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Preparation method of binary ceramic modified carbon/carbon composite

A carbon composite material and two-component technology, applied in the field of composite materials, can solve the problems of ZrC micropowder density, equipment pollution, long production cycle, etc., and achieve excellent high-temperature erosion resistance, excellent mechanical properties, and avoid damage.

Active Publication Date: 2014-07-09
AVIC COMPOSITES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The use of chemical vapor deposition process for material preparation has problems such as difficult control of process parameters, long preparation cycle, and environmental pollution caused by reaction by-product corrosion equipment; and direct impregnation of micro-powder technology is a more economical method, but due to the high density of ZrC micro-powder, the material It is difficult to guarantee the suspension and impregnation uniformity of slurry

Method used

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  • Preparation method of binary ceramic modified carbon/carbon composite
  • Preparation method of binary ceramic modified carbon/carbon composite

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preparation example Construction

[0026] (2) Preparation of low-density carbon / carbon composite material: using methane or propane as a carbon source, put the fiber preform into a high-temperature deposition furnace for chemical vapor deposition to obtain the low-density carbon / carbon composite material Body;

[0027] (3) Glue configuration: use polycarbosilane / xylene solution and zirconium carbide precursor xylene solution as modification solution, use ultrasonic oscillation method to mix the solutions, and use this mixed solution to vacuum the fiber preform Dipping;

[0028] (4) Vacuum impregnation: Use the prepared impregnation glue to vacuum impregnate the above-mentioned low-density carbon / carbon composite material.

[0029] (5) Pyrolysis: put the fiber prefabricated body that has been vacuum-impregnated into a high-temperature cracking furnace, and perform high-temperature cracking under vacuum;

[0030] (6) repeat step (4) and step (5) glue impregnation-pyrolysis, until the weight after the completion...

Embodiment 1

[0039] (1) Material preparation:

[0040] a. Using carbon felt as a fiber reinforcement to prepare a fiber preform

[0041] b. Prepare SiC and ZrC ceramic precursor solutions.

[0042] (2) Preparation of low-density carbon / carbon composite material: using propane as a carbon source, put the fiber prefabricated body into a high-temperature deposition furnace for chemical vapor deposition to obtain the low-density carbon / carbon composite material green body ; The chemical vapor deposition process conditions are: propane as the carbon source, the flow rate is 800ml / min; the dilution gas is high-purity nitrogen, the flow rate is 800ml / min; the deposition temperature is 1000°C, the deposition pressure is 0.5KPa, and the deposition time is 100h. The resulting low-density carbon / carbon composite material has a density of 1.2g / cm3 .Analyze the microstructure of low-density carbon / carbon composites, the scan photos are as follows figure 1 (a), (b) shown. From figure 1 It can be see...

Embodiment 2

[0053] A kind of preparation method of ZrC / SiC two-component modified carbon / carbon composite material of the present invention, comprises the following steps:

[0054] (1) Material preparation:

[0055] a. Using carbon felt as a fiber reinforcement to prepare a fiber preform

[0056] b. Prepare SiC and ZrC ceramic precursor solutions.

[0057] (2) Preparation of low-density carbon / carbon composite material: using propane as a carbon source, put the fiber prefabricated body into a high-temperature deposition furnace for chemical vapor deposition to obtain the low-density carbon / carbon composite material green body The chemical vapor deposition process conditions are: propane as the carbon source, the flow rate is 1000ml / min; the dilution gas is high-purity nitrogen gas, the flow rate is 1000ml / min; the deposition temperature is 1100°C, the deposition pressure is 1.5KPa, and the deposition time is 120h. The resulting low-density carbon / carbon composite material has a density ...

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Abstract

The invention belongs to the technical field of composite materials, relates to preparations of a modified carbon / carbon composite, and particularly relates to a preparation method of a binary ceramic modified carbon / carbon composite. The preparation method comprises the following steps of preparing a fiber perform; preparing a low density carbon / carbon composite green body via a chemical vapor deposition process by putting the fiber perform in a vacuum deposition furnace with methane or propane as a reactant gas; carrying out impregnation of the low density carbon / carbon green body in a vacuum impregnation kettle, by using a SiC and ZrC precursor solution as an impregnation modification solution; putting an impregnated sample in a high temperature cracking furnace; carrying out high temperature pyrolysis under a vacuum state; repeating the cycle of vacuum impregnation-high temperature pyrolysis until a weight gain rate of the material in one vacuum impregnation-high temperature pyrolysis cycle is lower than 1%; and finishing the preparation. The developed component has the advantages of excellent mechanical properties, good ablation resistance and short development period.

Description

technical field [0001] The invention belongs to the technical field of composite materials, and relates to the preparation of modified carbon / carbon composite materials, in particular to a preparation method of bicomponent ceramic modified carbon / carbon composite materials. Background technique [0002] With the continuous improvement of aviation technology, how to improve the performance of aviation composite materials has become the focus of research in the field of aviation materials. Carbon / carbon composite materials have become the research focus and hotspot in the field of aero-engines because of their high specific strength, high specific modulus, light weight, and excellent high temperature resistance. However, since the carbon / carbon composite material starts to oxidize at 370°C, and the oxidation intensifies after 500°C, which limits its application in aero-engines, since the carbon / carbon composite material came out, its oxidation resistance and anti-ablation prot...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/83
Inventor 李秀倩邱海鹏焦健王宇邹豪
Owner AVIC COMPOSITES
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