CN114336144A - Aeroengine ignition cable interface structure - Google Patents
Aeroengine ignition cable interface structure Download PDFInfo
- Publication number
- CN114336144A CN114336144A CN202111522843.4A CN202111522843A CN114336144A CN 114336144 A CN114336144 A CN 114336144A CN 202111522843 A CN202111522843 A CN 202111522843A CN 114336144 A CN114336144 A CN 114336144A
- Authority
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- China
- Prior art keywords
- bush
- interface structure
- plug
- ignition cable
- cable interface
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000007789 sealing Methods 0.000 claims description 17
- -1 polytetrafluoroethylene Polymers 0.000 claims description 4
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 4
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 4
- 230000006978 adaptation Effects 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 6
- 238000012360 testing method Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000004904 shortening Methods 0.000 description 2
- 235000014676 Phragmites communis Nutrition 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000002788 crimping Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 208000002925 dental caries Diseases 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Landscapes
- Ignition Installations For Internal Combustion Engines (AREA)
- Spark Plugs (AREA)
Abstract
The application belongs to the field of engine ignition cable design, and particularly relates to an aeroengine ignition cable interface structure. The structure comprises a plug sleeve (4), wherein the ratio of the length to the inner diameter of a core rod (3) and the plug sleeve (4) which are integrally pressed with a wire is arranged in the plug sleeve (4) and is between 5 and 6, a first annular cavity (41) and a second annular cavity (42) are arranged on the outer ring of the plug sleeve (4), a bushing (7) is directly sleeved outside the plug sleeve (4), the inner wall of the bushing (7) is provided with a first annular bulge (71) of the first annular cavity (41), a nut (5) is arranged outside the bushing (7), and the nut (5) can be matched and arranged on an ignition device. This application plug cover adopts the buckle formula to be connected with the bush, has cancelled the spring and has compressed tightly the part, has shortened cooperation length size.
Description
Technical Field
The application belongs to the field of engine ignition cable design, and particularly relates to an aeroengine ignition cable interface structure.
Background
The interface structure of the existing ignition cable of a certain type of aero-engine is a spring compression type contact pin structure, a bushing and a special nut are arranged on the outermost layer of the interface and are connected with an ignition device through threads, a polytetrafluoroethylene plug sleeve is used for insulation in the middle layer, the middle layer is compressed through the spring structure during connection, a core rod and a lead are integrally compressed and connected through a check ring, and the core rod and the lead are clamped and fixed through the check ring as shown in figure 2.
At present, along with the improvement of the technical state of the engine, the installation position of the ignition cable is changed, the problem of interference between the tail of the existing interface of the ignition cable and other equipment is found during assembly, the interference distance is 6.5mm, and the installation requirement cannot be met.
Disclosure of Invention
In order to solve the technical problem, the application provides an aeroengine ignition cable interface structure, and outmost bush and special nut size of shortening shortens, spring hold-down structure is cancelled in the intermediate level, shortens plug cover size, redesigns plug cover and bush connected mode, guarantees to design or technical innovation with several aspects such as ignition fit size invariant to reach the purpose that reduces interface structure length.
The application provides an aeroengine ignition cable interface structure, including the plug cover, install in the plug cover with wire crimping core rod as an organic whole, wherein, the length of plug cover and the ratio of internal diameter are between 5 ~ 6, plug cover outer loop is provided with first ring chamber and second ring chamber, the outer direct cover of plug cover is equipped with the bush, and the bush inner wall has and arranges in the first annular in first ring chamber is protruding, and the bush outer wall has the second ring chamber that sets up at the bush tip protruding, and the bush externally mounted has the nut, and the bottom of nut has the block the bellied base of second ring chamber, and the nut can the adaptation be installed on ignition, ignition is located the part of nut can extrude and be located sealing washer in the second ring chamber.
Preferably, the plug sleeve is made of polytetrafluoroethylene.
Preferably, the pin is clamped inside the plug bush by a retainer ring.
Preferably, the sealing ring is sleeved in the second annular cavity of the plug sleeve in a matching mode, and the outer diameter of the sealing ring is larger than the inner diameter of the lining.
Preferably, an end of the sealing ring facing the ignition device is provided with a conical surface.
Preferably, the outer wall of the plug sleeve is provided with a plurality of first annular cavities, and correspondingly, the inner wall of the bushing is provided with a plurality of first annular bulges corresponding to the first annular cavities.
Preferably, the length of the bushing is substantially comparable to the dimension of its largest inner diameter.
Preferably, the length of the nut is less than its maximum internal diameter.
