CN113669161A - Igniter with oxygen supplementing structure - Google Patents
Igniter with oxygen supplementing structure Download PDFInfo
- Publication number
- CN113669161A CN113669161A CN202110984777.6A CN202110984777A CN113669161A CN 113669161 A CN113669161 A CN 113669161A CN 202110984777 A CN202110984777 A CN 202110984777A CN 113669161 A CN113669161 A CN 113669161A
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- Prior art keywords
- oxygen
- base
- nozzle
- igniter
- shell
- Prior art date
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- 239000001301 oxygen Substances 0.000 title claims abstract description 94
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 94
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 title claims abstract description 93
- 230000001502 supplementing effect Effects 0.000 title claims abstract description 16
- 239000000945 filler Substances 0.000 claims abstract description 25
- 238000001816 cooling Methods 0.000 claims description 29
- 238000002485 combustion reaction Methods 0.000 claims description 16
- 239000007789 gas Substances 0.000 claims description 14
- 238000007789 sealing Methods 0.000 claims description 9
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 6
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 2
- 229910001882 dioxygen Inorganic materials 0.000 claims description 2
- 230000001706 oxygenating effect Effects 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 239000002737 fuel gas Substances 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 5
- 238000010892 electric spark Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 3
- 239000013589 supplement Substances 0.000 description 3
- 230000009469 supplementation Effects 0.000 description 3
- 239000000112 cooling gas Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- 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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Air Supply (AREA)
Abstract
An igniter with an oxygen supplementing structure comprises a base and an electric nozzle, wherein a hollow shell is connected and arranged at the lower end of the base; the upper end of the electric nozzle is inserted into the base, and the lower end of the electric nozzle is inserted into the inner cavity of the shell; a gap is formed between the inner wall of the shell and the outer surface of the electric nozzle to form an oxygen flow channel; the lower end of the shell is provided with an exhaust port; and a filler neck structure used for conveying oxygen into the oxygen flow channel is arranged on the side surface of the base. According to the invention, the electric nozzle is inserted into the shell, the shell can protect the electric nozzle from being ablated by high-temperature fuel gas, meanwhile, a gap exists between the inner wall of the shell and the outer surface of the electric nozzle to form an oxygen flow channel, when ignition is difficult under severe conditions at high altitude, oxygen is conveyed to the oxygen flow channel through the pipe connecting nozzle structure and then is discharged to the ignition area of the flame tube through the exhaust port, and the successful ignition is ensured by improving the oxygen content.
Description
Technical Field
The invention relates to the technical field of ignition equipment of combustion chambers of aero-engines, in particular to an igniter with an oxygen supplementing structure.
Background
The igniter is an electric ignition device which is used for igniting oil-gas mixture in a combustion chamber when an aeroengine is started on the ground or in the air, and the quality of ignition performance is directly related to whether the aeroengine can normally work. Igniter designs must take into account the success of the ignition in all the conditions that may occur during the flight of the aircraft.
Ignition modes of an aircraft engine igniter are generally divided into two modes, namely indirect ignition and direct ignition. Indirect ignition generally uses an induction system to ignite a small amount of starting fuel in an igniter to form an ignition torch, and the generated high-temperature and high-pressure torch ignites the whole combustion chamber. The direct ignition mode is that the ignition electric nozzle adopts a capacitance discharge system to generate high-energy electric spark to directly ignite the oil-gas mixture in the flame tube. The energy of the electric spark generated by the capacitance discharge system adopted by the direct ignition mode is tens of times higher than that of the electric spark generated by the inductance system in the indirect ignition mode. The direct ignition method has been developed and widely used from the 50 s of the 20 th century.
Because the oxygen concentration and pressure are very low in high altitude, ignition by direct ignition is difficult. In addition, in the direct ignition mode, a part of the electric nozzle needs to be inserted into the flame tube, in the existing igniter structure, the electric nozzle part inserted into the flame tube is directly exposed in the flame tube, and a cooling structure is not arranged to cool the electric nozzle inserted into the flame tube, so that the electric nozzle is easily ablated by high-temperature gas in the flame tube, and the ignition performance and the service life of the whole igniter are affected.
