CN114421284A - Air-cooled multi-electrode high-energy igniter - Google Patents
Air-cooled multi-electrode high-energy igniter Download PDFInfo
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- CN114421284A CN114421284A CN202210321236.XA CN202210321236A CN114421284A CN 114421284 A CN114421284 A CN 114421284A CN 202210321236 A CN202210321236 A CN 202210321236A CN 114421284 A CN114421284 A CN 114421284A
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- 238000001816 cooling Methods 0.000 claims abstract description 51
- 238000002485 combustion reaction Methods 0.000 claims abstract description 23
- 239000012212 insulator Substances 0.000 claims description 12
- 239000004065 semiconductor Substances 0.000 description 10
- 238000010892 electric spark Methods 0.000 description 8
- 229910045601 alloy Inorganic materials 0.000 description 6
- 239000000956 alloy Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 6
- 239000010935 stainless steel Substances 0.000 description 6
- 229910001220 stainless steel Inorganic materials 0.000 description 6
- 238000002679 ablation Methods 0.000 description 5
- 238000007599 discharging Methods 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 5
- 230000035515 penetration Effects 0.000 description 5
- 230000002035 prolonged effect Effects 0.000 description 5
- 238000003466 welding Methods 0.000 description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 229910052799 carbon Inorganic materials 0.000 description 4
- 230000008021 deposition Effects 0.000 description 4
- 239000007772 electrode material Substances 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- PNEYBMLMFCGWSK-UHFFFAOYSA-N Alumina Chemical compound [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000010891 electric arc Methods 0.000 description 2
- 230000008020 evaporation Effects 0.000 description 2
- 238000001704 evaporation Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 238000010992 reflux Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 238000009421 internal insulation Methods 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000011214 refractory ceramic Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
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Classifications
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01T—SPARK GAPS; OVERVOLTAGE ARRESTERS USING SPARK GAPS; SPARKING PLUGS; CORONA DEVICES; GENERATING IONS TO BE INTRODUCED INTO NON-ENCLOSED GASES
- H01T13/00—Sparking plugs
- H01T13/20—Sparking plugs characterised by features of the electrodes or insulation
- H01T13/22—Sparking plugs characterised by features of the electrodes or insulation having two or more electrodes embedded in insulation
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01T—SPARK GAPS; OVERVOLTAGE ARRESTERS USING SPARK GAPS; SPARKING PLUGS; CORONA DEVICES; GENERATING IONS TO BE INTRODUCED INTO NON-ENCLOSED GASES
- H01T13/00—Sparking plugs
- H01T13/02—Details
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01T—SPARK GAPS; OVERVOLTAGE ARRESTERS USING SPARK GAPS; SPARKING PLUGS; CORONA DEVICES; GENERATING IONS TO BE INTRODUCED INTO NON-ENCLOSED GASES
- H01T13/00—Sparking plugs
- H01T13/02—Details
- H01T13/16—Means for dissipating heat
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01T—SPARK GAPS; OVERVOLTAGE ARRESTERS USING SPARK GAPS; SPARKING PLUGS; CORONA DEVICES; GENERATING IONS TO BE INTRODUCED INTO NON-ENCLOSED GASES
- H01T13/00—Sparking plugs
- H01T13/20—Sparking plugs characterised by features of the electrodes or insulation
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- Spark Plugs (AREA)
Abstract
The invention belongs to the technical field of aero-engine combustion chambers, and discloses an air-cooled multi-electrode high-energy igniter. The igniter comprises a multi-electrode electric nozzle, a cooling hole, a cooling airflow channel, a circulating hole, an external shell and a mounting seat; the multi-electrode electric nozzle is overlapped with the axis of the outer shell, and is nested in the outer shell; the top end plane of the multi-electrode electric nozzle is inwards sunken to form a discharge concave cavity with the outer shell; cooling holes which are uniformly distributed along the circumferential direction are arranged on the top end plane of the outer shell close to the edge; the side wall of the outer shell is provided with a circulation hole, the inner wall of the outer shell is provided with a circular seam type cooling airflow channel, the cooling airflow channel is connected with the cooling hole and the circulation hole, and the rear end of the outer shell is provided with a mounting seat. The igniter can effectively solve the problems of poor ignition reliability and short service life of an aircraft engine under the high altitude extreme condition, improves the ignition reliability of an engine combustion chamber under the extreme condition and prolongs the service life.
