CN217641870U

CN217641870U - Aeroengine ignition cable

Info

Publication number: CN217641870U
Application number: CN202123274037.8U
Authority: CN
Inventors: 张宇飞; 王晓乐; 苏子为
Original assignee: AVIC Shenyang Xinghua Aero Electrical Appliance Co Ltd
Current assignee: AVIC Shenyang Xinghua Aero Electrical Appliance Co Ltd
Priority date: 2021-12-23
Filing date: 2021-12-23
Publication date: 2022-10-21
Anticipated expiration: 2031-12-23

Abstract

An aircraft engine ignition cable for connecting an ignition device and an ignition torch, comprising: the high-voltage-resistant wire connector comprises a first contact device, a second contact device and a high-voltage-resistant wire; the first contact device comprises a first metal inner core, a wiring pipe and a rubber support sleeve, the wiring pipe is sleeved on the outer layer of the first metal inner core, the rubber support sleeve is sleeved on the outer layer of one end of the wiring pipe, and the other end of the wiring pipe is electrically connected with the ignition device; the second contact device comprises a second metal inner core, a spring, a supporting sleeve, a ceramic insulator and a contact, wherein the supporting sleeve is sleeved on the outer layer of the second metal inner core, the spring is sleeved on the outer layer of one end of the supporting sleeve, the ceramic insulator is sleeved on the outer layer of the other end of the supporting sleeve, one end of the ceramic insulator is connected with the contact, and the contact is electrically connected with the ignition electric nozzle. Unique first contact device and second contact device have been designed according to ignition system butt joint demand, have researched and developed high voltage resistant wire simultaneously, have promoted the cable and have born and the transmission ability to the high voltage in ignition system.

Description

Aeroengine ignition cable

Technical Field

The specification relates to the field of aircraft engine ignition systems, in particular to an aircraft engine ignition cable.

Background

The ignition system is used as the key for starting the energy of the aircraft engine, is a key part for starting and restarting the engine, and mainly comprises an igniter body, an ignition electric nozzle and an ignition cable. The ignition cable is used for connecting the igniter body and the ignition electric nozzle, and needs to have the capacity of bearing short-time high pressure, and the common structural cable cannot complete the work. Under the circumstances, there is an urgent need for an ignition cable capable of withstanding high voltage, stably transmitting instantaneous high voltage in an ignition system, and enabling the system to operate normally.

SUMMERY OF THE UTILITY MODEL

In view of this, the embodiments of the present disclosure provide an aircraft engine ignition cable to solve the problem that the high voltage between the ignition device and the ignition nozzle in the aircraft engine ignition system cannot be sustained and transmitted.

The embodiment of the specification provides the following technical scheme:

an aircraft engine ignition cable for connecting an ignition device and an ignition torch, comprising: a first contact device 1, a second contact device 2 and a high voltage resistant wire 3;

the first contact device 1 comprises a first metal inner core, a wiring pipe 101 and a rubber support sleeve 102, the wiring pipe 101 is sleeved on the outer layer of the first metal inner core, the rubber support sleeve 102 is sleeved on the outer layer of one end of the wiring pipe 101, and the other end of the wiring pipe 101 is electrically connected with an ignition device;

the second contact device 2 comprises a second metal inner core, a spring 201, a support sleeve 202, a ceramic insulator 203 and a contact 204, the support sleeve 202 is sleeved on the outer layer of the second metal inner core, the spring 201 is sleeved on the outer layer of one end of the support sleeve 202, the ceramic insulator 203 is sleeved on the outer layer of the other end of the support sleeve 202, one end of the ceramic insulator 203 is connected with the contact 204, and the contact 204 is electrically connected with the ignition electric nozzle;

one end of the high-voltage resistant wire 3 is electrically connected with the first metal inner core of the first contact device 1, and the other end of the high-voltage resistant wire 3 is electrically connected with the second metal inner core of the second contact device 2.