Disclosure of Invention
The invention mainly aims to provide an igniter with an oxygen supplementing structure, and aims to solve the technical problems.
In order to achieve the purpose, the invention provides an igniter with an oxygen supplementing structure, which comprises a base and an electric nozzle, wherein a hollow shell is connected and arranged at the lower end of the base; the upper end of the electric nozzle is inserted into the base, and the lower end of the electric nozzle is inserted into the inner cavity of the shell; a gap is formed between the inner wall of the shell and the outer surface of the electric nozzle to form an oxygen flow channel; the lower end of the shell is provided with an exhaust port; and a filler neck structure used for conveying oxygen into the oxygen flow channel is arranged on the side surface of the base.
Preferably, at least one cooling air intake hole is provided at a lower portion of the housing; when the igniter is arranged on the combustion chamber, the cooling air inlet is positioned in the outer two channels of the combustion chamber, and the outer two channels are communicated with the oxygen flow channel through the cooling air inlet.
Preferably, the lower end face of the electric nozzle is flush with the lower end face of the shell; when the igniter is arranged on the combustion chamber, the lower end surface of the electric nozzle is positioned in the backflow area of the flame tube; the lower extreme of casing is uncovered form the gas vent one side of terminal surface is provided with the water conservancy diversion tongue piece under the casing, the water conservancy diversion tongue piece with be equipped with the clearance between the lower terminal surface of electric mouth.
Preferably, a plurality of protrusions for positioning the electric nozzle are provided on an inner surface of the lower end of the housing, and an exhaust groove is formed between adjacent two protrusions.
Preferably, an annular groove is arranged on the inner wall of the shell, and an oxygen gas collection chamber is formed between the annular groove and the outer wall of the electric nozzle.
Preferably, the filler neck structure comprises a filler neck and a neck seat; the nozzle base is arranged on the side surface of the base, and an open accommodating cavity is formed in the nozzle base; one end of the filler pipe nozzle is arranged at the opening of the accommodating cavity, and the outer wall of the other end of the filler pipe nozzle is provided with an external thread for connecting with a pipeline of an oxygen generation system of an airplane; the pipe connecting nozzle is provided with a pipe nozzle hole communicated to the accommodating cavity in the pipe nozzle seat; a groove is formed in the inner wall of the base and communicated with the oxygen flow channel; the pipe nozzle seat and the base are integrally formed, and an inclined hole is formed in the connecting part of the pipe nozzle seat and the base; one end of the inclined hole is communicated with the groove, and the other end of the inclined hole is communicated with the accommodating cavity.
Preferably, the inclined hole is provided with an air tap for adjusting and controlling the oxygen flow, the air tap has multiple specifications, and oxygen via holes with different diameters are formed in the air taps with different specifications.
Preferably, a spring and a floating valve body are arranged in the accommodating cavity; one end of the spring is abutted against the bottom wall of the accommodating cavity, and when oxygen is not supplemented, the other end of the spring is abutted against the floating valve body to be plugged at the air outlet end of the filler neck; and during oxygen supplementation, oxygen pushes the floating valve body to enter the accommodating cavity.
Preferably, the filler neck is in threaded connection with the opening of the accommodating cavity, and a first sealing ring is arranged between the filler neck and the opening of the accommodating cavity.
Preferably, a positioning clamping edge is arranged on the upper end face of the shell, and the shell and the base are welded after the positioning clamping edge is inserted into an inner hole in the lower end of the base; the electric nozzle is in threaded connection with the base, and a second sealing ring is arranged between the electric nozzle and the base; the base is provided with an ear plate, and when the igniter is installed on the combustion chamber, the ear plate is lapped on the culvert casing.