This application plug cover adopts the buckle formula to be connected with the bush, has cancelled the spring and has compressed tightly the part, has shortened cooperation length size. During the assembly, the plug sleeve is embedded into the bushing through extrusion, the structure is simple and firm, and the operation is convenient. Meanwhile, 3 parts are reduced, and the production and the processing are easy.
Drawings
FIG. 1 is a schematic structural diagram of a preferred embodiment of an aircraft engine ignition cable interface structure according to the present application.
Fig. 2 is a schematic diagram of a conventional interface structure.
Fig. 3 is a schematic structural diagram of the plug bush of the embodiment shown in fig. 1 of the present application.
Fig. 4 is a schematic view of the bushing structure of the embodiment of fig. 1 of the present application.
The device comprises a retainer ring 1, a reed 2, a core rod 3, a plug sleeve 4, a first annular cavity 41, a second annular cavity 42, a nut 5, a lead 6, a bushing 7, a first annular bulge 71, a second annular bulge 72, a sealing ring 8, a sealing ring 9, a spring sleeve 10 and a spring 11.
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. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides an aeroengine ignition cable interface structure, as shown in figure 1, mainly comprising a plug sleeve 4, a core rod 3 which is integrally pressed with a lead is arranged in the plug sleeve 4, wherein the ratio of the length to the inner diameter of the plug sleeve 4 is 5-6, a first annular cavity 41 and a second annular cavity 42 are arranged on the outer ring of the plug sleeve 4, a bushing 7 is directly sleeved outside the plug sleeve 4, a first annular bulge 71 arranged in the first annular cavity 41 is arranged on the inner wall of the bushing 7, a second annular bulge 72 arranged at the end part of the bushing is arranged on the outer wall of the bushing 7, a nut 5 is arranged outside the bushing 7, the bottom end of the nut 5 is provided with a bottom edge clamped with the second annular bulge 72, and the nut 5 can be fitted on the ignition device, the part of the ignition device located in the nut 5 can press the sealing ring 8 located in the second annular cavity 42.
At present, an ignition cable interface structure adopts a spring compression type contact pin structure, can meet performance requirements, but has the defect of large length, as shown in fig. 2. When an engine in a new state is installed, the problem that the tail of an ignition cable interface interferes with other equipment exists, and the installation requirement cannot be met. In order to reduce the length of the interface and ensure the normal installation and use of the ignition cable, the invention researches and invents the interface structure of the ignition cable of the aero-engine, and in order to realize the aim of the invention, the sizes of the shortening bush and the special nut on the outermost layer are provided by starting analysis from three layers of the interface structure; a spring pressing structure is omitted in the middle layer, the size of the plug sleeve is shortened, and the connection mode of the plug sleeve and the bushing is redesigned; the inner layer is designed or technically innovated in several aspects of ensuring the unchanged matching size with the ignition device by using the existing core rod and wire compression joint and insulation processing structure, thereby achieving the purpose of reducing the length of the interface structure.
The improved interface structure redesigns three parts of a bushing, a special nut and a plug sleeve, wherein the length of the bushing is 27.5mm in the prior art, the application shortens the bushing, so that the length of the bushing 7 is basically equivalent to the maximum inner diameter, and in one specific embodiment, as shown in fig. 4, the inner diameter of the bushing is 12mm, and the length of the bushing is 11.5 mm; on the other hand, the special nut of the application shortens the depth of the thread, the total length is 20mm in the prior art, the length of the nut 5 designed by the application is smaller than the maximum inner diameter, for example, the length is shortened to 17mm, and the maximum inner diameter is about 20 mm; third, the present application improves the plug wrap length, which in the prior art is 44.5mm, and the plug wrap length of the present application is reduced such that the ratio of the length of the plug wrap 4 to the inner diameter is between 5 and 6, for example, in one embodiment, referring to fig. 3, the plug wrap length is reduced to 34.5mm and the inner diameter is 6 mm. Compared with the existing interface structure, the length and the size of the interface can be reduced by 20.5mm after improvement.
This application is improved plug cover and bush connected mode, and in the interface after the improvement, plug cover and bush adopt the buckle formula to be connected, have cancelled the spring and have compressed tightly the part, have shortened cooperation length size. During the assembly, the plug sleeve is embedded into the bushing through extrusion, the structure is simple and firm, and the operation is convenient. Meanwhile, 3 parts are reduced, and the sealing ring 9, the spring sleeve 10 and the spring 11 are reduced by combining the figure 1 and the figure 2, so that the integral structure is easy to produce and process.
In order to verify that the ignition cable interface provided by the patent is reasonable and effective in structure, 1 ignition cable test piece is processed according to the method, the performance parameters of the ignition cable before and after the interface is improved are detected, and the comparison condition is shown in table 1.
