CN112664324A - Aviation ignition electric nozzle capable of adjusting discharge gap - Google Patents
Aviation ignition electric nozzle capable of adjusting discharge gap Download PDFInfo
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- CN112664324A CN112664324A CN202011490156.4A CN202011490156A CN112664324A CN 112664324 A CN112664324 A CN 112664324A CN 202011490156 A CN202011490156 A CN 202011490156A CN 112664324 A CN112664324 A CN 112664324A
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- electrode
- discharge gap
- adjusting
- insulator
- nozzle capable
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- 239000012212 insulator Substances 0.000 claims abstract description 20
- 229910000575 Ir alloy Inorganic materials 0.000 claims abstract description 18
- 239000000956 alloy Substances 0.000 claims description 11
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 10
- 238000002788 crimping Methods 0.000 claims description 6
- 229910052786 argon Inorganic materials 0.000 claims description 5
- 238000003466 welding Methods 0.000 claims description 5
- 238000013461 design Methods 0.000 abstract description 7
- 210000001503 joint Anatomy 0.000 abstract description 2
- 238000012856 packing Methods 0.000 abstract 2
- 230000005611 electricity Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 7
- 229910045601 alloy Inorganic materials 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 239000007772 electrode material Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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Abstract
The utility model belongs to aeroengine ignition electric nozzle design field relates to an aviation ignition electric nozzle that can carry out discharge gap adjustment, including side electrode, central electrode, insulator, adjustment packing ring, pin and casing, wherein, the pin sets up in the casing with central electrode, and keeps apart through insulator and casing, and the tip of casing has the ring cap along radially extending, the side electrode is compressed tightly by the insulator in the axial on the ring cap, the tip of pin is provided with the extension that the internal diameter reduces to form the step in the department of reducing, be provided with the blind hole of radial extension rather than the central electrode tip of butt joint, the extension can stretch into in the blind hole to realize the electricity and connect, the step with be provided with the adjustment packing ring of removable thickness between the central electrode tip. The application realizes accurate controllability of the size of the discharge gap of the ignition nozzle and high consistency, thereby ensuring stable and reliable performance of the ignition nozzle with the iridium alloy electrode and meeting the requirement of the engine on the service life of the ignition nozzle.
Description
Technical Field
The application belongs to the field of aero-engine ignition electric nozzle design, and particularly relates to an aero-ignition electric nozzle capable of adjusting a discharge gap.
Background
The existing method for adjusting the discharge gap of the ignition nozzle of the aero-engine ensures that the discharge gap meets the requirements by machining the end face size of an electrode, specifically, as shown in fig. 1, the ignition nozzle comprises a core rod 6 connected with one pole of a discharge device and a shell 7 connected with the other pole of the discharge device, the core rod 6 is arranged in the shell 7 and is isolated from the shell 7 through an insulator 4, the end part of the core rod 6 in the shell 7 is connected with a high-temperature alloy electrode 8, and the discharge gap between the high-temperature alloy electrode 8 and a side electrode (not shown) connected with the shell 7 needs to meet the design requirements.
In the prior art, the electrode is made of high-temperature alloy and has good processing performance. At present, the engine provides higher requirements for the service life of the ignition electric nozzle, the conventional high-temperature alloy electrode cannot meet the service requirement of the whole service life, a novel iridium alloy electrode material is required to be adopted, but the iridium alloy material has high processing difficulty and cannot be processed for the second time after being formed, so that the existing discharge gap adjusting method is not suitable any more, the discharge gap adjusting method needs to be redesigned, and the stable performance of the ignition electric nozzle is ensured.
Disclosure of Invention
In order to solve the problem, the application provides an aviation ignition nozzle capable of adjusting a discharge gap so as to ensure that the discharge gap of the ignition nozzle meets the design requirement, and further ensure that the discharge voltage and the spark energy of the ignition nozzle are stable and reliable. And simultaneously, the requirement of the engine on the service life of the ignition nozzle is met.
