Carbon fiber reinforced carbon-tantalum hafnium carbide solid solution composite material and preparation method thereof

A composite material and carbon fiber prefabricated technology, applied in the field of C/C composite material preparation, can solve the problems of low content of antioxidant components, poor thermal matching, uneven distribution, etc., to achieve enhanced antioxidant performance, excellent oxidation resistance, The effect of high TaxHfC content

Active Publication Date: 2020-01-07
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The method of the invention solves the problems of low content of anti-oxidation components, uneven distribution and poor thermal matching in the matrix of the existing modified C / C composite material, and simultaneously improves the high-temperature oxidation resistance and mechanical properties of the C / C composite material

Method used

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  • Carbon fiber reinforced carbon-tantalum hafnium carbide solid solution composite material and preparation method thereof
  • Carbon fiber reinforced carbon-tantalum hafnium carbide solid solution composite material and preparation method thereof
  • Carbon fiber reinforced carbon-tantalum hafnium carbide solid solution composite material and preparation method thereof

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preparation example Construction

[0032] The present invention provides a C f / C-Ta x The preparation method of HfC composite material, the method includes the following steps:

[0033] (1) Impregnating carbon fiber preforms deposited with pyrolytic carbon interface layer with phenolic resin (C f Preform), and then sequentially subject the impregnated carbon fiber preform to the steps of curing and pyrolysis;

[0034] (2) Repeat step (1) 2 to 5 times (for example, 2, 3, 4, or 5 times) to prepare a composite material containing a C matrix (carbon matrix);

[0035] (3) Immerse the composite material containing the C matrix with a hafnium tantalum carbon precursor solution, and then sequentially subject the impregnated composite material containing the C matrix to the steps of solidification and high temperature cracking; the hafnium tantalum carbon precursor solution From the molar ratio of 1:(2~4):(3~5) (e.g. 1:2:3, 1:2:4, 1:2:5, 1:3:3, 1:3:4, 1 :3:5, 1:4:3, 1:4:4 or 1:4:5) hafnium tantalum precursor, phenolic resin ...

Embodiment approach

[0050] According to some specific embodiments, the C f / C-Ta x The preparation method of HfC composite material includes the following steps:

[0051] ① Preparation of C matrix: The carbon fiber preform deposited with the pyrolytic carbon interface layer is completely immersed in phenolic resin, and immersed in an environment with a vacuum of 5-100kPa for 1 to 3 hours, and then at 150-220°C and a pressure of 3~ Cross-linking and curing in a 10MPa pressure tank for 5-10 hours; the cured preform is placed in a cracking furnace and cracked at a high temperature of 700-1000°C for 2-5 hours. Repeat the foregoing process 2 to 5 times to make the density of the composite material containing the C matrix 1.0~1.4g / cm 3 .

[0052] ②C-Ta x Preparation of HfC transition matrix: The composite material containing the C matrix in step ① is completely immersed in the hafnium tantalum carbon precursor solution, immersed in an environment with a vacuum of 5-50kPa for 1 to 3 hours, and then at a pres...

Embodiment 1

[0057] A kind of C f / C-Ta x The preparation method of HfC composite material, its specific steps are:

[0058] ① Preparation of C matrix: The carbon fiber preform deposited with the pyrolytic carbon interface layer is completely immersed in phenolic resin, immersed in a vacuum of 10kPa for 3 hours, and then crosslinked and cured in a pressure tank at 200°C and a pressure of 5MPa 5 hours; the cured preform is placed in a cracking furnace and cracked at a high temperature of 900°C for 3 hours. Repeat the foregoing process twice to make the density of the composite material containing the C matrix 1.1g / cm 3 .

[0059] ②C-Ta x Preparation of the HfC transition matrix: 1 part of hafnium tantalum precursor, 2 parts of phenolic resin and 3 parts of alcohol solvent (ethylene glycol) are prepared into a hafnium tantalum carbon precursor solution in mole fractions. The composite material containing the C matrix in step ① is completely immersed in the hafnium tantalum carbon precursor solut...

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Abstract

The invention relates to a carbon fiber reinforced carbon-tantalum hafnium carbide solid solution composite material and a preparation method thereof. The preparation method comprises the following steps: preparing a pyrolytic carbon interface layer on a carbon fiber preform by utilizing a chemical vapor infiltration technology, preparing a C matrix by using a pyrolysis technology or a precursor infiltration and pyrolysis technology, then preparing a C-TaxHfC transition matrix from a tantalum hafnium carbide ceramic by using the precursor infiltration and pyrolysis technology, and finally preparing a TaxHfC matrix from the tantalum hafnium carbide by using the infiltration and pyrolysis technology. The Cf / C-TaxHfC composite material contains the C-TaxHfC transition matrix which is uniformly distributed, so that the thermal matching property of the first C matrix and the antioxidant TaxHfC matrix can be improved, and the mechanical properties of the composite material are enhanced; andthe Cf / C-TaxHfC composite material has a high TaxHfC content, so the oxidation resistance of the composite material can be obviously enhanced.

Description

Technical field [0001] The invention belongs to the technical field of C / C composite material preparation, and in particular relates to a C / C composite material f / C-Ta x HfC composite material and its preparation method. Background technique [0002] C / C composite material has low density, high temperature resistance, ablation resistance, thermal shock resistance, etc., and has excellent performance above 3000 ℃. As a high temperature structural material, it is widely used in solid rocket engines, aircraft hot end components, and aircraft Brake discs, etc. However, because C / C composite materials are composed of C elements, at temperatures above 400°C, C easily reacts with oxygen to generate carbon-oxygen compounds, which are lost in the form of gas, resulting in poor high-temperature oxidation resistance of C / C composite materials. Therefore, it is necessary to modify the anti-oxidation of the C / C composite material to meet the high temperature oxidizing air flow to wash the s...

Claims

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Application Information

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IPC IPC(8): C04B35/84C04B35/83C04B35/622
CPCC04B35/622C04B35/83C04B2235/3839C04B2235/77C04B2235/96C04B2235/9684
Inventor 裴雨辰刘伟宋环君于艺张宝鹏刘俊鹏
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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