CN114284778A - Aeroengine ignition cable - Google Patents

Abstract

An aircraft engine ignition cable for connecting an ignition device and an ignition torch, comprising: the high-voltage-resistant wire 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

An aero-engine ignition cable

technical field

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

Background technique

The ignition system, as the key to the energy opening of the aero-engine, is the key component of the engine's starting and restarting. It is mainly composed of the igniter body, the ignition nozzle and the ignition cable. The ignition cable is used to connect the igniter body and the ignition nozzle. It needs to have the ability to withstand short-term high voltage, and ordinary structural cables cannot complete this work. In this case, an ignition cable that can withstand high voltage is urgently needed, which can stably transmit instantaneous high voltage in the ignition system, so that the system can work normally.

SUMMARY OF THE INVENTION

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

The embodiments of this specification provide the following technical solutions:

An aero-engine ignition cable for connecting an ignition device and an ignition nozzle, comprising: a first contact device 1, a second contact device 2 and a high-voltage resistant wire 3;

The first contact device 1 includes a first metal inner core, a wire tube 101 and a rubber support sleeve 102. The wire tube 101 is sleeved on the outer layer of the first metal inner core, and the rubber support sleeve 102 is sleeved on the outer layer of one end of the wire tube 101. The wire tube The other end of 101 is electrically connected to the ignition device;

The second contact device 2 includes 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, and a spring sleeve is sleeved at one end of the support sleeve 202. 201, the outer layer of the other end of the support sleeve 202 is sleeved with a ceramic insulator 203, one end of the ceramic insulator 203 is connected to a contact 204, and the contact 204 is electrically connected to the ignition tip;

One end of the high-voltage conductor 3 is electrically connected to the first metal inner core of the first contact device 1 , and the other end of the high-voltage conductor 3 is electrically connected to the second metal inner core of the second contact device 2 .

Further, the high-voltage resistant wire 3 is a multi-layer structure, and the innermost layer of the high-voltage resistant wire 3 is a conductor 301. In the direction from the inside to the outside, the conductor 301 is sequentially sheathed with an insulator 302, an insulating fiber tape wrapping 303 and glass fibers. Silk braid 304 .

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

Further, the insulating fiber tape wrap 303 is a wrapped glass fiber layer.

Further, the rubber support sleeve 102 is silicon rubber.

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

Further, the shielded hose assembly 4 includes a first connection nut 401, a second connection nut 402 and a shielded hose, the shielded hose is sleeved on the outer layer of the high-voltage resistant wire 3, and the two ends of the shielded hose sleeve are respectively installed The first connection nut 401 and the second connection nut 402 .

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 a 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 also includes a connecting pipe assembly 5, the connecting pipe assembly 5 includes a first joint 501, a second joint 502 and a metal straight pipe 503, the first joint 501 is connected to the second connecting nut 402, and the second joint 502 Connect the first connecting nut 401 .

Further, the connecting pipe assembly 5 is fixed on the set equipment through a special clamp for the engine.

Compared with the prior art, the beneficial effects that can be achieved by the above at least one technical solution adopted in the embodiments of this specification at least include:

According to the docking requirements of the ignition system, a unique first contact device 1 and a second contact device 2 are designed, and a high-voltage resistant wire 3 is developed at the same time, which solves the problem that ordinary structural cables cannot withstand voltages above 10,000V, and improves the accuracy of cables in the ignition system. High voltage withstand capability and transmission capability. A shielded hose assembly 4 is provided on the outer casing of the high-voltage resistant wire 3 . A connecting pipe assembly 5 is added to meet the actual installation and laying requirements of the cable. The ignition cable structure has the characteristics of small size, light weight, strong environmental resistance, high reliability, and high transmission capacity, and can be applied to various aero-engine ignition systems.

Description of drawings

In order to illustrate the technical solutions of the embodiments of the present application more clearly, the following briefly introduces the drawings that are used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.

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

2 is a schematic structural diagram of a first contact device of the present invention;

3 is a schematic structural diagram of the second contact device of the present invention;

Fig. 4 is the structure schematic diagram of the high voltage resistant wire of the present invention;

FIG. 5 is a schematic structural diagram of the connecting pipe assembly of the present invention.