This application can carry out aviation ignition electric nozzle of discharge gap adjustment mainly includes: the electrode comprises a side electrode, a center electrode, an insulator, an adjusting washer, a core rod and a shell, wherein the core rod and the center electrode are arranged in the shell and are isolated from the shell through the insulator, a ring cover radially extends from the end of the shell, the side electrode is axially pressed on the ring cover through the insulator, an extension part with a reduced inner diameter is arranged at the end of the core rod, a step is formed at the reduced part, a blind hole radially extending is formed at the end of the center electrode in butt joint with the extension part, the extension part can extend into the blind hole and realize electric connection, and the adjusting washer with replaceable thickness is arranged between the step and the end of the center electrode.
Preferably, three sets of adjusting washers are preset in each set, the thicknesses of the three sets of adjusting washers are respectively 0.1mm, 0.3mm and 0.5mm, two adjusting washers with the thickness of 0.1mm are arranged, and one adjusting washer with the rest thickness is arranged.
Preferably, one or more tuning washers are disposed between the step and the end of the center electrode.
Preferably, a gasket is provided between the outer side of the side electrode in the radial direction and the inner wall of the case.
Preferably, the core rod further comprises a crimping portion having a relatively large inner diameter, the insulator being provided with an inclined conical surface facing away from the side electrode in the axial direction, the crimping portion being crimped onto the inclined conical surface in the radial direction.
Preferably, the central electrode is an electrode made of iridium alloy material.
Preferably, the side electrode is an electrode made of an iridium alloy material.
Preferably, after the gap between the center electrode and the side electrode is adjusted by the adjusting washer, the center electrode and the core rod are connected by argon arc welding at a position between the step and the center electrode.
The discharge gap is a core parameter of an ignition nozzle product, and the size of the discharge gap determines the size of discharge voltage and spark energy, so that the selection of the optimal discharge gap and the reduction of the deviation of the discharge gap are very important. The method solves the problem that the discharge gap of the iridium alloy electrode is not well adjusted, so that the adjustment range of the discharge gap of the iridium alloy electrode reaches +/-0.5 mm, and the minimum adjustment size is 0.1 mm. The size of the discharge gap of the ignition nozzle is accurate and controllable, the consistency is high, the ignition nozzle with the iridium alloy electrode is stable and reliable in performance, and the service life requirement of an engine on the ignition nozzle is met.
Drawings
Fig. 1 is a structure diagram of a conventional superalloy electrode discharge end.
Fig. 2 is a schematic structural diagram of an aviation ignition nozzle capable of adjusting a discharge gap according to the present application.
Fig. 3 is a schematic diagram of the structure of the center electrode according to the embodiment shown in fig. 2 of the present application.
FIG. 4 is a schematic illustration of the mandrel structure of the embodiment of FIG. 2 of the present application.
Among them, 1-side electrode, 2-gasket, 3-center electrode, 4-insulator, 5-tuning gasket, 6-mandrel, 61-extension, 62-step, 63-crimp, 7-shell, 8-superalloy electrode.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
As shown in fig. 2-4, the aviation ignition nozzle capable of adjusting discharge gap provided by the present application mainly comprises a side electrode 1, a central electrode 3, an insulator 4, an adjusting washer 5, a core rod 6 and a housing 7, wherein the core rod 6 and the central electrode 3 are arranged in the housing 7 and are separated from the housing 7 by the insulator 4, an end of the housing 7 extends in a radial direction to form a ring cover, the side electrode 1 is pressed on the ring cover by the insulator 4 in an axial direction, the end of the core rod 6 is provided with an extension part 61 with a reduced inner diameter, a step 62 is formed at the reduction, the end of the central electrode 3 abutting against the extension part is provided with a blind hole 31 extending in a radial direction, the extension part 61 can extend into the blind hole 31 and realize electrical connection, and the adjusting washer 5 with replaceable thickness is arranged between the step 62 and the end of the central electrode 3.
In some alternative embodiments, each set of adjusting washers 5 is preset with three sets, with thicknesses of 0.1mm, 0.3mm and 0.5mm, respectively, wherein there are two adjusting washers with a thickness of 0.1mm, and one adjusting washer with the remaining thickness.