Description
Technical Field
The invention belongs to the technical field of aero-engine combustion chambers, and particularly relates to an air-cooled multi-electrode high-energy igniter.
Background
After the aeroengine is flamed out at high altitude, parameters such as the air inlet temperature and the pressure of the combustion chamber are rapidly reduced, the viscosity of fuel oil is increased, the oxygen content is reduced, and the links such as atomization, evaporation, ignition, flame propagation and the like are all adversely affected. Secondary ignition of engine combustion chambers is subject to extreme conditions of low pressure and low temperature, requiring more reliable high performance igniters.
The igniter of the main combustion chamber of the aircraft engine generally adopts a semiconductor electric nozzle based on spark discharge, the discharge of the semiconductor electric nozzle is concentrated in an electric arc channel between a central high-voltage electrode and an outer edge low-voltage electrode, the electric spark energy is low, an ignition core area is small, and the penetration depth is insufficient. Under the conditions of high air pressure and low temperature, the quality of fuel oil atomization, evaporation and mixing is poor, even if a semiconductor electric nozzle generates fire nuclei, the ignition failure is caused because the size and penetration degree of the fire nuclei are limited and the semiconductor electric nozzle is difficult to enter a central reflux area with high oil-gas ratio.
At present, an oxygen supplement device is usually added on an engine to solve the problem of high-altitude ignition of an aeroengine, so that the structure of an ignition system is complex, and the weight of the engine is increased.
There is a need to develop a gas flow cooled multi-electrode high energy igniter.
Disclosure of Invention
The invention aims to solve the technical problem of providing an air flow cooling type multi-electrode high-energy igniter.
The air flow cooling type multi-electrode high-energy igniter can realize multi-electrode high-energy spark discharge, strong penetrating electric sparks are generated at the head of the igniter after the electric sparks are converged by the concave cavity, a large heating area is formed, and fuel oil can be prevented from attaching to the surface of an electrode to form carbon deposition; the igniter is provided with an airflow cooling channel, so that the temperature is prevented from being overhigh after the multi-electrode electric nozzle improves the discharge energy, the ablation of electrode materials and a semiconductor glaze layer is reduced, and the service life of the igniter is prolonged.
The invention relates to an air-cooled multi-electrode high-energy igniter which is characterized by comprising a multi-electrode electric nozzle, a cooling hole, a cooling air flow channel, a circulation hole, an external shell and a mounting seat;
the multi-electrode electric nozzle is overlapped with the axis of the outer shell, and is nested in the outer shell; the top end plane of the multi-electrode electric nozzle is inwards sunken to form a discharge concave cavity with the outer shell;
cooling holes which are uniformly distributed along the circumferential direction are arranged on the top end plane of the outer shell close to the edge; the side wall of the outer shell is provided with a circulation hole, the inner wall of the outer shell is provided with a circular seam type cooling airflow channel, the cooling airflow channel is connected with the cooling hole and the circulation hole, and the rear end of the outer shell is provided with a mounting seat.
Furthermore, the multi-electrode electric nozzle is formed by nesting and installing a central electrode, an inner-layer insulating part, a relay electrode and an outer-layer insulating part from inside to outside in sequence; the number of the relay electrodes is more than or equal to 1 to increase the arc length.
Furthermore, the central electrode, the inner layer insulating part, the relay electrode and the outer layer insulating part of the multi-electrode electric nozzle have the same internal expansion angle, and a discharge concave cavity with a smooth surface and a V-shaped section is formed after the multi-electrode electric nozzle is nested and installed.
