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A kind of high thermal conductivity c/sic composite material and preparation method thereof

A composite material and high thermal conductivity technology, which is applied in the field of high thermal conductivity C/SiC composite materials and its preparation, can solve the problems of thermal stress deformation of components, difficulty in maintaining aerodynamic shape of components, and harsh aerodynamic thermal environment.

Active Publication Date: 2022-05-10
湖南东映碳材料科技股份有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The C / SiC composite material prepared in the prior art can meet the short-term use in an aerobic environment above 2000°C, but the aerodynamic and thermal environment is extremely harsh under long-term flight conditions, and the ablation stagnation temperature of the components is very high, and the heat is too late. The transfer leads to a significant increase in the thermal stress deformation of the component, which aggravates the risk of damage to the composite component; at the same time, the long-term ablation intensifies makes it difficult for the component to maintain its aerodynamic shape, and the structural reliability and stability deteriorate accordingly

Method used

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  • A kind of high thermal conductivity c/sic composite material and preparation method thereof
  • A kind of high thermal conductivity c/sic composite material and preparation method thereof
  • A kind of high thermal conductivity c/sic composite material and preparation method thereof

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preparation example Construction

[0021] The invention provides a method for preparing a high thermal conductivity C / SiC composite material, comprising the following steps:

[0022] (1) Deposit and graphitize the carbon cloth and the gaseous carbon source in sequence to obtain a two-dimensional carbon cloth;

[0023] (2) Coating the adhesive and the matrix suspension onto the two-dimensional carbon cloth in sequence, and performing non-melting treatment to obtain a prefabricated body;

[0024] (3) Sintering the preform to obtain a low-density material;

[0025] (4) Densifying the low-density material to obtain the high thermal conductivity C / SiC composite material.

[0026] In the present invention, the specification of the carbon cloth in the step (1) is preferably 1-12K mesophase pitch-based carbon fiber, more preferably 3-10K mesophase pitch-based carbon fiber, more preferably 5-8K mesophase pitch-based carbon fiber The heat treatment temperature of the mesophase pitch-based carbon fiber is preferably 600...

Embodiment 1

[0051] The 1K mesophase pitch-based twill carbon cloth heat-treated at 600°C was placed in a chemical vapor deposition furnace, methane gas was introduced, the deposition pressure was set at 5kPa, the deposition temperature was set at 800°C, the deposition time was 6h, and the gas flow rate was 300mL / min, to obtain a mesophase pitch-based twill carbon cloth containing a pyrolytic carbon interface, and then place it in an induction graphitization furnace under the protection of high-purity argon, and perform graphitization at 2800°C to form a C / C framework to obtain a two-dimensional carbon cloth.

[0052] Weigh 70g of flake graphite with a particle size of 50μm, 65g of SiC powder with a particle size of 100nm, 1800g of zirconia balls with a particle size of 0.2mm, and 900g of zirconia balls with a particle size of 2mm and put them into a ball mill jar for ball milling at 300rpm Ball milling at a rotating speed of 20 hours to obtain a graphite / silicon carbide composite powder,...

Embodiment 2

[0062] Put the 2K mesophase pitch-based non-woven cloth heat-treated at 800°C in a chemical vapor deposition furnace, feed propylene gas, set the deposition pressure to 8kPa, set the deposition temperature to 900°C, set the deposition time to 8h, and the gas flow rate to 400mL / min, to obtain a mesophase pitch-based non-woven fabric containing pyrolytic carbon interface, and then place it in an induction graphitization furnace under the protection of high-purity argon, and perform graphitization treatment at 2900 ° C to form a C / C framework to obtain a two-dimensional carbon cloth.

[0063] Weigh 120g of flake graphite with a particle size of 80μm, 60g of SiC powder with a particle size of 120nm, 3600g of zirconia balls with a particle size of 0.2mm, and 1800g of zirconia balls with a particle size of 2mm and put them into a ball mill jar for ball milling at 400rpm Ball milling at a rotating speed of 24 hours to obtain a graphite / silicon carbide composite powder, which was add...

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Abstract

The invention belongs to the technical field of material preparation. The invention provides a method for preparing a high thermal conductivity C / SiC composite material. After forming a layer of pyrolytic carbon interface on the surface of carbon fiber by depositing a gaseous carbon source, graphitization treatment is performed to obtain a two-dimensional carbon cloth; The surface of the carbon cloth is coated with adhesive and matrix suspension in turn, and the preform is obtained through non-melting treatment; the obtained preform is sintered to obtain a low-density material; after densification of the low-density material, the volume density increases The high thermal conductivity C / SiC composite material is obtained; the present invention improves the thermal conductivity of the composite material through a series of treatment methods. The invention also provides the high thermal conductivity C / SiC composite material obtained by the preparation method, and the thermal conductivity performance of the composite material is improved by adopting the graphene modified matrix and the high thermal conductivity carbon fiber skeleton reinforcement.

Description

technical field [0001] The invention relates to the technical field of material preparation, in particular to a high thermal conductivity C / SiC composite material and a preparation method thereof. Background technique [0002] C / SiC composite materials have excellent characteristics such as high specific strength, high specific modulus, high temperature resistance, oxidation resistance, low thermal expansion coefficient, and wear resistance. The C / SiC composite material prepared in the prior art can meet the short-term use in an aerobic environment above 2000°C, but the aerodynamic and thermal environment is extremely harsh under long-term flight conditions, and the ablation stagnation temperature of the components is very high, and the heat is too late. The transfer leads to a significant increase in the thermal stress deformation of the component, which intensifies the risk of damage to the composite component; at the same time, the long-term ablation makes it difficult fo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/52C04B35/565C04B35/622
CPCC04B35/52C04B35/565C04B35/622C04B2235/5248C04B2235/614
Inventor 叶崇刘玲黄东曾超廖超前伍孝余洋吴晃叶高明张岳峰刘金水
Owner 湖南东映碳材料科技股份有限公司