The invention has the following beneficial effects:
(1) according to the invention, the electric nozzle is inserted into the shell, the shell can protect the electric nozzle from being ablated by high-temperature fuel gas, meanwhile, a gap exists between the inner wall of the shell and the outer surface of the electric nozzle to form an oxygen flow channel, when ignition is difficult under severe conditions at high altitude, oxygen is conveyed to the oxygen flow channel through the pipe connecting nozzle structure and then is discharged to the ignition area of the flame tube through the exhaust port, and the successful ignition is ensured by improving the oxygen content.
(2) Through set up the cooling inlet port on the casing for the cooling air in the outer two shares of passageway can get into the oxygen runner, can play fine cooling effect to the electric nozzle. In addition, by arranging the flow guide tongue piece, part of cooling air can flow out along the end face of the electric nozzle to isolate high-temperature gas, so that the cooling effect is further improved, the electric nozzle is prevented from being ablated by the high-temperature gas, and the service life and the reliability of the igniter are improved; meanwhile, the cooling gas flowing out of the igniter and the backflow gas flowing out of the flame tube have the same flow direction, and the structure of the backflow area cannot be damaged.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic structural view of an igniter with an oxygen supplement structure according to the present invention;
FIG. 2 is a schematic view of an igniter with an oxygen supplement structure according to the present invention installed in a combustion chamber;
FIG. 3 is a schematic structural view of an igniter housing with an oxygen supplement structure according to the present invention;
FIG. 4 is a view taken along line A of FIG. 3;
description of reference numerals: 1-a base; 101-a nozzle base; 102-a housing chamber; 103-a groove; 104-inclined holes; 105-ear plate; 2-electric nozzle; 3-a shell; 301-oxygen flow channel; 302-an exhaust port; 303-flow guiding tongue piece; 304-a protrusion; 305-an exhaust tank; 306-an annular groove; 307-cooling air inlet holes; 308-positioning the clamping edge; 4-air tap; 5-a spring; 6-floating valve body; 7-filler neck; 701-nozzle hole; 8-a first sealing ring; 81-a second seal ring; 90-combustor case; 91-a flame tube; 92-outer two-strand channels; 93-culvert casing.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
An igniter with an oxygen supplementing structure comprises a base 1 and an electric nozzle 2, wherein the electric nozzle 2 is a semiconductor electric nozzle, the upper end of the electric nozzle 2 is connected with a capacitance discharging system through a high-voltage insulated wire, and the electric nozzle 2 releases high-energy electric sparks to ignite an oil-gas mixture in a flame tube 91 after being electrified. A hollow shell 3 is connected and arranged at the lower end of the base 1; the upper end of the electric nozzle 2 is inserted into the base 1, and the lower end of the electric nozzle 2 is inserted into the inner cavity of the shell 3; a gap is formed between the inner wall of the shell 3 and the outer surface of the electric nozzle 3 to form an oxygen flow channel 301; the lower end of the shell 3 is provided with an air outlet 302; the side of the base 1 is provided with a filler neck structure for delivering oxygen into the oxygen flow channel 301. When ignition is difficult under severe conditions at high altitude, oxygen is conveyed to the oxygen flow channel 301 through the filler neck structure and then is discharged to the ignition area of the flame tube through the exhaust port 302, and the ignition success is ensured by improving the oxygen content.
In the present embodiment, the filler neck structure includes a filler neck 7 and a neck seat 101; the nozzle base 101 is arranged on the side surface of the base 1, and an open accommodating cavity 102 is arranged on the nozzle base 101; one end of the filler pipe nozzle 7 is installed at the opening of the accommodating cavity 102, and the outer wall of the other end is provided with an external thread for connecting with a pipeline of an oxygen generation system of an airplane; a nozzle hole 701 is arranged on the nozzle 7 and communicated to the accommodating cavity 102 in the nozzle seat 101; a groove 103 is formed in the inner wall of the base 1 and communicated with the oxygen runner 301; the nozzle base 101 and the base 1 are integrally formed, and an inclined hole 103 is formed in the connecting part of the nozzle base 101 and the base 1; one end of the inclined hole 103 is communicated with the groove 103, and the other end is communicated with the accommodating cavity 102. When the igniter is installed, the nozzle hole 701 on the nozzle 7 forms an oxygen inlet, the nozzle 7 is connected with an oxygen generation system pipeline of an airplane to be introduced with high-pressure oxygen, and the high-pressure oxygen enters the accommodating cavity 102 through the nozzle hole 701, then enters the groove 103 through the inclined hole, and finally enters the oxygen flow channel 301. The nozzle base 101 and the base 1 can be integrally cast, so that the airtightness between the nozzle base 101 and the base 1 can be ensured.
