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Process for preparing self-sealing silicon carbide ceramic based composite material

A technology of composite materials and silicon carbide, which is applied in the field of preparation of self-healing silicon carbide ceramic matrix composite materials, can solve the problems of easy peeling, long time, complicated process, etc., and achieves improved thermal oxidation life, strong oxidation resistance, The effect of simple process

Active Publication Date: 2009-08-12
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, these anti-oxidation measures have the following disadvantages: (1) The scale of the coating is limited, and the thickness is generally within 200 μm. If the coating is too thick, it is easy to peel off; It is difficult to effectively prevent oxidation under stress; (2) the scale of the interface is smaller, the thick interface will lose the mechanical transmission function, and the interface is already close to the fiber, it is even more difficult to greatly improve the thermal oxidation life of the material
[0005] US patent (US5246736) and Canadian patent (CA2214465) have invented a multilayer Si-B-C substrate manufacturing method, which uses B4C and Si-B-C modify the SiC matrix of silicon carbide ceramic matrix composites, and the manufactured materials can achieve self-healing at higher temperatures, but the process is complex, time-consuming, and costly
There is no research report on C / (SiC-BCx)n self-healing SiC-based composites

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] (1) Use 2D plain carbon cloth with brand T300 as the reinforcement of the composite material, and cut the 2D fiber cloth to a specification of 250mm×125mm;

[0025] (2) Laminate 2-dimensional carbon fiber cloth and shape it with a graphite mold. The thickness of the fiber prefabricated body is 2.3mm;

[0026] (3) Infiltrating the carbon fiber preform into the pyrolytic carbon interface layer, the thickness of which is 100nm;

[0027] (4) High temperature treatment is performed on the carburized preform, the treatment temperature is 1700°C, the treatment atmosphere is Ar gas, and the treatment time is 3.0 hours;

[0028] (5) Put the preform after high temperature heat treatment into the chemical vapor infiltration furnace to infiltrate the silicon carbide substrate, the infiltration temperature: 900°C, the holding time: 150h, the pressure in the furnace: 2kPa, the precursor is CH 3 SiCl 3 ;

[0029] (6) Continue to infiltrate the boron carbide matrix, infiltration tem...

Embodiment 2

[0033] (1) Use the 3D carbon fiber with the brand name T300 as the reinforcement of the composite material, and weave the 3D fiber into a length and width of 250mm×125mm and a thickness of 4.5mm;

[0034] (2) The 3-dimensional carbon fiber braid is directly fixed and formed with a graphite mold;

[0035] (3) Infiltrating the carbon fiber preform into the pyrolytic carbon interface layer, the thickness of which is 300nm;

[0036] (4) High temperature treatment is performed on the carburized preform, the treatment temperature is 2100°C, the treatment atmosphere is Ar gas, and the treatment time is 1.0 hour;

[0037] (5) Put the preform after high temperature heat treatment into the chemical vapor infiltration furnace to infiltrate the silicon carbide substrate, the infiltration temperature: 1050°C, the holding time: 100h, the pressure in the furnace: 2kPa, the precursor is CH 3 SiCl 3 ;

[0038] (6) Continue to infiltrate boron carbide matrix, infiltration temperature: 1050°C...

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Abstract

The invention relates to a method for manufacturing a self-healing silicon carbide ceramic matrix composite. The method comprises the following steps: preparing fiber preform; filtrating a pyrolytic carbon interface layer by chemical gas phase; carrying out thermal treatment on the interface layer; infiltrating silicon carbide and boron carbide substrate by chemical gas phase alternately; and depositing three silicon carbide coatings by the chemical gas phase. The method has strong designability, simple process and good repeatability. The ceramic matrix composite manufactured by the method has good high temperature resistance and oxidation resistance, has excellent mechanical performance and thermal performance, and can meet the use requirement of a sealing strip / an adjustment sheet, an interior cone and other components of a high thrust-weight ratio aeroengine.

Description

technical field [0001] The invention relates to a preparation method of a self-healing silicon carbide ceramic matrix composite material, in particular to a fiber reinforced multilayer (SiC-BC x ) n Method for the manufacture of self-healing silicon carbide ceramic matrix composites. Background technique [0002] Fiber-reinforced silicon carbide ceramic matrix composite (CMC-SiC) is a new generation of high-temperature-resistant, low-density, high-performance thermal structural materials, which can effectively increase the operating temperature of the engine and reduce the structural weight. application prospects. The density of CMC-SiC is 2~2.5g / cm 3 , is 1 / 4 to 1 / 10 of high-temperature metal structural materials, and the potential maximum service temperature is 1650°C, which is 400-500°C higher than high-temperature metal structural materials. In addition, CMC-SiC also overcomes the shortcomings of high brittleness and poor reliability of structural ceramics, poor oxid...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/83C04B35/565C04B35/622
Inventor 刘永胜张立同成来飞徐永东殷小玮董宁栾新刚
Owner NORTHWESTERN POLYTECHNICAL UNIV
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