Furthermore, the igniter is arranged in the combustion chamber of the aircraft engine, and the height of the circulating hole is positioned between the outer shell of the combustion chamber of the aircraft engine and the wall of the flame tube.
Furthermore, the top plane edge of the outer shell is provided with a round edge chamfer, and cooling holes which are uniformly distributed along the circumferential direction are formed in the round edge chamfer.
The igniter electric nozzle in the air-cooled multi-electrode high-energy igniter adopts a multi-electrode discharging mode, and is formed by coaxially nesting a central electrode, an inner-layer insulating part, a relay electrode and an outer-layer insulating part, when a loading voltage reaches a breakdown condition, multi-stage crossing breakdown among the central electrode, the relay electrode and an outer shell is realized, a continuous long electric arc is formed, the discharging energy is increased, and the electric spark volume is enhanced; the center electrode, the inner-layer insulating part, the relay electrode, the outer-layer insulating part and the outer shell of the multi-electrode electric nozzle are provided with the same internal expansion angle, and after the multi-electrode electric nozzle and the outer shell are coaxially nested, a smooth discharging concave cavity is formed at the head of the igniter, so that discharging energy can be gathered, the penetration degree of electric sparks is enhanced, fuel oil in a combustion chamber is prevented from being attached to the head of the electric nozzle, carbon deposition of the electric nozzle is reduced, and discharging reliability is improved; the outer shell is provided with a circulation hole, cooling airflow is driven by the difference of pressure inside and outside the flame tube of the combustion chamber and reaches the cooling hole at the head of the igniter through the cooling airflow channel, the multi-electrode electric nozzle is cooled, ablation of electrode materials and a semiconductor glaze layer is reduced, and the service life of the igniter is prolonged.
The air-cooled multi-electrode high-energy igniter has the following characteristics:
1. according to the air-cooled multi-electrode high-energy igniter, the relay electrode is additionally arranged between the central electrode and the outer shell, so that an arc channel formed by discharge is prolonged, the effective energy output of the ignition device is improved, high-energy and strong-penetration electric sparks are generated at the top of the multi-electrode electric nozzle, high-energy and large-volume initial fire nuclei are formed in a combustion chamber, and then the ignition device quickly enters the central reflux area to form stable flames.
2. The multi-electrode electric nozzle head part in the air-cooled multi-electrode high-energy igniter is of a concave cavity structure, and the central electrode, the inner-layer insulating part, the relay electrode, the outer-layer insulating part and the outer shell are gradually contracted from inside to outside to form a concave cavity with a V-shaped section. On one hand, the concave cavity can collect high-energy electric arcs, the penetration degree of electric sparks is enhanced, and the ignition reliability is improved; on the other hand, the concave cavity can effectively reduce fuel adhesion, reduce carbon deposition at the head of the multi-electrode electric nozzle and prolong the service life of the igniter.
3. The outer shell of the air-cooled multi-electrode high-energy igniter is provided with the circulation hole, the circulation hole is positioned between the outer shell of the combustion chamber and the wall of the flame tube after the igniter is installed, cold air flow enters the cooling air flow channel from the circulation hole under the driving of differential pressure to cool the end surface of the multi-electrode electric nozzle, the ablation of electrode materials and a semiconductor glaze layer is reduced, the service life of the igniter is prolonged, and the reliability of the igniter is improved.
The air-cooled multi-electrode high-energy igniter can effectively solve the problems of poor ignition reliability and short service life of an aircraft engine under extreme high altitude conditions. Multi-electrode high-energy discharge is realized, electric sparks which are strongly penetrated are generated at the head of the igniter after being gathered by the concave cavity, the size and the penetration degree of a fire core are increased, a larger heating area is formed, and fuel oil can be prevented from being attached to the surface of an electrode to form carbon deposition; the ablation is reduced through a cooling technology, an airflow cooling channel is arranged in the igniter, the phenomenon that the temperature is too high in the use process of the electric nozzle is avoided, the ablation of electrode materials and a semiconductor glaze layer is slowed down, the service life of the igniter is prolonged, and the ignition reliability of an engine combustion chamber under extreme conditions is improved.
