Preparation method of C/SiC-ZrB2-ZrC ultrahigh-temperature ceramic-based composite material

A technology of ultra-high temperature ceramics and composite materials, which is applied in the field of preparation of C/SiC-ZrB2-ZrC ultra-high temperature ceramic matrix composite materials, and can solve the problem of low ZrC volume fraction, weak matrix bonding, poor mechanical properties and ablation properties of materials and other problems, to achieve the effect of improving ablation resistance, high volume content, and fine grains

Active Publication Date: 2012-06-27
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] In order to avoid the deficiencies of the prior art, the present invention proposes a C / SiC-ZrB 2 - The preparation method of ZrC ultra-high temperature ceramic matrix composite material can overcome the weak matrix bonding and slurry impregnation of ZrB due to slurry coating in the prior art 2 , The volume fraction of ZrC is low, resulting in poor mechanical properties and ablation properties of the material

Method used

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  • Preparation method of C/SiC-ZrB2-ZrC ultrahigh-temperature ceramic-based composite material
  • Preparation method of C/SiC-ZrB2-ZrC ultrahigh-temperature ceramic-based composite material
  • Preparation method of C/SiC-ZrB2-ZrC ultrahigh-temperature ceramic-based composite material

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Embodiment 1

[0028] step 1:

[0029] Preparation of composite material preform: cleaning the C / SiC composite material preform with an open porosity of 20vol%-30vol% by ultrasonic cleaning for at least 30 minutes, and drying in an oven at 80°C-100°C to obtain a C / SiC preform;

[0030] Slurry preparation: Dissolve phenolic resin in absolute alcohol, then add B 4 C powder is added to the alcohol solution of phenolic resin and ball milled on a roller ball mill for more than 24 hours to prepare B 4 C phenolic resin slurry; the proportion of slurry is phenolic resin, hexamethylenetetramine, B 4 The mass ratio of C powder is 10:1:5; the content of absolute alcohol controls the viscosity of the slurry to 50-100mPa·s and measures the viscosity with a rotational viscometer, and controls the dispersibility at 10-11 by adjusting the pH value;

[0031] Step 2: Vacuum pressure impregnation: C / SiC preform and B 4 C phenolic resin slurry is put into the vacuum tank at the same time, but not in contact;...

Embodiment 2

[0035] step 1:

[0036] Preparation of composite material preform: cleaning the C / SiC composite material preform with an open porosity of 20vol%-30vol% by ultrasonic cleaning for at least 30 minutes, and drying in an oven at 80°C-100°C to obtain a C / SiC preform;

[0037] Slurry preparation: Dissolve furan resin in absolute alcohol, then add B 4 C powder is added to the alcohol solution of furan resin and ball milled on a roller ball mill for more than 24 hours to prepare B 4 C furan resin slurry; the proportion of slurry is furan resin, hexamethylenetetramine, B 4 The mass ratio of C powder is 10:1:5; the content of absolute alcohol controls the viscosity of the slurry to 50-100mPa·s and measures the viscosity with a rotational viscometer, and controls the dispersibility at 10-11 by adjusting the pH value;

[0038] Step 2: Vacuum pressure impregnation: C / SiC preform and B 4 C furan resin slurry is placed in a vacuum tank at the same time, but without contact; vacuumize for ...

Embodiment 3

[0042] step 1:

[0043] Preparation of composite material preform: cleaning the C / SiC composite material preform with an open porosity of 20vol%-30vol% by ultrasonic cleaning for at least 30 minutes, and drying in an oven at 80°C-100°C to obtain a C / SiC preform;

[0044] Slurry preparation: mix B 4 C powder is added to 0.5%-1% mass fraction of cellulose sodium (CMC) aqueous solution and ball milled for more than 24 hours to prepare slurry b, B 4 C mass fraction 30%; Phenolic resin, hexamethylenetetramine are dissolved in absolute alcohol to prepare slurry c, phenolic resin mass fraction 50%; The viscosity of slurry is controlled by the content of absolute alcohol or CMC aqueous solution 50- 100mPa·s and measure the viscosity with a rotational viscometer, and control the dispersion by adjusting the pH value at 10-11;

[0045] Step 2: Vacuum pressure impregnation: The C / SiC preform is vacuum pressure impregnated into slurry b and c in turn; the C / SiC preform and slurry b are p...

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Abstract

The invention relates to a preparation method of a C/SiC-ZrB2-ZrC ultrahigh-temperature ceramic-based composite material. According to the invention, B4C and a C organic precursor are introduced into a C/SiC composite material with a vacuum pressure impregnation method; the obtained material is cured and is subject to a heat treatment, such that the C organic precursor is cracked, and pores sealed by the C organic precursor are opened; with a reactive melt infiltration method, under a condition that a temperature is higher than that of silicozirconium alloy, silicozirconium alloy is subject to a reaction with B4C and C, such that in-situ productions of SiC, ZrB2, and ZrC are realized, and the C/SiC-ZrB2-ZrC composite material is prepared. According to the invention, with the vacuum pressure impregnation method, B4C and the C organic precursor are introduced into the C/SiC composite material; with the reactive melt infiltration method, silicozirconium alloy is subject to a reaction with B4C and C, such that in-situ productions of SiC, ZrB2, and ZrC are realized. The produced ZrB2 and ZrC are advantaged in fine grains and high volume content. The ablation resistance and mechanical properties of the composite material are effectively improved.

Description

technical field [0001] The invention relates to a C / SiC-ZrB 2 -The preparation method of ZrC ultra-high temperature ceramic matrix composite material, especially a kind of using ZrB 2 1. A method for modifying the matrix of C / SiC ceramic matrix composites with ablation resistance by ZrC. Background technique [0002] Continuous carbon fiber toughened silicon carbide ceramic matrix composite (C / SiC) is an ideal high-temperature structural material, which has a series of advantages such as high temperature resistance, low density, high strength, and thermal shock resistance. Aircraft thermal protection systems and rocket engine nozzles have a wide range of applications and prospects. In an environment with a temperature lower than 1700 ° C, SiO exists on the surface of C / SiC 2 The oxide layer has excellent anti-ablation and anti-oxidation capabilities. The temperature of hot-end parts such as the nose cone of the atmospheric re-entry vehicle, the leading edge of the wing, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B41/87C04B35/80C04B35/84
Inventor 王一光皮慧龙范尚武成来飞张立同
Owner NORTHWESTERN POLYTECHNICAL UNIV
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