Composite insulating high-temperature-resistant cable for aero-engine

Abstract

The utility model discloses a composite insulating high-temperature-resistant cable for an aero-engine, which comprises an insulating wire core, a nickel-plated copper wire shielding layer is wrapped on the circumferential outer side of the insulating wire core, and a quartz fiber woven sheath is wrapped on the circumferential outer side of the nickel-plated copper wire shielding layer; the insulating wire core comprises a conductor wire core, an inner insulating layer wraps the outer side of the conductor wire core in the circumferential direction, an outer insulating layer wraps the outer side of the inner insulating layer in the circumferential direction, and the outer insulating layer is a quartz fiber temperature-resistant layer. The composite insulating high-temperature-resistant cable for the aero-engine is suitable for application occasions where the aero-engine can resist the temperature of 400 DEG C for a long time, and the adopted materials are high-temperature-resistant, fire-resistant and excellent in insulating performance. The selection of the insulating material and the design of each structure wrapping in the application play a crucial role in realizing the application of the cable for resisting the temperature of 400 DEG C.

Description

Technical Field

[0001] This utility model relates to the field of cable technology, and in particular to a composite insulated high-temperature resistant cable for aero-engines. Background Technology

[0002] Cables used in the general aviation field need to be lightweight and resistant to high temperatures (typically 400°C). However, most cables on the market do not meet these requirements. Commonly used cables typically use fluoroplastics or polytetrafluoroethylene (PTFE) resin. However, high-temperature resistant fluoroplastics are no longer suitable for applications at 400°C. PTFE resin, known as the "king of plastics," has a maximum continuous operating temperature of 260°C and is in a molten state at 312°C. Due to the working environment requirements of aircraft cables, they must possess characteristics such as high operating temperature, lightweight, and excellent electrical performance.

[0003] For example, in the design of patent number 201920020365.9 (patent name: a moisture-proof and high-temperature resistant cable), ceramicized silicone rubber is selected, and the temperature resistance of ceramicized silicone rubber is around 200°C. However, the insulation material used in this invention has a temperature resistance of 500-600°C, which is fundamentally different from mica tape and glass fiber.

[0004] In the design of patent number 201920647469.2 (patent title: A Fire-Resistant and High-Temperature Cable), although mica is used for the fire-resistant insulation layer and the wrapping layer, the main insulation material of this cable limits the long-term operating temperature of the invention. Only in the case of flame, the ceramicization of the insulation material gives it short-term working characteristics. In contrast, the long-term operating temperature of this invention is 400°C, and the temperature resistance of the material reaches about 500 to 600 degrees Celsius. Therefore, this invention is fundamentally different from it.

[0005] Therefore, this application proposes a composite insulated high-temperature resistant cable for aircraft engines, which can operate for a long time in a high-temperature environment (400℃). Utility Model Content

[0006] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide a composite insulated high-temperature resistant cable for aero-engines.

[0007] This utility model provides a composite insulated high-temperature resistant cable for aircraft engines, comprising an insulated core, wherein a nickel-plated copper wire shielding layer is wrapped around the circumferential outer side of the insulated core, and a quartz fiber braided sheath is wrapped around the circumferential outer side of the nickel-plated copper wire shielding layer; the insulated core includes a conductor core, wherein an inner insulation layer is wrapped around the circumferential outer side of the conductor core, and an outer insulation layer, wherein the outer insulation layer is a quartz fiber heat-resistant layer, the outer insulation layer being a quartz fiber heat-resistant layer.

[0008] Furthermore, the conductor core is a nickel-plated copper conductor core.

[0009] Furthermore, the inner insulation layer includes a first mica heat-resistant layer disposed on the circumferential outer side of the conductor core, and a second mica heat-resistant layer is disposed on the circumferential outer side of the first mica heat-resistant layer.

[0010] Compared with the prior art, the beneficial effects of this utility model are:

[0011] This utility model discloses a composite insulated high-temperature resistant cable for aero-engines, suitable for long-term temperature resistance applications of 400℃ in aero-engines. All materials used are high-temperature resistant, fire-resistant, and possess excellent insulation properties. The selection of insulation materials and the design of each structural element play a crucial role in achieving the 400℃ temperature resistance of the cable. Specifically, the conductor core uses nickel-plated copper wire stranded conductors, which have high operating temperatures and are not easily oxidized. The inner insulation layer uses a double-layer mica tape wrapping structure. The outer insulation layer is made of quartz fiber glass fiber braided, with a higher SiO2 content (greater than 99%), making it less flammable, with a higher temperature resistance rating, softening only at 1700℃, a long-term operating temperature of around 1000℃, and a volume resistivity reaching 10. 20 Ω·cm is an excellent refractory, high-temperature resistant, flame-retardant, and insulating material.

[0012] It should be understood that the content described in the utility model description section is not intended to limit the key or important features of the embodiments of this utility model, nor is it intended to limit the scope of this utility model.