Drawings
FIG. 1 is a schematic diagram of the structure of an air-cooled multi-electrode high energy igniter of the invention;
FIG. 2 is a schematic center sectional view of an air-cooled multi-electrode high energy igniter of the invention;
fig. 3 is a schematic front view of the air-cooled multi-electrode high-energy igniter of the invention.
In the figure, 1, a multi-electrode electric nozzle; 2. a cooling hole; 3. a cooling gas flow channel; 4. a flow-through hole; 5. an outer housing; 6. a mounting seat;
101. a center electrode; 102. an inner layer insulator; 103. a relay electrode; 104. an outer insulation member.
Detailed Description
The invention is explained in detail below with reference to the figures and examples.
The air-cooled multi-electrode high-energy igniter comprises a multi-electrode electric nozzle 1, a cooling hole 2, a cooling air flow channel 3, a circulation hole 4, an external shell 5 and a mounting seat 6;
the multi-electrode electric nozzle 1 is overlapped with the axis of the outer shell 5, and the multi-electrode electric nozzle 1 is nested in the outer shell 5; the top end plane of the multi-electrode electric nozzle 1 is inwards sunken to form a discharge concave cavity with the outer shell 5;
Further, the multi-electrode electric nozzle 1 is formed by nesting and mounting a central electrode 101, an inner-layer insulating part 102, a relay electrode 103 and an outer-layer insulating part 104 from inside to outside in sequence; the number of relay electrodes 103 is 1 or more to increase the arc length.
Further, the center electrode 101, the inner layer insulator 102, the relay electrode 103 and the outer layer insulator 104 of the multi-electrode electric nozzle 1 have the same internal divergence angle, and form a discharge cavity with a smooth surface and a V-shaped cross section after being nested and installed.
Furthermore, the igniter is arranged in the combustion chamber of the aircraft engine, and the height of the circulating hole 4 is positioned between the outer shell of the combustion chamber of the aircraft engine and the wall of the flame tube.
Furthermore, the top plane edge of the outer shell 5 is provided with a round edge chamfer, and cooling holes 2 which are uniformly distributed along the circumferential direction are formed in the round edge chamfer.
Example 1
With reference to fig. 1 to 3, the air-cooled multi-electrode high-energy igniter of the present embodiment includes a multi-electrode electric nozzle 1 of the igniter, a cooling hole 2, a cooling air flow channel 3, a circulation hole 4, an external housing 5, and a mounting seat 6. The multi-electrode electric nozzle comprises a multi-electrode electric nozzle 1, an external shell 5, a cooling hole 2, a circulating hole 4, a cooling air channel 3 and a mounting seat 6, wherein the axes of the multi-electrode electric nozzle 1 and the external shell 5 are overlapped, the multi-electrode electric nozzle 1 is nested in the external shell 5, the outer edge of a cavity at the head of the multi-electrode electric nozzle 1 is overlapped with the inner edge of an expansion angle in the external shell 5, the front surface and the round edge chamfer angle at the top end of the external shell 5 are provided with the cooling hole 2, one side of the external shell 5, which is close to the top end, is provided with the circulating hole 4, the cooling hole 2 and the circulating hole 4 are connected through the cooling air channel 3 to form an air flow channel, and the bottom of the external shell 5 is connected with the mounting seat 6 and used for mounting and fixing an igniter.
