Carbon-ceramic composite material and preparation method for same through precursor impregnation

A carbon-ceramic composite material and precursor technology, which is applied in the field of carbon-ceramic composite material preparation, can solve the problems of increasing the number of openings on the surface of the material and affecting the performance of the composite material, and achieves the effects of low equipment requirements, excellent performance and simple operation.

Inactive Publication Date: 2018-06-08
西安天运新材料科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the silicon-containing precursor solution used in this method is an impregnation solution, and the densification process mainly relies on the impregnation and cracking process. This relatively simple process will cause a large number of closed pores inside the material on the one hand, and increase the surface density of the material on the other hand. The number of openings affects the final performance of the composite material

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] A kind of precursor impregnation preparation method of carbon-ceramic composite material, comprises the following steps:

[0026] Step 1: Set the density to 0.15g / cm 3 The carbon fiber mat is placed in the deposition furnace, with nitrogen as the carrier gas and methane as the carbon source gas for chemical vapor infiltration until the fiber preform density increases to 1.1g / cm 3 , followed by a high-temperature treatment at 2100°C for 2.5 hours under a nitrogen protective atmosphere to obtain a preform I. The specific process of chemical vapor infiltration is as follows: the volume ratio of carbon source gas to carrier gas is 1:7, the pressure in the deposition furnace is controlled to 1.9KPa, and the pyrolysis Temperature 1100°C;

[0027] Step 2: Put the preform I in the mixture, ultrasonically vibrate for 2 hours, then take it out and let it stand for 2 hours, transfer it to an atmosphere furnace and heat it up to 1100°C for 3 hours at a heating rate of 3°C / min, rep...

Embodiment 2

[0030] A kind of precursor impregnation preparation method of carbon-ceramic composite material, comprises the following steps:

[0031] Step 1: Set the density to 0.40g / cm 3 The carbon fiber 3D needle felt is placed in the deposition furnace, with nitrogen as the carrier gas and methane as the carbon source gas for chemical vapor infiltration until the density of the fiber preform increases to 1.0g / cm 3 , followed by a high-temperature treatment at 2000°C for 2 hours under a nitrogen protective atmosphere to obtain preform I. The specific process of chemical vapor infiltration is as follows: the volume ratio of carbon source gas to carrier gas is 1:4, the pressure in the deposition furnace is controlled to 1.4KPa, and the pyrolysis temperature 1050°C;

[0032] Step 2: Put the preform I in the mixture, ultrasonically vibrate for 3 hours, then take it out and let it stand for 4 hours, transfer it to the atmosphere furnace and heat it up to 1000°C for 4 hours at a heating rate ...

Embodiment 3

[0035] A kind of precursor impregnation preparation method of carbon-ceramic composite material, comprises the following steps:

[0036] Step 1: Set the density to 0.49g / cm 3 The silicon carbide fiber braided body is placed in a deposition furnace, with nitrogen as the carrier gas and methane as the carbon source gas for chemical vapor infiltration until the fiber preform density increases to 1.05g / cm 3 , followed by a high-temperature treatment at 2200°C for 3 hours under a nitrogen protective atmosphere to obtain a preform I. The specific process of chemical vapor infiltration is as follows: the volume ratio of carbon source gas to carrier gas is 1:3, the pressure in the deposition furnace is controlled to 1.0KPa, and the pyrolysis temperature 1080°C;

[0037] Step 2: Put the preform I in the mixture, ultrasonically vibrate for 5 hours, then take it out and let it stand for 3 hours, transfer it to an atmosphere furnace and heat it up to 1200°C for 2 hours at a heating rate ...

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Abstract

The invention discloses a carbon-ceramic composite material and a preparation method for the same through precursor impregnation, and belongs to the technical field of preparation of carbon-ceramic composite materials. The preparation method of the present invention comprises the steps of putting a fiber preform with a certain density in a deposition furnace, performing chemical vapor infiltrationby taking nitrogen gas as a carrier gas, and then performing high-temperature treatment in a protective atmosphere of nitrogen; then putting the perform subjected to chemical vapor densification in amixture, performing ultrasonic oscillating, taking out the treated system for standing, and then transferring the system to an atmosphere furnace for sintering, so as to obtain a sintered preform; and finally, performing precursor impregnation-cracking process on the sintered perform for multiple times, so as to obtain the carbon-ceramic composite material. The method is simple to operate and lowin equipment requirement, and can achieve multi-level densification of a porous preform.

Description

technical field [0001] The invention belongs to the technical field of preparation of carbon-ceramic composite materials, and in particular relates to a carbon-ceramic composite material and a preparation method for impregnating a precursor thereof. Background technique [0002] Carbon-ceramic composite materials have a series of advantages such as high strength, oxidation resistance, electrical conductivity, corrosion resistance, thermal shock resistance and easy machining, and can be used as mechanical seals, bearings, molds and high-temperature resistant The heating element has broad application prospects. [0003] The precursor impregnation method is one of the main processes currently used to prepare carbon-ceramic composite materials. It uses polymer precursors to impregnate porous fiber braids. After cross-linking and curing and high-temperature cracking, the silicon carbide matrix can be generated in situ. However, due to the escape of cracked small molecules to for...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/565C04B35/571
CPCC04B35/565C04B35/571C04B35/806C04B2235/6562C04B2235/6567C04B2235/658C04B2235/661C04B2235/77
Inventor 罗威江汛张鸿翔艾涛马洋洋延成宇
Owner 西安天运新材料科技有限公司
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