In some alternative embodiments, one or more tuning washers 5 are disposed between the step 62 and the end of the center electrode 3.
In some alternative embodiments, a gasket 2 is provided between the outside of the side electrode 1 in the radial direction and the inner wall of the housing 7.
In some alternative embodiments, the mandrel 6 further comprises a crimping portion 63 with a larger inner diameter, the insulator 4 being provided with an inclined conical surface facing axially away from the side electrode, the crimping portion 63 being crimped radially onto the inclined conical surface.
In some alternative embodiments, the central electrode 3 is an electrode made of iridium alloy material.
In some alternative embodiments, the side electrode 1 is an electrode made of an iridium alloy material.
In some alternative embodiments, center electrode 3 and mandrel 6 are joined by argon arc welding at a location between step 62 and center electrode 3 after the gap between center electrode 3 and side electrode 1 is adjusted by adjusting washer 5.
When the ignition torch provided by the present application is used for adjusting the discharge gap, the ignition torch mainly includes the following steps:
the parts are first assembled according to fig. 2: the gasket is placed in the case together with the side electrode, and then the insulator is placed with the discharge end facing downward, and the side electrode is pressed flat with the insulator. Then an adjusting washer with the thickness of 0.5mm is placed between the mandrel and the iridium alloy electrode to form a whole and is arranged in the insulator. Finally, the core rod is propped against, the discharge end is integrally inverted upwards, and the size of the discharge gap is measured;
then, adjusting a discharge gap: and comparing the design size according to the discharge gap measurement result in the last step, and adjusting the combination of the adjusting washer. When the size of the discharge gap is larger, the thickness of the adjusting gasket is increased, and when the size of the discharge gap is smaller, the thickness of the adjusting gasket is reduced. Then, reassembling and measuring the gap size of the placing points according to the first step until the gap size is adjusted to the design size;
the discharge voltage was then tested: measuring the discharge voltage of the component with the adjusted discharge gap by using special discharge voltage test equipment for the ignition nozzle, and ensuring that the discharge voltage meets the design requirement;
and finally, argon arc welding connection is carried out: a set of parts with normal discharge voltage measurement were connected by argon arc welding at the position shown in fig. 2, and finally all parts were assembled in place.
The discharge gap is a core parameter of an ignition nozzle product, and the size of the discharge gap determines the size of discharge voltage and spark energy, so that the selection of the optimal discharge gap and the reduction of the deviation of the discharge gap are very important. The method solves the problem that the discharge gap of the iridium alloy electrode is not well adjusted, so that the adjustment range of the discharge gap of the iridium alloy electrode reaches +/-0.5 mm, and the minimum adjustment size is 0.1 mm. The size of the discharge gap of the ignition nozzle is accurate and controllable, the consistency is high, the ignition nozzle with the iridium alloy electrode is stable and reliable in performance, and the service life requirement of an engine on the ignition nozzle is met.
The method has the characteristics of large adjustment range and high precision, and can be used for selecting the optimal size of the discharge gap of the iridium alloy electrode ignition nozzle and adjusting the discharge gap in production and processing. The method is successfully applied to the discharge gap adjustment of the iridium alloy electrode ignition electric nozzle of a new research and development machine, and has good use effect.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (8)
1. An aviation ignition torch capable of adjusting a discharge gap, comprising:
a side electrode (1), a center electrode (3), an insulator (4), an adjusting washer (5), a core rod (6) and a shell (7), wherein the core rod (6) and the central electrode (3) are arranged in the shell (7), and is separated from the shell (7) by an insulator (4), the end part of the shell (7) extends along the radial direction to form a ring cover, the side electrode (1) is pressed on the ring cover by an insulator (4) in the axial direction, the end of the mandrel (6) is provided with an extension part (61) with a reduced inner diameter, and a step (62) is formed at the reduced part, the end part of the center electrode (3) butted with the center electrode is provided with a blind hole (31) extending in the radial direction, the extending part (61) can extend into the blind hole (31), and realize the electric connection, be provided with adjustable washer (5) of removable thickness between step (62) and the center electrode (3) tip.
