Ignition cable structure of aero-engine

Abstract

The invention discloses an ignition cable structure of an aero-engine. The ignition cable structure is characterized by comprising an aluminum alloy bent pipe and connecting joints connected with the two ends of the aluminum alloy bent pipe through shielding hose assemblies; the shielding hose assembly comprises a shielding hose and a wave-proof sleeve which are matched in a sleeved mode and further comprises a connecting cylinder, one end of the connecting cylinder is provided with a concentric-square-shaped groove matched with the shielding hose and the wave-proof sleeve, and the other end of the connecting cylinder is matched with the connecting joint and the connecting nut. The connecting nut is in threaded fit with the aluminum alloy bent pipe; the connecting joint comprises a main screw cap and a ceramic connecting sleeve, and the main screw cap is clamped and matched with the connecting cylinder; the lower end of the ceramic connecting sleeve is matched with the connecting cylinder, the upper end is provided with a metal inner core, and a wire penetrates through the ceramic connecting sleeve and a center hole of the metal inner core and then is welded to the metal inner core. The structure has the advantages of being round and neat in appearance, good in electromagnetic shielding performance, high in environment resistance, high in reliability and the like, and can be popularized to various aero-engine ignition systems.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft engine cables, and in particular relates to an aircraft engine ignition cable structure. Background Art

[0002] As the key to opening the energy of aircraft engines, the ignition system is a key component for starting and restarting the engine. As the requirements for the use environment, anti-electromagnetic interference capability and installation protection of the engine continue to increase. In this case, there is an urgent need for a high-reliability ignition cable that can stably transmit instantaneous high voltage in the ignition system to ensure the normal operation of the system while meeting the requirements of anti-electromagnetic interference, anti-vibration and other environmental requirements of aircraft engines, and can be quickly installed and laid in complex three-dimensional space locations. Summary of the invention

[0003] The purpose of the present invention is to provide an aircraft engine ignition cable structure to solve the problems in the prior art.

[0004] The present invention is realized by the following technical scheme: an aircraft engine ignition cable structure, characterized in that it comprises an aluminum alloy bent pipe and a connecting joint connected to both ends of the aluminum alloy bent pipe through a shielded hose assembly; The shielding hose assembly includes a shielding hose and a wave-proof sleeve that are sleeved together, and also includes a connecting tube, one end of which is provided with a circular groove that matches the shielding hose and the wave-proof sleeve, and the other end of the connecting tube is matched with a connecting joint and a connecting nut respectively; the connecting nut is matched with the aluminum alloy elbow thread; The connecting joint includes a main nut and a ceramic connecting sleeve, the main nut is snap-fitted with the connecting tube; the lower end of the ceramic connecting sleeve is matched with the connecting tube, and the upper end is provided with a metal inner core, and the wire passes through the ceramic connecting sleeve and the center hole of the metal inner core and is welded to the metal inner core.

[0005] Furthermore: a spring is arranged in the inner cavity of the connecting tube located inside the main nut, the lower end of the spring cooperates with the step of the inner cavity of the connecting tube, and the upper end cooperates with the gasket; the upper end of the gasket is limited by a limiting ring, and the limiting ring is snap-fitted or threadedly fitted with the connecting tube.

[0006] Furthermore, the ends of the shielding hose and the wave-proof sleeve are inserted into the round-shaped groove and are respectively welded to the round-shaped groove.

[0007] Further: the connecting nut is matched with the threaded joints welded at both ends of the aluminum alloy.

[0008] Further: the wire is a high voltage resistant wire.

[0009] The advantages of the present invention are: in the structure of the present invention, the aluminum alloy elbow can be designed with a specific three-dimensional elbow shape according to the docking requirements of the ignition system, meeting the actual complex three-dimensional space installation and laying requirements of the cable. At the same time, the present structure greatly guarantees the ability of the cable to withstand high voltage in the ignition system and stably transmit high voltage signals. In addition, the present structure also has the characteristics of rounded shape, good electromagnetic shielding, strong environmental resistance, high reliability, etc., and can be extended to a variety of aircraft engine ignition systems. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 This is a schematic diagram of the structure of a high voltage ignition cable; Figure 2 It is a structural schematic diagram of a high-voltage ignition cable shielding hose assembly; Figure 3 This is a schematic diagram of the structure of the three-dimensional aluminum alloy bent tube assembly for high-voltage ignition cables.