As shown in fig. 2, the multi-electrode electric nozzle 1 is of a nested structure and comprises a central electrode 101, an inner layer insulator 102, a relay electrode 103 and an outer layer insulator 104. The number of the relay electrodes 103 of the present invention may be plural, and may be adjusted according to the size of the igniter. In the present embodiment, the number of relay electrodes 103 is 1.
The central electrode 101 is made of 310S stainless steel or high-temperature-resistant alloy, preferably nickel-based high-temperature alloy. The central electrode 101 is a cylindrical structure with a diameter of 1-4 mm, preferably 2 mm. The outer circular surface of the central electrode 101 coincides with the inner circular surface of the internal insulating member 102, the axes of the two are the same, the outer edge of the top end of the central electrode 101 coincides with the inner edge of the expansion angle inside the internal insulating member 102, and the central electrode 101 is nested in the internal insulating member 102 and connected by adopting a welding technology.
The internal insulation part 102 is of a circular tube type structure with an internal expansion opening, the expansion angle is 130-160 degrees, the preferred expansion angle is 140 degrees, the inner diameter is 1-4 mm, the preferred expansion angle is 2mm, and the outer diameter is 4-8 mm, and the preferred expansion angle is 6 mm. The inner insulator 102 is made of refractory ceramic insulating material, preferably 95 high alumina ceramic, and the exposed surface of the expansion opening is coated with semiconductor coating, preferably Cu2And an O glaze layer. The outer circular surface of the inner layer insulating part 102 is superposed with the inner circular surface of the relay electrode 103, the axes of the two are superposed, the outer edge of the internal expansion angle of the inner layer insulating part 102 is superposed with the inner edge of the internal expansion angle of the relay electrode 103, the inner layer insulating part 102 is nested in the relay electrode 103, and the two are connected by adopting a welding technology.
The relay electrode 103 is of a circular tube type structure with an internal expansion opening, the expansion angle is 130-160 degrees, the preferred expansion angle is 140 degrees, the inner diameter is 4-8 mm, the preferred expansion angle is 6mm, and the outer diameter is 8-12 mm, and the preferred expansion angle is 10 mm. The relay electrode 103 is made of 310S stainless steel or high-temperature-resistant alloy, preferably nickel-based high-temperature alloy. The outer circular surface of the relay electrode 103 is coincided with the inner circular surface of the outer insulating part 104, the axes of the relay electrode 103 and the inner circular surface are coincided, the outer edge of the internal expansion angle of the relay electrode 103 is coincided with the inner edge of the internal expansion angle of the outer insulating part 104, the relay electrode 103 is nested in the outer insulating part 104, and the relay electrode 103 and the outer insulating part are connected by adopting a welding technology.
The outer-layer insulating part 104 is of a circular tube type structure with an internal expansion opening, the expansion angle is 130-160 degrees, preferably 140 degrees, the inner diameter is 8-12 mm, preferably 10mm, the outer diameter is 12-16 mm,preferably 14 mm. The outer insulation member 104 is made of high temperature resistant ceramic insulation material, preferably 95 high alumina ceramic, and the exposed surface of the expansion opening is coated with a semiconductor coating, preferably Cu2And an O glaze layer.
The outer circular surface of the multi-electrode electric nozzle 1 is coincided with the inner circular surface of the outer shell 5, the axes of the multi-electrode electric nozzle and the inner circular surface are coincided, the outer edge of the concave cavity at the head of the multi-electrode electric nozzle 1 is coincided with the inner edge of the expansion angle in the outer shell 5, the multi-electrode electric nozzle 1 is nested in the outer shell 5, and the multi-electrode electric nozzle and the outer shell are connected through a welding technology. The inner divergence angles of the central electrode 101, the inner layer insulator 102, the relay electrode 103 and the outer layer insulator 104 of the multi-electrode electric nozzle 1 are consistent with the inner divergence angle of the outer shell 5, and after the assembly is finished, a smooth concave cavity with a V-shaped section is formed at the head of the igniter. The lengths of the multi-electrode electric nozzle 1 and the outer shell 5 are determined according to the structure of the combustion chamber, and the plane of the head of the igniter is flush with the inner wall of a flame tube of the combustion chamber after the igniter is installed.