[0013] Other features of this invention will become readily apparent from the following description. Attached Figure Description

[0014] Other features, objects, and advantages of this invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0015] Figure 1 A schematic diagram of the structure of a composite insulated high-temperature resistant cable for aero-engines provided for an embodiment of this utility model;

[0016] Figure 2 This is a schematic diagram of the structure of an insulated wire core;

[0017] The diagram is labeled as follows: 1. Insulated wire core; 11. Nickel-plated copper conductor core; 12. First mica heat-resistant layer; 13. Second mica heat-resistant layer; 14. Quartz fiber heat-resistant layer; 2. Nickel-plated copper wire shielding layer; 3. Quartz fiber braided sheath. Detailed Implementation

[0018] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings.

[0019] It should be noted that, where there is no conflict, the embodiments and features in the embodiments of this utility model can be combined with each other. The present utility model will now be described in detail with reference to the accompanying drawings and embodiments.

[0020] Please refer to Figures 1-2 The present invention provides a composite insulated high-temperature resistant cable for aircraft engines, including an insulated core 1, a nickel-plated copper wire shielding layer 2 wrapped around the circumferential outer side of the insulated core 1, and a quartz fiber braided sheath 3 wrapped around the circumferential outer side of the nickel-plated copper wire shielding layer 2.

[0021] The quartz fiber braided sheath material 3 is made of quartz fiber braiding. Since the long-term operating temperature is 400℃, ordinary high-temperature resistant fluoroplastics can no longer meet the requirements of actual aerospace applications. Quartz fiber has a long-term operating temperature of 1000℃ and excellent insulation properties, with a volume resistivity of up to 10. 20 Ω·cm.

[0022] The insulated core 1 includes a conductor core, an inner insulation layer is wrapped around the outer periphery of the conductor core, and an outer insulation layer is wrapped around the outer periphery of the inner insulation layer. The outer insulation layer is a quartz fiber heat-resistant layer 14.

[0023] In a preferred embodiment, the conductor core is a nickel-plated copper conductor core 11.

[0024] Because shielding requires nickel-plated copper wire that can withstand temperatures up to 400℃ for a long time, and nickel-plated copper monofilaments are relatively hard, 0.10mm nickel-plated copper monofilaments are prone to breakage when braiding with 24 spindles, and are prone to stacking when multiple strands are bundled together, the design uses 24 spindles of nickel-plated copper with a single wire diameter of 0.12mm, and the braiding angle is designed to be between 50° and 60°.

[0025] The outer insulation layer is made of woven quartz fiber. Quartz fiber differs from ordinary glass fiber. Ordinary alkali-free glass fiber has an SiO2 content of about 55%, while quartz fiber has a higher SiO2 content, exceeding 99%. It is less flammable, has a higher temperature resistance, softens only at 1700℃, has a long-term operating temperature of around 1000℃, and a volume resistivity of up to 10. 20 Ω·cm is an excellent fire-resistant, high-temperature resistant, flame-retardant, and insulating material. When weaving quartz fiber, the weaving angle must be designed to be greater than 55°, otherwise it is very easy for the wheels to fall off. The weaving density should be designed to be above 98% to avoid gaps that are visible to the naked eye.

[0026] In a preferred embodiment, the inner insulation layer includes a first mica heat-resistant layer 12 disposed on the circumferential outer side of the conductor core, and a second mica heat-resistant layer 13 disposed on the circumferential outer side of the first mica heat-resistant layer 12.

[0027] Specifically, the inner insulation layer in this application adopts a double-layer mica tape wrapping structure. The mica tape is made by attaching mica sheets to fiberglass tape with silicone. Therefore, it is relatively hard and prone to shedding during wrapping. It has a small bending radius and the wrapping angle should be controlled between 45° and 60°. This wrapping angle can also increase the lateral wrapping tension and increase the tightness of the wrapping.

[0028] This application relates to a composite insulated high-temperature resistant cable for aero-engines, suitable for long-term temperature resistance applications of 400℃ in aero-engines. The materials used in this application are all high-temperature resistant, fire resistant, and have excellent insulation properties. The conductor is a nickel-plated copper stranded conductor, the inner insulation layer adopts a double-layer mica tape wrapping structure, and the outer insulation layer adopts quartz fiber braiding. The selection of insulation materials, structural design, and determination of processing parameters play a crucial role in achieving long-term temperature resistance of 400℃ in this application.

[0029] In the description of this specification, the terms "connection," "installation," and "fixing," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0030] In the description of this specification, the terms "one embodiment," "some embodiments," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0031] The above are merely preferred embodiments of this application and are not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A composite insulated high-temperature resistant cable for aircraft engines, characterized in that, The device includes an insulated wire core, the outer periphery of which is covered with a nickel-plated copper wire shielding layer, and the outer periphery of which is covered with a quartz fiber braided sheath; the insulated wire core includes a conductor wire core, the outer periphery of which is covered with an inner insulation layer, and the outer periphery of which is covered with an outer insulation layer, which is a quartz fiber heat-resistant layer.

2. The composite insulated high-temperature resistant cable for aero-engines according to claim 1, characterized in that, The conductor core is a nickel-plated copper conductor core.

3. The composite insulated high-temperature resistant cable for aero-engines according to claim 1, characterized in that, The inner insulation layer includes a first mica heat-resistant layer disposed on the circumferential outer side of the conductor core, and a second mica heat-resistant layer is disposed on the circumferential outer side of the first mica heat-resistant layer.

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