In the present embodiment, at least one cooling air inlet hole 307 is disposed at the lower portion of the housing 3, specifically, the number of the cooling air inlet holes 307 in the present embodiment is 6, and the cooling air inlet holes are annularly and uniformly distributed at the lower end of the housing 3; when the igniter is installed on the combustion chamber, the cooling air inlet hole 307 is positioned in the outer two-strand channel 92 of the combustion chamber, and the outer two-strand channel 92 is communicated with the oxygen flow channel 301 through the cooling air inlet hole 307. During oxygen supplementation, the pressure of oxygen introduced into the pipeline of the aircraft oxygen generation system can be controlled, so that the pressure of the oxygen in the oxygen channel 301 is smaller than the pressure of cooling air in the outer two channels 92 and is larger than the pressure of the air in the flame tube, the oxygen cannot leak out of the outer two channels 92 when passing through the cooling air inlet hole 307, and the cooling air in the outer two channels 92 can enter the oxygen channel 301. The oxygen is discharged to the flame tube ignition area from the air outlet 302 together with the cooling air entering from the cooling air inlet hole 307, and the oxygen content is increased to ensure the successful ignition. By arranging the cooling air inlet hole 307, the cooling air in the outer two-strand channel 92 can enter the oxygen flow channel 301, and the cooling air has a cooling effect on the electric nozzle 2.
In this embodiment, the inclined hole 104 is provided with an air tap 4 for adjusting and controlling the oxygen flow, the air tap 4 has multiple specifications, and oxygen passing holes with different diameters are formed in the air taps 4 with different specifications. By arranging the air tap 4, the flow of oxygen can be adjusted, and further the oxygen pressure in the oxygen flow channel 301 can be controlled.
In the present embodiment, the lower end surface of the electric nozzle 2 is flush with the lower end surface of the housing 3; when the igniter is arranged on the combustion chamber, the lower end surface of the electric nozzle 2 is positioned in the backflow area of the flame tube 91; the lower extreme of casing 3 is for uncovered form forms gas vent 302 one side of terminal surface is provided with water conservancy diversion tongue piece 303 under the casing 3, water conservancy diversion tongue piece 303 with be equipped with the clearance between the lower terminal surface of electric nozzle 2. By arranging the flow guide tongue piece 303, part of cooling air can flow out along the end face of the electric nozzle 2 to isolate high-temperature gas, so that the cooling effect is further improved, the electric nozzle is prevented from being ablated by the high-temperature gas, and the service life and the reliability of the igniter are improved; meanwhile, the cooling gas flowing out of the igniter and the backflow gas flowing out of the flame tube 91 are ensured to flow in the same direction, and the structure of a backflow area is not damaged.
In this embodiment, a plurality of projections 304 for positioning the electric nozzle 2 are provided on an inner surface of a lower end of the housing 3, and an air discharge groove 305 is formed between adjacent two projections 304. When electric nozzle 2 is installed in casing 3, a plurality of protruding 304 support and lean on the surface of electric nozzle 2 lower extreme, play the positioning action to electric nozzle 2, guarantee electric nozzle 2 and casing 3's axis coincidence, and then guarantee the clearance of oxygen runner 301. In addition, the adoption of the structure that the protrusion 304 is matched with the exhaust groove 305 can improve the rigidity of the tail end of the shell 3, so that the electric nozzle 2 and the shell 3 can ensure that the exhaust hole 302 and the oxygen flow channel 301 are not blocked even under the high-temperature condition.