Description of reference numerals: 1. first contact device; 101, wire tube; 102, rubber support sleeve; 2, second contact device; 201, spring; 202, support sleeve; 203, ceramic insulator; 204, contact; 3 301, conductor; 302, insulator; 303, insulating fiber tape wrapping; 304, glass fiber braid; 4, shielded hose assembly; 401, first connection nut; 402, second connection screw cap; 5. connecting pipe assembly; 501, first joint; 502, second joint; 503, metal straight pipe.

Detailed ways

The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

The embodiments of the present application are described below through specific specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, but not all of the embodiments. The present application can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other under the condition of no conflict. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present application.

To illustrate, various aspects of embodiments within the scope of the appended claims are described below. 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 illustrative only. Based on this application, one skilled in the art should appreciate that an 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 may be practiced using any of the numbers and aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.

It should also be noted that the drawings provided in the following embodiments only illustrate the basic concept of the present application in a schematic way, and the drawings only show the components related to the present application rather than the number, shape and the number of components in actual implementation. For dimension drawing, the type, quantity and proportion of each component can be changed at will in actual implementation, and the component layout may also be more complicated.

Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, one skilled in the art will understand that the described 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.

One embodiment of the present invention refers to FIGS. 1 to 5 .

FIG. 1 is a schematic diagram of the overall structure of the ignition cable of this embodiment.

FIG. 2 is a schematic structural diagram of the first contact device in this embodiment.

FIG. 3 is a schematic structural diagram of the second contact device in this embodiment.

FIG. 4 is a schematic diagram of the structure of the high-voltage-resistant wire of the present embodiment.

FIG. 5 is a schematic structural diagram of the connecting pipe assembly of the present embodiment.

As shown in FIG. 2 , the first contact device 1 adopts a metal inner core, and a wire tube 101 is sleeved outside the metal inner core. The outside of the wiring tube 101 is equipped with a rubber support sleeve 102 made of 6144 silicone rubber. After welding the metal core and the high-voltage wire 3, the solder fills 2-3mm. When in use, the first connecting nut 401 on the shielding hose assembly 4 is used to connect with the ignition device, and the rubber support sleeve 102 ensures reliable connection.

In this embodiment, the shielding hose of the shielding hose assembly 4 is braided with 1Cr18Ni9Ti stainless steel wire.

As shown in FIG. 3 , the second contact device 2 adopts a metal inner core, and a support sleeve 202 made of brass is sleeved outside the metal inner core. The outer end of the support sleeve 202 is sleeved with a ceramic insulator 203, the ceramic insulator 203 is a ceramic connecting sleeve, and the ceramic connecting sleeve is a horizontal trumpet-shaped structure, one end is wide and the other end is narrow. After the ceramic connecting sleeve is butted with the ignition nozzle, a ceramic creeping nozzle can be formed. The ceramic creeping nozzle is a nozzle that discharges along the surface of the ceramic insulator, with high energy, high ignition reliability and long service life. The ceramic creeping nozzle adopts a recessed recessed pole structure, which is beneficial to reduce the temperature of the nozzle end and prolong the service life of the nozzle. The breakdown voltage of this type of nozzle is high, and the breakdown voltage is generally 5KV to 8KV.

The other end of the support sleeve 202 is equipped with the structure of the spring 201. When welding with the high-voltage wire 3, the high-voltage wire 3 needs to be pulled out from the second contact device 2 and broken up for welding. After welding, grinding treatment is performed to ensure that the welding end surface is flat and smooth. It is smooth and connected to the ignition device through the second connecting nut 402 on the shielding hose assembly 4 during use, and the spring 201 ensures reliable butt locking.

As shown in Figure 4, the thickness of the insulating layer of the normal wire is 0.1-0.2mm, and the sintering process is used. While increasing the thickness of the insulator 302, the high-voltage wire 3 adopts the wrapping form instead of the sintering process, and an insulating fiber tape wrapping 303 layer is added outside the insulator 302, which improves the high-voltage resistance performance of the high-voltage wire 3 compared with the traditional wire. . At the same time, the outermost layer of the high-voltage resistant wire 3 is sheathed with a glass fiber braided layer 304 . The above structure of the high-voltage-resistant wire 3 enables it to withstand the high-frequency spark test of 13kV and the ultimate withstand voltage test of 25kV, and the operating temperature can meet the requirements of -60°C to 250°C.