Further, the high-voltage resistant wire 3 is of a multilayer structure, the innermost layer of the high-voltage resistant wire 3 is a conductor 301, and an insulator 302, an insulating fiber tape wrapping 303 and a glass fiber braid 304 are sequentially sleeved outside the conductor 301 along the direction from inside to outside.

Further, the insulator 302 is one or more of a polytetrafluoroethylene film or a polyperfluoroethylene propylene film.

Further, the insulating fiber tape wrapping 303 is a wrapped and wrapped fiberglass layer.

Further, the rubber support sleeve 102 is silicon rubber.

Further, the aircraft engine ignition cable further comprises a shielding hose assembly 4, and the shielding hose assembly 4 is arranged on the outer layer of the high-voltage resistant lead 3.

Further, the shielding hose assembly 4 includes a first connection nut 401, a second connection nut 402 and a shielding hose, the shielding hose is sleeved on the outer layer of the high voltage resistant wire 3, and the first connection nut 401 and the second connection nut 402 are respectively disposed at two ends of the shielding hose.

Further, the first metal inner core of the first contact device 1 and the high voltage resistant wire 3 are provided with a connecting portion, and the outer layer of the connecting portion is sleeved with the first connecting nut 401.

Further, the second metal inner core of the second contact device 2 and the high voltage resistant wire 3 are provided with a connecting portion, and the outer layer of the connecting portion is sleeved with a second connecting nut 402.

Further, the aircraft engine ignition cable further comprises a connecting tube assembly 5, wherein the connecting tube assembly 5 comprises a first connector 501, a second connector 502 and a metal straight tube 503, the first connector 501 is connected with the second connecting nut 402, and the second connector 502 is connected with the first connecting nut 401.

Further, the junction block assembly 5 is fixed to a set device by a clamp dedicated to the engine.

Compared with the prior art, the beneficial effects that can be achieved by the at least one technical scheme adopted by the embodiment of the specification at least comprise:

unique first contact device 1 and second contact device 2 have been designed according to ignition system butt joint demand, have researched and developed high voltage resistant wire 3 simultaneously, have solved the problem that ordinary structure cable can't bear the voltage more than 10000V, have promoted cable bearing capacity and transmission ability to the high voltage in ignition system. The shielding hose assembly 4 is sleeved outside the high-voltage resistant lead 3. The connecting pipe assembly 5 is additionally arranged, and the requirement for actual installation and laying of the cable is met. The ignition cable structure has the characteristics of small volume, light weight, strong environment resistance, high reliability, high transmission capability and the like, and is suitable for various aircraft engine ignition systems.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

Fig. 1 is a schematic view of the overall structure of the ignition cable of the present invention;

FIG. 2 is a schematic view of a first contact device according to the present invention;

FIG. 3 is a schematic view of a second contact device according to the present invention;

FIG. 4 is a schematic view of the structure of the high voltage resistant wire of the present invention;

fig. 5 is a schematic structural view of the connecting tube assembly of the present invention.

Description of the reference numerals: 1. a first contact device; 101. a wire connecting pipe; 102. a rubber support sleeve; 2. a second contact device; 201. a spring; 202. a support sleeve; 203. a ceramic insulator; 204. a contact; 3. a high voltage resistant wire; 301. a conductor; 302. an insulator; 303. wrapping the insulating fiber tape; 304. a glass fiber woven layer; 4. a shielding hose assembly; 401. a first connecting nut; 402. a second coupling nut; 5. a connecting tube assembly; 501. a first joint; 502. a second joint; 503. a straight metal tube.

Detailed Description

Embodiments of the present application are described in detail below with reference to the accompanying drawings.

The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The application is capable of other and different embodiments and its several details are capable of modifications and various changes in detail without departing from the spirit of the application. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. 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 application.

It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number and aspects set forth herein. In addition, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to or other than one or more of the aspects set forth herein.

It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present application, and the drawings only show the components related to the present application rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.

In addition, in the following description, specific details are provided to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.

The technical solutions provided by the embodiments of the present application are described below with reference to the accompanying drawings.