The outer shell 5 is of a circular tube type structure with an inner expansion opening, the expansion angle is 130-160 degrees, the preferred expansion angle is 140 degrees, the inner diameter is 12-16 mm, the preferred expansion angle is 14mm, and the outer diameter is 16-22 mm, and the preferred expansion angle is 18 mm. The outer shell 5 is made of 310S stainless steel or high-temperature-resistant alloy, and preferably 310S stainless steel.
Cooling holes 2 are formed in the front face and the round edge chamfer of the top end of the outer shell 5, wherein the cooling holes 2 in the front face are distributed in an equi-circle center mode, the number of the cooling holes is 10-20, preferably 16, and the hole diameter is 0.5-1.5 mm, preferably 1 mm; the cooling holes 2 of the round edge chamfer are distributed in the same circle center, the number is 15-25, the preferred number is 20, and the aperture is 0.3-1.0 mm, the preferred diameter is 0.5 mm.
One side of the outer shell 5 close to the top end is provided with a circulation hole 4, the position of the circulation hole 4 is determined according to the structure of the combustion chamber, the circulation hole 4 is located between the outer shell of the combustion chamber and the wall of the flame tube after the igniter is installed, and cold airflow enters the cooling airflow channel 3 through the circulation hole 4 under the pressure driving. The width of the circulation hole 4 is 2-8 mm, preferably 5mm, and the length is 8-12 mm, preferably 10 mm.
The cooling holes 2 and the circulation holes 4 are connected through cooling airflow channels 3 to form airflow channels, the axes of the airflow channels 3 and the axis of the outer shell 5 are coincident, the section of each airflow channel is of an L-shaped circular seam structure, the inner diameter of each airflow channel is 14-18 mm, the optimal diameter is 16mm, the outer diameter of each airflow channel is 15-20 mm, the optimal diameter is 17mm, and the L-shaped short depth is 2-6 mm, and the optimal diameter is 4 mm.
The rear end of the outer shell 5 is connected with the mounting seat 6, and the outer shell and the mounting seat are connected by adopting a welding technology. The external dimension of the mounting seat 6 is determined according to the structure of the combustion chamber, and 310S stainless steel or high-temperature resistant alloy, preferably 310S stainless steel, is adopted. A boss is arranged at the joint of the mounting seat 6 and the outer shell 5, and the angle of the inclined plane of the boss is determined according to the structure of the combustion chamber, so that the air tightness after mounting is ensured.
Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the description and the embodiments, and can be fully applied to various fields of gas flow cooled multi-electrode high energy igniters suitable for the present invention. Additional modifications and refinements of the present invention will readily occur to those skilled in the art without departing from the principles of the present invention, and therefore the present invention is not limited to the specific details and illustrations shown and described herein without departing from the general concept defined by the claims and their equivalents.
Claims (5)
1. An air-cooled multi-electrode high-energy igniter is characterized by comprising a multi-electrode electric nozzle (1), a cooling hole (2), a cooling air flow channel (3), a circulation hole (4), an outer shell (5) and a mounting seat (6);
the multi-electrode electric nozzle (1) is overlapped with the axis of the outer shell (5), and the multi-electrode electric nozzle (1) is nested in the outer shell (5); the top end plane of the multi-electrode electric nozzle (1) is inwards sunken to form a discharge concave cavity with the outer shell (5);
cooling holes (2) which are uniformly distributed along the circumferential direction are formed in the top end plane of the outer shell (5) close to the edge; the side wall of the outer shell (5) is provided with a circulation hole (4), the inner wall of the outer shell (5) is provided with a circular seam type cooling airflow channel (3), the cooling airflow channel (3) is connected with the cooling hole (2) and the circulation hole (4), and the rear end of the outer shell (5) is provided with a mounting seat (6).