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

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

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

The ignition cable is composed of a high-voltage resistant wire 3 , a first contact device 1 , a second contact device 2 , a shielded hose assembly 4 , and a connecting pipe assembly 5 . After the high-voltage-resistant wire 3 is welded with the first contact device 1 and the second contact device 2 at high temperature, the shielded hose assembly 4 and the connecting tube assembly 5 are sheathed outside, so that the ignition cable transmits high voltage and has resistance to salt spray, damp heat, The ability of the environment such as mold. The ignition cable structure is applied to the engine ignition system to transmit the instantaneous high voltage generated by the ignition device to the ignition nozzle to ignite the mixed gas in the combustion chamber of the engine. It has the advantages of light weight, high reliability and strong environmental resistance, and meets the needs of aviation power .

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

Table 1

In other embodiments, the insulator 302 may also use a polyperfluoroethylene propylene film.

Each embodiment in this specification is described in a progressive manner, and the same and similar parts between the various embodiments may be referred to each other, and each embodiment focuses on describing the differences from other embodiments. In particular, for the method embodiments described later, since they correspond to the system, the description is relatively simple, and reference may be made to the partial descriptions of the system embodiments for related parts.

The above are only specific embodiments of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art who is familiar with the technical field disclosed in the present application can easily think of changes or substitutions. All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (11)

1. an aero-engine ignition cable for connecting an ignition device and an ignition nozzle, characterized in that it 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 wiring tube (101) and a rubber support sleeve (102), the wiring tube (101) is sleeved on the outer layer of the first metal inner core, and one end of the wiring tube (101) is sleeved A rubber support sleeve (102) is sleeved on the outer layer of the wire tube, and the other end of the wiring tube (101) is electrically connected with the ignition device; The second contact device (2) includes a second metal inner core, a spring (201), a support sleeve (202), a ceramic insulator (203) and a contact (204), the second metal inner core outer layer sleeved with a support sleeve (202), one end of the support sleeve (202) is sleeved with a spring (201), the other end of the support sleeve (202) is sleeved with a ceramic insulator (203), and one end of the ceramic insulator (203) is connected to the contact (203). 204), the contact (204) is electrically connected to the ignition tip; One end of the high-voltage resistant wire (3) is electrically connected to 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 to the second metal of the second contact device (2). Inner core. 2. An aero-engine ignition cable according to claim 1, characterized in that the high-voltage resistant wire (3) is of a multi-layer structure, and the innermost layer of the high-voltage resistant wire (3) is a conductor (301), which extends from the inside to the In the outward direction, the conductor (301) is sheathed with an insulator (302), an insulating fiber tape wrap (303) and a glass fiber braided layer (304) in sequence. 3. An aero-engine ignition cable according to claim 2, characterized in that, the insulator (302) is one or more combinations of polytetrafluoroethylene film or polyperfluoroethylene propylene film. 4. An aero-engine ignition cable according to claim 2, characterized in that the insulating fiber tape wrap (303) is a glass fiber layer wrapped by wrapping. 5. An aero-engine ignition cable according to claim 1, characterized in that, the rubber support sleeve (102) is silicone rubber. 6. An aero-engine ignition cable according to claim 1, characterized in that, the aircraft-engine ignition cable further comprises a shielded hose assembly (4), and the shielded hose assembly (4) is arranged on the side of the high-voltage resistant wire (3). outer layer. 7. An aero-engine ignition cable according to claim 6, characterized in that the shielded hose assembly (4) comprises a first connection nut (401), a second connection nut (402) and a shielded hose, The shielding hose is sleeved on the outer layer of the high-voltage-resistant wire (3), and both ends of the shielding hose sleeve are respectively provided with a first connection nut (401) and a second connection nut (402). 8. An aero-engine ignition cable according to claim 7, characterized in that, the first metal inner core of the first contact device (1) and the high-voltage resistant wire (3) are provided with connecting parts, and the connection A first connecting nut (401) is sleeved on the outer layer. 9. An aero-engine ignition cable according to claim 7, characterized in that, 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 connecting A second connection nut (402) is sleeved on the outer layer. 10. An aero-engine ignition cable according to claim 1, the aircraft-engine ignition cable further comprising a connecting pipe assembly (5), the connecting pipe assembly (5) comprising a first joint (501), a second joint (502) and The metal straight pipe (503), the first joint (501) is connected to the second connection nut (402), and the second joint (502) is connected to the first connection nut (401). 11. An aero-engine ignition cable according to claim 10, wherein the connecting pipe assembly (5) is fixed on the set equipment through a special clamp for the engine.

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