As shown in fig. 2, the first contact device 1 uses a metal core, and a wire barrel 101 is sleeved outside the metal core. The wire connecting tube 101 is externally matched with a rubber supporting sleeve 102 made of 6144 silicon rubber. After the metal inner core and the high-voltage resistant lead 3 are welded, the solder is filled for 2-3 mm, the metal inner core is butted with an ignition device through a first connecting nut 401 on the shielding hose assembly 4 during use, and the rubber supporting sleeve 102 ensures reliable butting.

In this embodiment, the shield hose of the shield hose assembly 4 is braided using 1Cr18Ni9Ti stainless steel wires.

As shown in fig. 3, the second contact device 2 is a metal core, and a supporting sleeve 202 made of brass is sleeved outside the metal core. The ceramic insulator 203 is sleeved at one end of the outer part of the support sleeve 202, the ceramic insulator 203 is a ceramic connecting sleeve, the ceramic connecting sleeve is of a transverse horn-shaped structure, one end of the ceramic connecting sleeve is wide, and the other end of the ceramic connecting sleeve is narrow. The ceramic connecting sleeve can form a ceramic surface electric nozzle after being butted with the ignition point nozzle. The ceramic surface electric nozzle is an electric nozzle discharging along the surface of a ceramic insulator, and has the advantages of high energy, high ignition reliability and long service life. The ceramic creeping nozzle adopts a sunken electrode-hidden structure, which is beneficial to reducing the temperature of the end of the nozzle and prolonging the service life of the nozzle, and the nozzle has higher breakdown voltage which is generally 5KV to 8KV.

The structure of supporting the outside other end collocation spring 201 of cover 202, need wear out and break up the welding with high voltage resistant wire 3 from second contact device 2 when welding with high voltage resistant wire 3, polish the processing after the welding, guarantee that the welding terminal surface is level and smooth, dock with ignition through second connecting nut 402 on the shielding hose assembly 4 during the use, guarantee through spring 201 that the butt joint locking is reliable.

As shown in FIG. 4, the thickness of the insulation layer of the normal wire is 0.1-0.2mm, and a sintering process is adopted. The high-voltage resistant lead 3 adopts a lapping form to replace a sintering process while the thickness of the insulator 302 is increased, and an insulating fiber tape lapping 303 layer is added outside the insulator 302, so that the high-voltage resistance of the high-voltage resistant lead 3 is improved compared with the traditional lead. Meanwhile, the outermost layer of the high-voltage resistant wire 3 is sleeved with a glass fiber braided layer 304. The structure of the high-voltage resistant lead 3 enables the high-voltage resistant lead to bear 13kV high-frequency spark tests and 25kV limit voltage resistant tests, and meanwhile, the use temperature can meet the requirements of minus 60-250 ℃.

In this embodiment, the insulator (302) is a teflon film.

As shown in fig. 5, the connecting pipe assembly 5 is composed of a first joint 501 and a second joint 502 made of two aluminum alloy rods, and a straight metal pipe 503 made of an aluminum alloy pipe. The first joint 501 and the metal straight pipe 503, and the second joint 502 and the metal straight pipe 503 are welded through circumferential argon arc respectively. The joint of the connecting pipe assembly 5 is provided with threads, and two sections of shielding hose assemblies 4 can be connected together by butting with a first connecting nut 401 and a second connecting nut 402 on the shielding hose assemblies 4, so that the connecting pipe assembly has the advantages of light weight and high reliability. The connecting pipe assembly 5 can be connected with a fixing assembly such as a special clamp of an engine, and a cable can be installed and positioned to a required position.

As shown in fig. 1, the overall structure of the ignition cable is as follows:

the ignition cable is composed of a high-voltage-resistant lead 3, a first contact device 1, a second contact device 2, a shielding hose assembly 4 and a connecting pipe assembly 5. After the high-voltage-resistant lead 3 is welded with the first contact device 1 and the second contact device 2 at high temperature, the shielding hose assembly 4 and the connecting pipe assembly 5 are sleeved outside, so that the ignition cable has the capability of resisting environments such as salt mist, damp heat, mold and the like while transmitting high voltage. The ignition cable structure is applied to an engine ignition system, instantaneous high voltage generated by an ignition device is transmitted to an ignition electric nozzle, mixed gas in a combustion chamber of the engine is ignited, and the ignition cable structure has the advantages of light weight, high reliability, strong environment resistance and the like, and meets the use requirements of aviation power generation.

