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Carbon fiber reinforced ultra-temperature vacuum insulated composite material

A composite material and vacuum insulation technology, applied in the field of ultra-high temperature vacuum insulation composite materials, can solve problems such as unsatisfactory and low thermal conductivity, achieve low thermal conductivity, high strength, and realize the effect of structural and functional integration

Inactive Publication Date: 2017-11-17
SUZHOU HONGJIU AVIATION THERMAL MATERIALS TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

From the above data, it can be seen that a solid composite material cannot meet the requirements of extremely low thermal conductivity, and it is extremely urgent to invent a material with extremely low thermal conductivity and high temperature resistance.

Method used

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  • Carbon fiber reinforced ultra-temperature vacuum insulated composite material

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0010] refer to figure 1 , a carbon fiber-reinforced ultra-high temperature vacuum insulation composite material consisting of a sealed carbon fiber-reinforced ceramic matrix composite shell and an internal cavity, where [10] is the ceramic matrix composite shell and [20] is the internal cavity cavity. The ceramic matrix composite material shell [10] is composed of carbon fiber reinforced C / C composite material without penetrating pores, in which C fiber accounts for 50% of the volume fraction of the composite material shell, and its inner surface is coated with silicon carbide , the silicon carbide coating penetrates into the interior of the C / C composite material in a gradient distribution, prepares a silicon carbide coating on its outer surface, seals the C / C surface, and the silicon carbide coating penetrates into the interior of the C / C composite material, also presents a gradient distributed. The pressure of the gas in the inner cavity [20] is less than 1000Pa.

Embodiment 2

[0012] The main difference between the second embodiment and the first embodiment is that a layer of zirconium carbide is prepared on the outer surface of the composite shell in the second embodiment. refer to figure 1 , a carbon fiber-reinforced ultra-high temperature vacuum insulation composite material consisting of a sealed carbon fiber-reinforced ceramic matrix composite shell and an internal cavity, where [10] is the ceramic matrix composite shell and [20] is the internal cavity cavity. The ceramic matrix composite material shell [10] is composed of carbon fiber reinforced C / C composite material without penetrating pores. The volume fraction of C fiber in the composite material shell is 60%, and its inner surface is coated with silicon carbide. , the silicon carbide coating penetrates into the interior of the C / C composite material in a gradient distribution, prepares a zirconium carbide coating on its outer surface, seals the C / C surface, and the zirconium carbide coat...

Embodiment 3

[0014] The main difference between the third embodiment and the first embodiment is that in the third embodiment, a layer of silicon carbide is first prepared on the outer surface of the composite shell, and then a layer of zirconium carbide is prepared on the silicon carbide layer. refer to figure 1 , a carbon fiber-reinforced ultra-high temperature vacuum insulation composite material consisting of a sealed carbon fiber-reinforced ceramic matrix composite shell and an internal cavity, where [10] is the ceramic matrix composite shell and [20] is the internal cavity cavity. The ceramic matrix composite material shell [10] is composed of carbon fiber reinforced C / C composite material without penetrating pores, in which C fiber accounts for 50% of the volume fraction of the composite material shell, and its inner surface is coated with silicon carbide , the silicon carbide coating penetrates into the interior of the C / C composite material in a gradient distribution, prepares a ...

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Abstract

The invention discloses a carbon fiber reinforced ultra-temperature vacuum insulated composite material. The carbon fiber reinforced ultra-temperature vacuum insulated composite material is characterized by comprising a seal carbon fiber reinforced ceramic-based composite shell and an inner cavity. The composite shell is composed of a carbon fiber reinforced C / C composite material without through air holes, and a silicon carbide coating is arranged on the inner surface of the shell, a silicon carbide coating and a zirconium carbide coating are arranged on the outer surface, and the pressure of air in the inner cavity is lower than 1000 Pa. The material can be used in the environment with the temperature of 1500 DEG C or above, has an extremely low thermal conductivity coefficient and is high in strength and capable of being used as a structural material, and the structure and function integration is achieved.

Description

technical field [0001] The invention relates to a vacuum thermal insulation composite material, in particular to a carbon fiber reinforced ultra-high temperature vacuum thermal insulation composite material. Background technique [0002] In the development of energy technology, the 20th century is a century of full development of thermal insulation technology. The barrier film used in vacuum insulation panels in the traditional sense is generally composed of a nylon protective layer, an aluminum foil layer and a polyethylene heat-sealing layer. Using the principle of vacuum insulation, the vacuum insulation panels produced have extremely low thermal conductivity, but this The material can only be used in a low temperature environment and cannot meet the needs in a high temperature environment. Carbon-based composites and ceramic-based composites have the characteristics of high strength and high temperature resistance. However, these materials have high thermal conductivity...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/83C04B35/84C04B35/52C04B41/86C04B41/89
CPCC04B35/52C04B35/83C04B41/009C04B41/5059C04B41/52C04B41/86C04B41/89C04B41/5057
Inventor 陈照峰汪洋
Owner SUZHOU HONGJIU AVIATION THERMAL MATERIALS TECH CO LTD
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