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A kind of c/sic composite material preparation method

A composite material and resorcinol technology, which is applied in the field of C/SiC composite material preparation, can solve the problems of low reaction activity of matrix carbon and liquid-phase silicon, low densification speed, and potential safety hazards, so as to improve mechanical properties and Anti-ablation performance, improved porosity and pore uniformity, and good overall product performance

Active Publication Date: 2020-12-25
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this process still has the following disadvantages: (1) the densification speed of the matrix is ​​low, the production cycle is long, and the preparation cost is high; (2) the prepared composite material inevitably has 10% to 15% of pores as a by-product of high molecular weight deposition. (3) The reaction gas concentration near the pore entrance of the preform is high, and the deposition rate is greater than the internal deposition rate, which easily leads to the closure of the entrance (that is, the "bottleneck effect") and the Generate a density gradient; (4) In the process of preparing SiC, strong corrosive products are produced, which have a strong corrosion and damage effect on equipment
First of all, the matrix carbon prepared by these methods is basically amorphous carbon, which has poor reactivity with molten silicon and is not conducive to the infiltration of liquid silicon.
[0009] In order to solve the problem of low reactivity between matrix carbon and liquid-phase silicon in the existing RMI process, the Institute of Metal Research, Chinese Academy of Sciences, based on the liquid-phase silicon reaction infiltration mechanism, started by improving the microscopic morphology, porosity and pore surface area of ​​matrix carbon. Invented the active liquid phase siliconizing technology based on the high-reactivity active carbon filling technology in the carbon fiber prefabricated body, which changed the matrix carbon from dense amorphous carbon to nano-scale granular carbon with abundant pores, thus greatly improving the matrix carbon reactivity active
However, since this process uses a large amount of alcohols as precursor solvents, special treatment is required for storage and preparation, and industrial production cannot be realized due to potential safety hazards.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0043] Use resorcinol, formaldehyde and water according to the mass ratio of 6:9:15 and mix evenly for use. Put the carbon fiber preform into a container containing the above solution, vacuum impregnate it, and keep it for 1 hour. After curing at 180°C, after natural cooling, the preform was taken out for high temperature cracking at 800°C, and the above impregnation-curing-cracking process was repeated 5 times, and finally the density of 1.30g / cm3 was prepared. 3 Low-density C / C porous body material. Embed the low-density C / C composite material into silicon powder, heat it to 1450°C for 30 minutes under vacuum, then raise it to 1700°C within 1 hour, and keep it for 60 minutes to prepare a C / SiC composite material with a density of 2.0 g / cm 3 , The bending strength is 260MPa.

Embodiment 2

[0045] Use resorcinol, formaldehyde, and water according to the mass ratio of 5:9:40, mix well and set aside. Put the carbon fiber preform into a container containing the above solution, vacuum impregnate it, and keep it for 1 hour. After being cured at 180°C, the preform was taken out for high temperature cracking at 800°C, and the above impregnation-curing-cracking process was repeated 7 times, and finally a density of 1.31g / cm3 was prepared. 3 Low-density C / C porous body material. Embed the low-density C / C composite material into silicon powder, heat it to 1450°C for 30 minutes under vacuum, then raise it to 1700°C within 1 hour, and keep it for 60 minutes to prepare a C / SiC composite material with a density of 2.1 g / cm 3 , The bending strength is 272MPa.

Embodiment 3

[0047] Use resorcinol, formaldehyde and water according to the mass ratio of 5:9:15 and mix evenly for use. Put the carbon fiber preform into a container containing the above solution, vacuum impregnate it, and keep it for 1 hour. After curing at 180°C, the preform was taken out and subjected to high temperature cracking at 800°C, and the above impregnation-curing-cracking process was repeated 6 times, and finally a density of 1.35g / cm3 was prepared. 3 Low-density C / C porous body material. Embed the low-density C / C composite material into silicon powder, heat it to 1450°C for 30 minutes under vacuum, then raise it to 1700°C within 1 hour, and keep it for 60 minutes to prepare a C / SiC composite material with a density of 2.3 g / cm 3 , The bending strength is 265MPa.

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PUM

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Abstract

The invention provides a preparation method of a C / SiC composite material. The C / SiC composite material is prepared by preparing a porous C / C composite material by means of an infiltration method. Asa special high-activity porous body C / C is adopted to reactive infiltration, the mechanical property and the anti- ablation property of the material are improved. The preparation method can be also applied to rapid low-cost preparation of a ceramic-based composite material.

Description

technical field [0001] The invention relates to a method for preparing a C / SiC composite material, which belongs to the technical field of composite material preparation. Background technique [0002] Developed countries such as the United States, France, Germany, and Japan have carried out extensive research on the preparation technology and application of C / SiC composite materials in the past 30 years. At present, C / SiC composite materials have been used as heat-resistant materials in reusable spacecraft and rocket engine systems, such as fuselage flaps, nose cone caps, wing leading edges of the US X-38 aircraft, and French SNECMA's The nozzle diffuser section of the HM7 large rocket engine. In addition, C / SiC composite materials also have broad application prospects in rocket engine combustion chambers, space mirrors, turbine engines, armor plates, and braking materials for aircraft and racing cars. [0003] The main preparation processes of C / SiC composite materials in...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/565C04B35/622C04B35/65C04B35/83C04B38/06C04B35/84
CPCC04B35/806C04B35/573C04B35/622C04B35/65C04B35/83C04B38/067C04B2235/77C04B2235/96
Inventor 王鹏于新民孙彬彬李晓东宋环君
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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