TABLE 1 Performance comparison before and after improvement
The comparison shows that the performance of the ignition cable is not adversely affected after the interface is changed, and the performance meets the requirement. The test piece, the ignition electric nozzle and the ignition device are matched to form an ignition system, a vibration environment test is carried out, the test result is qualified, and the installation requirement of the engine in a new state can be met.
In some alternative embodiments, the plug wrap 4 is made of polytetrafluoroethylene.
In some alternative embodiments, the pin 3 is clamped inside the plug housing 4 by the retainer ring 1, and in this embodiment, the retainer ring 1 presses the pin 3 and the lead 6 into the plug housing by the pressing spring pieces 2.
In some alternative embodiments, the sealing ring 8 is fitted in the second annular cavity of the plug bush 4, and the outer diameter of the sealing ring 8 is larger than the inner diameter of the bushing 7. Referring to fig. 1, the thickness of the sealing ring 8 is set to be able to press at least the end of the plug bush 4 and the bush 7 simultaneously.
In some alternative embodiments, the end of the sealing ring 8 facing the ignition device is provided as a conical surface. In this embodiment, the ignition device continuously presses the seal ring 8 during the tightening of the nut 5 by the tapered surface, thereby improving the sealing performance of the structure.
In some alternative embodiments, the outer wall of the plug bush 4 is provided with a plurality of first annular cavities, and correspondingly, the inner wall of the bush 7 is provided with a plurality of first annular projections corresponding to the first annular cavities 41. In this embodiment, through the cooperation of a plurality of first ring cavitys and first annular bulge, realize the sealed cooperation of bush and plug cover, improve sealed effect.
The ignition cable interface structure is successfully installed on the engine in a new state, the gap between the ignition cable interface structure and other equipment after installation can reach 14mm, and the use requirement can be met.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides an aeroengine ignition cable interface structure, includes plug cover (4), install in plug cover (4) and press with the wire core pole (3) as an organic whole, its characterized in that, the ratio of the length of plug cover (4) and internal diameter is between 5 ~ 6, plug cover (4) outer loop is provided with first ring chamber (41) and second ring chamber (42), direct cover is equipped with bush (7) outside plug cover (4), and bush (7) inner wall has arranges in first annular bulge (71) of first ring chamber (41), and bush (7) outer wall has sets up second annular bulge (72) at the bush tip, and bush (7) installs nut (5) outward, and the bottom of nut (5) has the block the base of second annular bulge (72), and nut (5) can the adaptation be installed on ignition, ignition is located the part of nut (5) can extrude and be located the sealing washer in second ring chamber (42) (8).
2. An aircraft engine ignition cable interface structure as claimed in claim 1, characterized in that the plug bush (4) is made of polytetrafluoroethylene.
3. The aeroengine ignition cable interface structure of claim 1, characterized in that the pin (3) is snap-fitted inside the plug bush (4) by a retainer ring (1).
4. The aircraft engine ignition cable interface structure of claim 1, characterized in that the sealing ring (8) is adapted to be sleeved in the second annular cavity of the plug bush (4), and the outer diameter of the sealing ring (8) is larger than the inner diameter of the bushing (7).
5. An aircraft engine ignition cable interface structure as claimed in claim 1, characterized in that the end of the sealing ring (8) facing the ignition device is provided as a conical surface.
6. An aircraft engine ignition cable interface structure as claimed in claim 1, characterized in that the plug bush (4) outer wall is provided with a plurality of first annular cavities, and correspondingly, the bush (7) inner wall has a plurality of first annular projections corresponding to the first annular cavities (41).
7. An aircraft engine ignition cable interface structure as claimed in claim 1, characterized in that the length of the bushing (7) is substantially comparable to the dimension of its largest inner diameter.
8. An aircraft engine ignition cable interface structure as claimed in claim 1, characterized in that the length of the nut (5) is less than its largest inner diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111522843.4A CN114336144B (en) | 2021-12-13 | 2021-12-13 | Aeroengine ignition cable interface structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111522843.4A CN114336144B (en) | 2021-12-13 | 2021-12-13 | Aeroengine ignition cable interface structure |
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| Publication Number | Publication Date |
|---|---|
| CN114336144A true CN114336144A (en) | 2022-04-12 |
| CN114336144B CN114336144B (en) | 2024-05-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111522843.4A Active CN114336144B (en) | 2021-12-13 | 2021-12-13 | Aeroengine ignition cable interface structure |
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2021
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| CN114336144B (en) | 2024-05-03 |
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