[0011] Figure 4 This is a schematic diagram of the termination structure of the high-voltage ignition cable.

[0012] Explanation of the numbers in the figure: 1 is the connection joint, 2 is the shielded hose assembly, and 3 is the aluminum alloy elbow; 11 is a main nut, 12 is a ceramic connecting sleeve, 13 is a metal inner core, 14 is a spring, 15 is a gasket, and 16 is a limit ring; 21 is a shielding hose, 22 is a wave-proof sleeve, 23 is a connecting tube, 24 is a connecting nut, and 25 is a circular groove. DETAILED DESCRIPTION

[0013] The following will combine the embodiments of this patent to clearly and completely describe the high-voltage ignition cable structure in the form of drawings. The high-voltage ignition cable structure shown in the drawings is only one of the embodiments of this patent, not all embodiments. All embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this patent.

[0014] Reference Figure 1-4The present invention discloses an aircraft engine ignition cable structure, comprising an aluminum alloy bent pipe 3 and a connecting joint 1 connected to both ends of the aluminum alloy bent pipe through a shielded hose assembly 2; the shielded hose assembly 2 comprises a shielded hose 21 and a wave-proof sleeve 22 that are sleeved together, and also comprises a connecting tube 23, one end of the connecting tube 23 is provided with a circular groove 25 that matches the shielded hose 21 and the wave-proof sleeve 22, and the other end of the connecting tube 23 matches the connecting joint 1 and the connecting nut 24 respectively; the connecting nut 24 is threadedly matched with the aluminum alloy bent pipe 3; the connecting joint 1 comprises a main nut 11 and a ceramic connecting sleeve 12, and the main nut 11 is snap-fitted with the connecting tube 23; the lower end of the ceramic connecting sleeve 12 matches the connecting tube 23, and the upper end is provided with a metal inner core 13, and the wire passes through the ceramic connecting sleeve 12 and the center hole of the metal inner core 13 and is welded and connected to the metal inner core 13.

[0015] Preferably: a spring 14 is provided in the inner cavity of the connecting tube 23 located inside the main nut 11, the lower end of the spring 14 cooperates with the step of the inner cavity of the connecting tube 23, and the upper end cooperates with the gasket 15; the upper end of the gasket 15 is limited by a limiting ring 16, and the limiting ring 16 is snap-fitted or threadedly fitted with the connecting tube 23.

[0016] Preferably, the ends of the shielding hose 21 and the wave-proof sleeve 22 are inserted into the meandering groove 25 and are respectively connected to the meandering groove 25 by welding.

[0017] Preferably, the connecting nut 24 cooperates with threaded joints welded at both ends of the aluminum alloy.

[0018] Preferably, the conductor is a high voltage resistant conductor.

[0019] The present invention is further described below by way of examples.

[0020] Embodiment: This embodiment discloses an aircraft engine ignition cable structure. Figure 1 , which is a schematic diagram of the high-voltage ignition cable structure. In this structure, the connector + high-voltage wire + shielded hose assembly + aluminum alloy three-dimensional bent pipe assembly. The aluminum alloy three-dimensional bent pipe assembly is the main structure. The aluminum alloy straight pipe is bent according to the coordinates required by the three-dimensional laying space of the engine, and threaded joints are welded at both ends to form an aluminum alloy three-dimensional bent pipe assembly, which is the main protective support structure of the wire harness. The two ends of the aluminum alloy three-dimensional bent pipe assembly are respectively connected to high-strength and high-density shielded hose assemblies to establish an overall protective structure for the wire harness. The other end of the shielded hose assembly is connected to a fixed contact device, and the high-voltage wire is protected in the overall structure to form a high-voltage ignition cable.

