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Preparation method of SiB6 modified self-healing SiCf/SiC composite material

A composite material and self-healing technology, applied in ceramic products, applications, household appliances, etc., can solve the problems of high temperature service life of materials, and achieve the effect of improving high temperature oxidation resistance and excellent mechanical properties

Inactive Publication Date: 2020-07-14
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

SiB 6 The self-healing components are uniformly dispersed in the matrix, and oxidation reaction occurs at the micro-cracks of the matrix under oxidative conditions to form glass phase B 2 o 3 , so as to protect the interior of the material from the invasion of oxidizing media, and solve the impact of inherent defects such as pores and cracks in the composite material on the high-temperature service life of the material

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] Step 1: Mix 30g of SiB6 powder (particle size 200nm, purity 99.9%), 2.5g of powder dispersant and 150g of ethanol, then ultrasonicate for 60min, then add 80g of phenolic resin, and ball mill for 5h to make a mixed slurry;

[0027] Step 2: Brush the mixed slurry prepared in step 1 on the fiber fabric containing the interface layer, and let it dry at room temperature for 3 hours to make a prepreg;

[0028] Step 3: Put the prepreg obtained in step 2 in a mold and use a hot press for hot pressing molding. The hot pressing temperature is 200°C, the time is 3 hours, and the mold pressure is 5 MPa to obtain a preform;

[0029] Step 4: Carbonize the preform obtained in Step 3 for 30 minutes at 1200°C in an inert atmosphere to prepare a porous body;

[0030] Step 5: Place silicon powder (particle size 3 μm, purity 99.9%) with a mass ratio of 2:1 to the porous body on the surface of the porous body, put it into a graphite crucible, and under vacuum conditions, the infiltration te...

Embodiment 2

[0032] Step 1: Mix 20g of SiB6 powder (particle size 5 μm, purity 99.5%), 2.1g of powder dispersant and 100g of ethanol, and then sonicate for 120min, then add 40g of phenolic resin, and ball mill for 6h to make a mixed slurry;

[0033] Step 2: Brush the mixed slurry prepared in step 1 on the fiber fabric containing the interface layer, and let it dry at room temperature for 2 hours to make a prepreg;

[0034] Step 3: Put the prepreg obtained in step 2 into a mold and use a hot press for hot pressing molding. The hot pressing temperature is 260°C, the time is 4 hours, and the mold pressure is 3.5 MPa to obtain a preform;

[0035] Step 4: Carbonize the preform obtained in Step 3 for 120 minutes at 800°C in an inert atmosphere to prepare a porous body;

[0036] Step 5: Put silicon powder (particle size 325mesh, purity 99.99%) in a mass ratio of 3:1 to the porous body on the surface of the porous body, put it into a graphite crucible, and under vacuum conditions, the infiltration...

Embodiment 3

[0038] Step 1: Add 5gSiB 6 Powder (particle size 1 μm, purity 99.9%), 0.25g powder dispersant and 30g ethanol were mixed, then ultrasonicated for 30min, then 20g of phenolic resin was added, and ball milled for 8h to make a mixed slurry;

[0039] Step 2: Brush the mixed slurry prepared in step 1 on the fiber fabric containing the interface layer, and let it dry at room temperature for 3 hours to make a prepreg;

[0040] Step 3: Put the prepreg obtained in step 2 in a mold and use a hot press for hot pressing molding. The hot pressing temperature is 300°C, the time is 1h, and the mold pressure is 3MPa to obtain a preform;

[0041] Step 4: Carbonize the preform obtained in Step 3 for 40 minutes at 1000°C in an inert atmosphere to prepare a porous body;

[0042] Step 5: Put silicon powder (particle size 5 μm, purity 99.99%) with a mass ratio of 4:1 to the porous body on the surface of the porous body, put it into a graphite crucible, and under vacuum conditions, the infiltration...

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Abstract

The invention belongs to the technical field of preparation of ceramic matrix composite materials, and particularly relates to a preparation method of a SiB6 modified self-healing SiCf / SiC composite material. According to the invention, SiB6 self-healing components are uniformly dispersed and distributed in a matrix; under an oxidation condition, an oxidation reaction is carried out at a micro-crack of a matrix to generate glass-phase B2O3, so that the interior of the material is protected from being invaded by an oxidizing medium, and the influence of inherent defects such as pores and cracksin the composite material on the high-temperature service life of the material is solved; due to the good high-temperature oxidation resistance of SiB6, the high-temperature oxidation resistance of the prepared SiCf / SiC composite material is greatly improved. SiB6 is subjected to an oxidation reaction at a high temperature to generate B2O3 and SiO2 at the same time, the melting point is increasedthrough the borosilicate glass phase, no other gas by-products are generated, and cracks can be effectively healed; siB6 has excellent mechanical properties, and SiB6 and SiC have matched thermal expansion coefficients, so that the mechanical properties of the modified material are only reduced to a small extent.

Description

technical field [0001] The invention belongs to the technical field of preparation of ceramic matrix composite materials, in particular to a SiB 6 Modified self-healing SiC f / SiC composite material preparation method. Background technique [0002] With the development of future aviation equipment, for extreme service conditions, SiC f The / SiC composite material itself provides higher requirements, and there is a theoretical upper limit. Affected by factors such as infiltration process and internal structure, SiC f / SiC composites inevitably have structural defects such as pores and microcracks. These defects can provide transmission channels for environmental media such as oxygen, and the interior of the material is corroded at high temperatures, which seriously affects its long-life service in high-temperature oxidizing environments. Therefore, the self-healing modification of the matrix is ​​expected to solve the above problems. At present, the more typical self-he...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B38/06C04B35/80C04B35/565C04B35/622
CPCC04B35/565C04B35/622C04B38/067C04B2235/3804C04B2235/602C04B2235/6567C04B35/806
Inventor 周怡然焦健姜卓钰吕晓旭刘虎杨金华齐哲高晔
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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