In this embodiment, an annular groove 306 is disposed on the inner wall of the housing 3, and an oxygen collecting chamber is formed between the annular groove 306 and the outer wall of the electric nozzle 2, and the oxygen collecting chamber can store oxygen and also can form a slow flow effect on the charged high-pressure oxygen, so that the oxygen can be smoothly discharged from the exhaust hole 302 without damaging the backflow area of the flame tube.
In the present embodiment, a spring 5 and a floating valve body 6 are arranged in the accommodating cavity 102; one end of the spring 5 abuts against the bottom wall of the accommodating cavity 102, and when oxygen is not supplemented, the other end of the spring 5 abuts against the floating valve body 6 to block the air outlet end of the filler neck 7; during oxygen supplementation, oxygen pushes the floating valve body 6 away to enter the accommodating cavity 102. The filler neck 7 is in threaded connection with the opening of the accommodating cavity 102, and a first sealing ring 8 is arranged between the filler neck 7 and the opening of the accommodating cavity 102. Through setting up floating valve body 6 and first sealing washer 8, when not oxygenating, floating valve body 6 can carry out the shutoff to mouthpiece 7, forms sealedly with first sealing washer 8 butt mouthpiece 7 jointly, avoids the gas to leak.
In this embodiment, a positioning locking edge 308 is disposed on an upper end surface of the housing 3, when the housing 3 is mounted on the base 1, the positioning locking edge 308 is inserted into an inner hole at a lower end of the base 1, the positioning locking edge 308 is used for ensuring that the axis of the housing 3 coincides with the axis of the base 1, and after the positioning locking edge 308 is inserted into the base 1, the housing 3 and the base 1 are welded to ensure airtightness; the electric nozzle 2 is connected with the base 1 through threads, and a second sealing ring 81 is arranged between the electric nozzle 2 and the base 1; the base 1 is provided with an ear plate 105, and when the igniter is installed on the combustion chamber, the ear plate 105 is lapped on the culvert casing 93.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. The utility model provides a take some firearm of oxygenating structure, includes base (1), electric nozzle (2), its characterized in that: a hollow shell (3) is connected and arranged at the lower end of the base (1);
the upper end of the electric nozzle (2) is inserted into the base (1), and the lower end of the electric nozzle (2) is inserted into the inner cavity of the shell (3); a gap is formed between the inner wall of the shell (3) and the outer surface of the electric nozzle (3) to form an oxygen flow channel (301); the lower end of the shell (3) is provided with an exhaust port (302);
the side surface of the base (1) is provided with a filler neck structure used for conveying oxygen into the oxygen flow channel (301).
2. The igniter with the oxygen supplementing structure according to claim 1, wherein: at least one cooling air inlet hole (307) is arranged at the lower part of the shell (3); when the igniter is installed on the combustion chamber, the cooling air inlet hole (307) is positioned in the outer two channels (92) of the combustion chamber, and the outer two channels (92) are communicated with the oxygen flow channel (301) through the cooling air inlet hole (307).
3. The igniter with the oxygen supplementing structure according to claim 2, wherein: the lower end face of the electric nozzle (2) is flush with the lower end face of the shell (3); when the igniter is arranged on the combustion chamber, the lower end surface of the electric nozzle (2) is positioned in the backflow area of the flame tube 91; the lower extreme of casing (3) is uncovered form formation gas vent (302) one side of terminal surface is provided with water conservancy diversion tongue piece (303) under casing (3), water conservancy diversion tongue piece (303) with be equipped with the clearance between the lower terminal surface of electric nozzle (2).
4. The igniter with the oxygen supplementing structure according to claim 1, wherein: a plurality of protrusions (304) for positioning the electric nozzle (2) are arranged on the inner surface of the lower end of the shell (3), and an exhaust groove (305) is formed between every two adjacent protrusions (304).