[0021] Reference Figure 2, is a schematic diagram of the appearance of the high-voltage ignition cable shielded hose assembly. The shielded hose assembly has two intermediate shielding layers, the inner sealed metal corrugated hose, which plays a role of high shielding and serves as a supporting structure, and the outer layer is covered with a high-strength and high-density wave-proof sleeve, which is welded to the return groove of the connecting tube at both ends by high-temperature brazing. A main nut is installed at one end of the shielding protective layer, which is connected to the ignition nozzle connection end or the ignition device connection end, and the other end is connected to the threaded joint of the aluminum alloy three-dimensional elbow assembly through a connecting nut.

[0022] Reference Figure 3 , which is a schematic diagram of the appearance of the three-dimensional aluminum alloy elbow assembly for high-voltage ignition cables. The aluminum alloy three-dimensional elbow assembly is the main body of the protective structure. The aluminum alloy straight pipe is bent according to the coordinates required for the three-dimensional laying space of the engine to form an aluminum alloy elbow. Threaded joints are welded at both ends to form an aluminum alloy three-dimensional elbow assembly, which is the main protective support structure of the wire harness.

[0023] Reference Figure 4 , which is a schematic diagram of the appearance of the high-voltage ignition cable termination structure. The connection joint uses a hollow metal core to weld the wire core. The ceramic connection sleeve not only serves as a supporting structure for the metal core, but also ensures the insulation performance of the high-voltage wire. The end of the ceramic sleeve is limited on the component gasket, which is fixed by a limit ring. There is a spring underneath, and the elastic buffer structure design can ensure a reliable connection. The metal structural parts are matched and connected by laser welding. The main nut is connected to the ignition nozzle or ignition device interface.

[0024] This cable structure is used in 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 engine combustion chamber. It has the advantages of adapting to laying in complex three-dimensional space environments, high mechanical strength and reliability, and strong resistance to comprehensive environments, meeting the needs of aircraft engine use.

Claims

1. An aircraft engine ignition cable structure, characterized in that: It comprises an aluminum alloy bent pipe (3) and a connecting joint (1) connected to both ends of the aluminum alloy bent pipe via a shielded hose assembly (2); The shielding hose assembly (2) comprises a shielding hose (21) and a wave-proof sleeve (22) that are sleeved together, and also comprises a connecting tube (23), one end of the connecting tube (23) is provided with a circular groove (25) that matches the shielding hose (21) and the wave-proof sleeve (22), and the other end of the connecting tube (23) matches the connecting joint (1) and the connecting nut (24) respectively; the connecting nut (24) is threadedly matched with the aluminum alloy elbow (3); The connecting joint (1) comprises a main nut (11) and a ceramic connecting sleeve (12), wherein the main nut (11) is snap-fitted with the connecting tube (23); the lower end of the ceramic connecting sleeve (12) is matched with the connecting tube (23), and the upper end is provided with a metal inner core (13); the wire passes through the central holes of the ceramic connecting sleeve (12) and the metal inner core (13) and is then welded to the metal inner core (13).

2. The aircraft engine ignition cable structure according to claim 1, characterized in that: A spring (14) is arranged in the inner cavity of the connecting tube (23) located inside the main nut (11); the lower end of the spring (14) cooperates with the step of the inner cavity of the connecting tube (23), and the upper end cooperates with the gasket (15); the upper end of the gasket (15) is limited by a limiting ring (16), and the limiting ring (16) and the connecting tube (23) are engaged by snapping and riveting.

3. The aircraft engine ignition cable structure according to claim 1, characterized in that: The ends of the shielding hose (21) and the wave-proof sleeve (22) are inserted into the round-shaped groove (25) and are respectively connected to the round-shaped groove (25) by welding.

4. The aircraft engine ignition cable structure according to claim 1, characterized in that: The connecting nut (24) cooperates with the threaded joints welded at both ends of the aluminum alloy.

5. The aircraft engine ignition cable structure according to claim 1, characterized in that: The conductor is a high voltage resistant conductor.

Images