2. The airflow-cooled multi-electrode high-energy igniter according to claim 1, wherein the multi-electrode electric nozzle (1) is formed by nesting and installing a central electrode (101), an inner-layer insulator (102), a relay electrode (103) and an outer-layer insulator (104) from inside to outside in sequence; the number of the relay electrodes (103) is 1 or more to increase the arc length.
3. The airflow-cooled multi-electrode high-energy igniter according to claim 2, wherein the central electrode (101), the inner-layer insulator (102), the relay electrode (103) and the outer-layer insulator (104) of the multi-electrode electric nozzle (1) have the same internal expansion angle, and form a discharge cavity with a smooth surface and a V-shaped cross section after being nested and installed.
4. The gas-cooled multi-electrode high-energy igniter according to claim 1, wherein the igniter is installed in a combustion chamber of an aircraft engine, and the height of the flow holes (4) is between an outer casing of the combustion chamber of the aircraft engine and a wall of a flame tube.
5. The airflow-cooled multi-electrode high-energy igniter as claimed in claim 1, wherein the top plane edge of the outer shell (5) is provided with a round edge chamfer, and cooling holes (2) are uniformly distributed along the circumferential direction on the round edge chamfer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210321236.XA CN114421284B (en) | 2022-03-30 | 2022-03-30 | Air-cooled multi-electrode high-energy igniter |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210321236.XA CN114421284B (en) | 2022-03-30 | 2022-03-30 | Air-cooled multi-electrode high-energy igniter |
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| CN114421284A true CN114421284A (en) | 2022-04-29 |
| CN114421284B CN114421284B (en) | 2022-07-22 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117553321A (en) * | 2024-01-11 | 2024-02-13 | 中国空气动力研究与发展中心计算空气动力研究所 | Multi-channel discharge plasma fuel cracking pneumatic nozzle |
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|---|---|---|---|---|
| GB587564A (en) * | 1942-03-11 | 1947-04-30 | Power Jets Ltd | Improvements relating to igniter plugs |
| US20090021133A1 (en) * | 2007-07-17 | 2009-01-22 | Denso Corporation | Plasma ignition system |
| JP2011034828A (en) * | 2009-08-03 | 2011-02-17 | Ud Trucks Corp | Ignition plug for internal combustion engine |
| US20190154013A1 (en) * | 2017-11-20 | 2019-05-23 | Capacitor Sciences Incorporated | Plasma electric propulsion device |
| JP2019106322A (en) * | 2017-12-13 | 2019-06-27 | 日本特殊陶業株式会社 | Igniter plug |
-
2022
- 2022-03-30 CN CN202210321236.XA patent/CN114421284B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB587564A (en) * | 1942-03-11 | 1947-04-30 | Power Jets Ltd | Improvements relating to igniter plugs |
| US20090021133A1 (en) * | 2007-07-17 | 2009-01-22 | Denso Corporation | Plasma ignition system |
| JP2011034828A (en) * | 2009-08-03 | 2011-02-17 | Ud Trucks Corp | Ignition plug for internal combustion engine |
| US20190154013A1 (en) * | 2017-11-20 | 2019-05-23 | Capacitor Sciences Incorporated | Plasma electric propulsion device |
| JP2019106322A (en) * | 2017-12-13 | 2019-06-27 | 日本特殊陶業株式会社 | Igniter plug |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117553321A (en) * | 2024-01-11 | 2024-02-13 | 中国空气动力研究与发展中心计算空气动力研究所 | Multi-channel discharge plasma fuel cracking pneumatic nozzle |
| CN117553321B (en) * | 2024-01-11 | 2024-03-22 | 中国空气动力研究与发展中心计算空气动力研究所 | Multi-channel discharge plasma fuel cracking pneumatic nozzle |
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| CN114421284B (en) | 2022-07-22 |
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