2. The aviation ignition nozzle capable of discharge gap adjustment according to claim 1, characterized in that:
three groups of adjusting washers (5) are preset in each set, the thicknesses of the adjusting washers are respectively 0.1mm, 0.3mm and 0.5mm, two adjusting washers with the thickness of 0.1mm are arranged, and one adjusting washer with the rest thickness is arranged.
3. The aviation ignition nozzle capable of discharge gap adjustment according to claim 2, characterized in that:
one or more adjusting gaskets (5) are arranged between the step (62) and the end part of the central electrode (3).
4. The aviation ignition nozzle capable of discharge gap adjustment according to claim 1, characterized in that:
and a gasket (2) is arranged between the outer side of the side electrode (1) along the radial direction and the inner wall of the shell (7).
5. The aviation ignition nozzle capable of discharge gap adjustment according to claim 1, characterized in that:
the core rod (6) further comprises a crimping portion (63) with a relatively large inner diameter, the insulator (4) is provided with an oblique conical surface facing away from the side electrode in the axial direction, and the crimping portion (63) is crimped on the oblique conical surface in the radial direction.
6. The aviation ignition nozzle capable of discharge gap adjustment according to claim 1, characterized in that:
the central electrode (3) is made of iridium alloy material.
7. The aviation ignition nozzle capable of discharge gap adjustment according to claim 1, characterized in that:
the side electrode (1) is an electrode made of iridium alloy material.
8. The aviation ignition nozzle capable of discharge gap adjustment according to claim 1, characterized in that:
after the gap between the central electrode (3) and the side electrode (1) is adjusted through the adjusting washer (5), the central electrode (3) and the mandrel (6) are connected through argon arc welding at the position between the step (62) and the central electrode (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011490156.4A CN112664324A (en) | 2020-12-16 | 2020-12-16 | Aviation ignition electric nozzle capable of adjusting discharge gap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011490156.4A CN112664324A (en) | 2020-12-16 | 2020-12-16 | Aviation ignition electric nozzle capable of adjusting discharge gap |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112664324A true CN112664324A (en) | 2021-04-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011490156.4A Pending CN112664324A (en) | 2020-12-16 | 2020-12-16 | Aviation ignition electric nozzle capable of adjusting discharge gap |
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| Country | Link |
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| CN (1) | CN112664324A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1450825A (en) * | 1974-05-02 | 1976-09-29 | Smiths Industries Ltd | Methods of manufacturing semiconductor bodies and to the products of such methods |
| CN201215862Y (en) * | 2008-06-23 | 2009-04-01 | 南京电气（集团）有限责任公司 | Intermittent apparatus for electricity discharging |
| CN102678339A (en) * | 2012-05-29 | 2012-09-19 | 哈尔滨工程大学 | Plasma igniter with reusable cathode |
| CN110821733A (en) * | 2019-11-13 | 2020-02-21 | 陕西航空电气有限责任公司 | Engine electric nozzle capable of preventing fuel flow attenuation |
-
2020
- 2020-12-16 CN CN202011490156.4A patent/CN112664324A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1450825A (en) * | 1974-05-02 | 1976-09-29 | Smiths Industries Ltd | Methods of manufacturing semiconductor bodies and to the products of such methods |
| CN201215862Y (en) * | 2008-06-23 | 2009-04-01 | 南京电气（集团）有限责任公司 | Intermittent apparatus for electricity discharging |
| CN102678339A (en) * | 2012-05-29 | 2012-09-19 | 哈尔滨工程大学 | Plasma igniter with reusable cathode |
| CN110821733A (en) * | 2019-11-13 | 2020-02-21 | 陕西航空电气有限责任公司 | Engine electric nozzle capable of preventing fuel flow attenuation |
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Application publication date: 20210416 |
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| RJ01 | Rejection of invention patent application after publication |