Table 1 shows specific parameters of the structure of the high-voltage-resistant wire 3.

TABLE 1

In other embodiments, the insulator 302 may also be a fluorinated ethylene propylene film.

The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments can be referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, for the method embodiments described later, since they correspond to the system, the description is simple, and for relevant points, reference may be made to the partial description of the system embodiments.

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

1. An aircraft engine ignition cable for connecting an ignition device and an ignition torch, comprising: the device comprises a first contact device (1), a second contact device (2) and a high-voltage-resistant wire (3);

the first contact device (1) comprises a first metal inner core, a wire connecting pipe (101) and a rubber support sleeve (102), the wire connecting pipe (101) is sleeved outside the first metal inner core, the rubber support sleeve (102) is sleeved outside one end of the wire connecting pipe (101), and the other end of the wire connecting pipe (101) is electrically connected with the ignition device;

the second contact device (2) comprises a second metal inner core, a spring (201), a supporting sleeve (202), a ceramic insulator (203) and a contact (204), the supporting sleeve (202) is sleeved on the outer layer of the second metal inner core, the spring (201) is sleeved on the outer layer of one end of the supporting sleeve (202), the ceramic insulator (203) is sleeved on the outer layer of the other end of the supporting sleeve (202), one end of the ceramic insulator (203) is connected with the contact (204), and the contact (204) is electrically connected with the ignition electric nozzle;

one end of the high-voltage resistant wire (3) is electrically connected with the first metal inner core of the first contact device (1), and the other end of the high-voltage resistant wire (3) is electrically connected with the second metal inner core of the second contact device (2).

2. The aircraft engine ignition cable of claim 1, characterized in that the high voltage resistant conducting wire (3) is of a multilayer structure, the innermost layer of the high voltage resistant conducting wire (3) is a conductor (301), and an insulator (302), an insulating fiber tape wrapping package (303) and a glass fiber braided layer (304) are sequentially sleeved outside the conductor (301) along the direction from inside to outside.

3. An aircraft engine ignition cable according to claim 1 characterised in that the insulating fibre tape is wrapped (303) as a wrapped layer of glass fibre.

4. An aircraft engine ignition cable according to claim 1, characterised in that the rubber support sleeve (102) is silicone rubber.

5. An aircraft engine ignition cable according to claim 1, characterized in that the aircraft engine ignition cable further comprises a shielding hose assembly (4), the shielding hose assembly (4) being arranged on the outer layer of the high voltage resistant conductor (3).

6. Aero-engine ignition cable according to claim 5, characterized in that the shielding hose assembly (4) comprises a first coupling nut (401), a second coupling nut (402) and a shielding hose, the shielding hose cover is arranged on the outer layer of the high voltage resistant conductor (3), and the first coupling nut (401) and the second coupling nut (402) are arranged at both ends of the shielding hose cover respectively.

7. An aircraft engine ignition cable according to claim 6, characterized in that the first metallic inner core and the high voltage resistant wire (3) of the first contact device (1) are provided with a connection portion, which is externally sheathed by a first connection nut (401).

8. An aircraft engine ignition cable according to claim 6, characterized in that the second metallic inner core and the high voltage resistant conductor (3) of the second contact device (2) are provided with a connection portion which is externally sheathed by a second connection nut (402).

9. An aircraft engine ignition cable according to claim 1, characterized in that the aircraft engine ignition cable further comprises a connector tube assembly (5), the connector tube assembly (5) comprising a first connector (501), a second connector (502) and a straight metal tube (503), the first connector (501) being connected to the second connection nut (402), the second connector (502) being connected to the first connection nut (401).

10. An aircraft engine ignition cable according to claim 9, characterised in that the connection tube assembly (5) is secured to the equipment set by means of a clamp specific to the engine.