaded connection with the oil delivery pipe 10; one end of the housing 70 is screwed with the insulator 60, the primary atomizer 20 and the secondary atomizer 30 are both located in the housing 70, and the other end of the housing 70 is screwed with the anode 50.
In this embodiment, the insulator 60 is a hollow revolving body structure, and is made of an insulating material, an internal thread is machined in the hollow part of the insulator, an external thread matched with the external thread is machined on the outside of the oil delivery pipe 10, and the insulator 60 is connected with the oil delivery pipe 10 through threads; the oil inlet of the oil delivery pipe 10 is provided with threads matched with threads of the high-pressure oil pipe quick connector, the high-pressure oil pipe quick connector can be fixedly arranged at the oil inlet of the oil delivery pipe 10, the lower end face of the insulator 60 coincides with the lower end face of the oil delivery pipe 10, the lower section of the insulator 60 is provided with a small boss used for being connected with the shell 70, the outer surface of the small boss is provided with external threads matched with the internal threads on the upper part of the shell 70, and the insulator 60 is fixedly connected with the shell 70 through threads.
As shown in FIG. 1, the housing 70 is a thin-walled solid of revolution structure with consistent inner diameter, the thickness of the upper half section of the housing 70 is greater than that of the lower half section, the length of the lower half section of the housing 70 is 20 mm-25 mm, the upper half section of the housing 70 is provided with an air inlet 71 and the air inlet 71 is used for being connected with an air quick plug, and the distance between the air inlet 71 and the upper end surface of the housing 70 is 10 mm-15 mm. The diameter of the air inlet 71 is 10 mm-12 mm, and an internal thread is arranged in the air inlet 71 and is used for being matched with an external thread of the air quick plug. The upper part of the shell 70 is provided with a circular groove, the inner surface of the groove is provided with an internal thread, the external thread of the insulator 60 is connected with the internal thread, and the lower end surface of the insulator 60 is coincident with the bottom surface of the groove. A small stretching boss is provided at a lower portion of the inner surface of the housing 70 for placing the cyclone 80.
As shown in fig. 1 and 3, the anode 50 is a hollow solid of revolution structure, an external thread is provided on the outer surface of the upper portion of the anode 50, an internal thread is provided on the inner wall of the lower portion of the housing 70, and the anode 50 is adjustably mounted on the lower portion of the housing 70 by the cooperation of the external thread provided on the anode 50 and the internal thread provided on the housing 70. The anode 50 has a funnel-shaped hollow portion, an upper inner section is a combustion zone, and a lower section is a jet zone. In the embodiment, the coal oil enters the primary atomizer through the oil delivery pipe, flows into the secondary atomizer after primary atomization through the fuel nozzle, and is atomized again under the action of swirl air of the secondary atomizer, and then the oil-gas mixture enters the combustion area. When the three-dimensional rotating sliding arc and the plasma released by the puncture air of the sliding arc pass through the oil-gas mixture area, if the energy released by the plasma is higher than the activation energy of the chemical reaction of the fuel, the fuel is ignited, and the ignited flame is jetted out at the outlet.
As shown in fig. 1, the cathode 40 is a thin-walled shell, the upper section of the outer surface of the cathode is provided with external threads, the cathode 40 is fixedly connected with the secondary atomizer 30 through threads, and the lower end of the cathode 40 is provided with a rounded corner opposite to the anode 50. The minimum gap between the cathode 40 and the anode 50 is 1mm to 2mm.
As shown in fig. 1, the cyclone 80 is disposed within the housing 70 and outside the lower end of the secondary atomizer 30. The cyclone 80 is an annular cylinder, the inner surface of the cyclone 80 coincides with the outer surface of the secondary atomizer 30, the outer surface of the cyclone 80 coincides with the inner surface of the shell 70, the cyclone 80 is a hole-shaped cyclone, the cyclone 80 is provided with cyclone holes 81, the diameter of each cyclone hole 81 is 1-3 mm, the included angle between the center line of each cyclone hole 81 and the center line of the cyclone 80 is 30-60 degrees, and the number of the cyclone holes 81 is 10-20 and the cyclone holes are uniformly distributed along the circumferential direction of the cyclone 80.
As shown in fig. 1, the oil delivery pipe 10, the primary atomizer 20, the secondary atomizer 30, the cathode 40, the anode 50, the insulator 60, the housing 70, and the cyclone 80 are all coaxially arranged. The outer diameters of the oil delivery pipe 10, the primary atomizer 20, the secondary atomizer 30 and the cathode 40 are all the same.
The working principle of the invention is as follows:
the ignition process of the invention is divided into three moments and two phases, wherein the three moments are respectively air-in moment, power-on moment and fuel-in moment, the fuel-in moment can be regarded as ignition moment, and the two phases are an air swirling phase and a sliding arc breakdown air forming non-equilibrium plasma phase.
When the air is introduced, the air flows in from the symmetrical air inlet holes 71 on two sides of the shell 70 and enters the air flow channel, and the gap of the air flow channel is 3-5 mm. When flowing through the secondary atomization section, a part of air enters the atomized fuel oil channel through the atomization holes 32 on the channel wall of the secondary atomization section, and the axially flowing air flow is changed into the axially flowing and anticlockwise rotating air flow under the action of the atomization holes 32; another portion of the air passing through the cyclone 81 is also changed to an axially flowing and clockwise rotating flow.
When the power supply is switched on the basis of air ventilation, the cathode and the anode break down air at the minimum gap to generate an electric arc, and the electric arc continuously slides, stretches and rotates under the action of rotational flow air of the airflow channel to form a sliding arc, namely the electric arc continuously rotates outwards to stretch until the energy of the power supply is insufficient and the electric arc breaks.