5. The igniter with the oxygen supplementing structure according to claim 1, wherein: an annular groove (306) is arranged on the inner wall of the shell (3), and an oxygen gas collection chamber is formed between the annular groove (306) and the outer wall of the electric nozzle (2).
6. The igniter with the oxygen supplementing structure according to claim 1, wherein: the filler neck structure comprises a filler neck (7) and a neck seat (101);
the nozzle base (101) is arranged on the side surface of the base (1), and an open accommodating cavity (102) is arranged on the nozzle base (101);
one end of the filler pipe nozzle (7) is arranged at the opening part of the accommodating cavity (102), and the outer wall of the other end is provided with an external thread for connecting with a pipeline of an oxygen generation system of an airplane; a nozzle hole (701) is formed in the nozzle (7) and communicated to an accommodating cavity (102) in the nozzle seat (101);
a groove (103) is formed in the inner wall of the base (1) and communicated with the oxygen flow channel (301);
the nozzle base (101) and the base (1) are integrally formed, and an inclined hole (103) is formed in the connecting part of the nozzle base (101) and the base (1); one end of the inclined hole (103) is communicated with the groove (103), and the other end of the inclined hole is communicated with the accommodating cavity (102).
7. The igniter with the oxygen supplementing structure according to claim 6, wherein: the inclined hole (104) is provided with an air tap (4) for adjusting and controlling the oxygen flow, the air tap (4) has multiple specifications, and oxygen via holes with different diameters are formed in the air taps (4) with different specifications.
8. The igniter with the oxygen supplementing structure according to claim 6, wherein: a spring (5) and a floating valve body (6) are arranged in the accommodating cavity (102);
one end of the spring (5) is abutted against the bottom wall of the accommodating cavity (102), and when oxygen is not supplemented, the other end of the spring (5) is abutted against the floating valve body (6) to block the air outlet end of the filler neck (7);
when oxygen is supplemented, oxygen pushes the floating valve body (6) away to enter the accommodating cavity (102).
9. The igniter with the oxygen supplementing structure according to claim 6, wherein: the filler neck (7) is in threaded connection with the opening of the accommodating cavity (102), and a first sealing ring (8) is arranged between the filler neck (7) and the opening of the accommodating cavity (102).
10. The igniter with the oxygen supplementing structure according to claim 1, wherein: a positioning clamping edge (308) is arranged on the upper end face of the shell (3), and the shell (3) and the base (1) are welded after the positioning clamping edge (308) is inserted into an inner hole in the lower end of the base (1);
the electric nozzle (2) is in threaded connection with the base (1), and a second sealing ring (81) is arranged between the electric nozzle (2) and the base (1);
the base (1) is provided with an ear plate (105), and when the igniter is installed on the combustion chamber, the ear plate (105) is lapped on the culvert casing (93).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110984777.6A CN113669161A (en) | 2021-08-24 | 2021-08-24 | Igniter with oxygen supplementing structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110984777.6A CN113669161A (en) | 2021-08-24 | 2021-08-24 | Igniter with oxygen supplementing structure |
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| CN113669161A true CN113669161A (en) | 2021-11-19 |
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| CN202110984777.6A Pending CN113669161A (en) | 2021-08-24 | 2021-08-24 | Igniter with oxygen supplementing structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110500611A (en) * | 2018-05-16 | 2019-11-26 | 赛峰航空器发动机 | Component for turbine engine combustion chamber |
| CN117738798A (en) * | 2024-02-21 | 2024-03-22 | 济南中科先行燃气轮机科技有限公司 | Oxygen supplementing combustion-supporting igniter for gas turbine and application method thereof |
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| CN110500611B (en) * | 2018-05-16 | 2023-02-17 | 赛峰航空器发动机 | Assembly for a turbine engine combustor |
| CN117738798A (en) * | 2024-02-21 | 2024-03-22 | 济南中科先行燃气轮机科技有限公司 | Oxygen supplementing combustion-supporting igniter for gas turbine and application method thereof |
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