On the basis of switching on air and power, when the oil way is switched on, kerosene enters the primary atomization section from the outer interface section, is atomized by the fuel nozzle, and then enters the secondary atomization section, under the action of swirling air, the kerosene is atomized again after being fully mixed with the air, and when the oil-gas mixture in the swirling state flows out of the annular cathode, the oil-gas mixture is mixed with the air in different swirling directions again, so that the atomization degree of the kerosene is higher, and enters a combustion area, in the combustion area, sliding arcs break down the air to generate unbalanced plasmas, and under the action of air flow and voltage, the plasma jet ignites the fuel in the combustion area. Finally, the plasma jet and the flame jet are jointly ejected from the anode outlet and ignite the main stream fuel in the combustion chamber.
The foregoing description is only a preferred embodiment of the invention, and is not intended to limit the invention in any way, and any simple modification, variation and equivalent structural transformation made to the above embodiment according to the technical matter of the invention still fall within the scope of the technical scheme of the invention.
Claims (9)
1. A precombustion type plasma jet igniter based on three-dimensional rotating sliding arc discharge, comprising:
an oil delivery pipe (10);
the oil delivery device comprises a primary atomizer (20), wherein a primary atomization cavity (21) is arranged in the primary atomizer (20), and an oil outlet of the oil delivery pipe (10) is communicated with one end of the primary atomization cavity (21);
the fuel nozzle (90) is arranged in the primary atomization cavity (21), and an oil inlet of the fuel nozzle (90) is communicated with the oil delivery pipe (10);
the secondary atomizer (30), a secondary atomization cavity (31) is arranged in the secondary atomizer (30), the other end of the primary atomization cavity (21) is communicated with one end of the secondary atomization cavity (31), fuel is sprayed into the secondary atomization cavity (31) communicated with the primary atomization cavity (21) from the primary atomization cavity (21) through the fuel nozzle (90), and an atomization hole (32) used for communicating the outer side of the secondary atomizer (30) with the secondary atomization cavity (31) is formed in the side wall of the secondary atomizer (30);
the cathode (40) is provided with a mixed fuel channel (41), and one end of the mixed fuel channel (41) is communicated with the other end of the secondary atomization cavity (31);
an anode (50), the anode (50) being disposed outside the cathode (40);
the precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge further comprises:
the insulator (60) is sleeved on the outer side of the oil delivery pipe (10) and is in threaded connection with the oil delivery pipe (10);
the primary atomizer (20) and the secondary atomizer (30) are both positioned in the shell (70), and the other end of the shell (70) is in threaded connection with the anode (50);
an air inlet hole (71) is formed in the upper half section of the shell (70), and the air inlet hole (71) is used for being connected with an air quick plug.
2. The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge according to claim 1, wherein the diameter of the atomization holes (32) is 1-3 mm, the center line of the atomization holes (32) forms an included angle of 45-70 degrees with the axial direction of the secondary atomizer (30), the center line of the atomization holes (32) forms an included angle of 30-60 degrees with the radial direction of the secondary atomizer (30), the number of the atomization holes (32) is multiple, and the atomization holes (32) are formed in the side wall of the secondary atomizer (30) in a uniform array mode.
3. The precombustion type plasma jet igniter based on three-dimensional rotating sliding arc discharge according to claim 2, wherein the number of the atomization holes (32) along the circumferential array of the secondary atomizer (30) is 6-8, the number of the atomization holes (32) along the axial array of the secondary atomizer (30) is 3-6, and the distance between the center of the atomization hole (32) on the side close to the upper surface of the secondary atomizer (30) and the upper surface of the secondary atomizer (30) is 10-15 mm.
4. The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge according to claim 1, wherein the outer shell (70) is of a thin-wall rotary body structure with the same inner diameter, the thickness of the upper half section of the outer shell (70) is larger than that of the lower half section, the length of the lower half section of the outer shell (70) is 20-25 mm, and the distance between the air inlet hole (71) and the upper end face of the outer shell (70) is 10-15 mm.
5. The precombustion type plasma jet igniter based on three-dimensional rotating sliding arc discharge according to claim 4, wherein the anode (50) is of a hollow revolution body structure, external threads are arranged on the outer surface of the upper portion of the anode (50), internal threads are arranged on the inner wall of the lower portion of the shell (70), and the anode (50) is adjustably mounted on the lower portion of the shell (70) through the cooperation of the external threads arranged on the anode (50) and the internal threads arranged on the shell (70).
6. The pre-ignition plasma jet igniter based on three-dimensional rotating and sliding arc discharge according to claim 5, further comprising a cyclone (80), wherein the cyclone (80) is disposed inside the housing (70) and outside the lower end of the secondary atomizer (30).
7. The precombustion type plasma jet igniter based on three-dimensional rotary sliding arc discharge according to claim 6, wherein swirl holes (81) are formed in the swirler (80), the diameter of each swirl hole (81) is 1-3 mm, the included angle between the center line of each swirl hole (81) and the center line of the swirler (80) is 30-60 degrees, and the number of the swirl holes (81) is 10-20 and is uniformly distributed along the circumference of the swirler (80).
8. A precombustion plasma jet igniter based on three dimensional rotating sliding arc discharge according to claim 7 wherein the oil delivery tube (10), primary atomizer (20), secondary atomizer (30), cathode (40), anode (50), insulator (60), housing (70) and cyclone (80) are all coaxially disposed.
9. A precombustion plasma jet igniter based on three dimensional rotating sliding arc discharge according to claim 8 wherein the outer diameters of the oil delivery tube (10), primary atomizer (20), secondary atomizer (30) and cathode (40) are all the same.
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