Preparation method of ablation resistant C/SiC ceramic matrix composite material

A composite material and ceramic-based technology, which is applied in the field of preparation of ablation-resistant C/SiC ceramic-based composite materials, can solve the problems of few researches on continuous carbon fiber impregnated multi-element amorphous ceramic composite materials, and improve high-temperature mechanical properties and expand Application range, effect of solving brittle problems

Active Publication Date: 2019-11-08
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In addition, amorphous ceramics are still in the laboratory stage and are mainly used as bulk materia...

Method used

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  • Preparation method of ablation resistant C/SiC ceramic matrix composite material
  • Preparation method of ablation resistant C/SiC ceramic matrix composite material
  • Preparation method of ablation resistant C/SiC ceramic matrix composite material

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preparation example Construction

[0031] The invention provides a preparation method of an ablation-resistant C / SiC ceramic matrix composite material, the preparation method comprising the following steps:

[0032] (1) Provide a porous C / C composite material preform, preferably with a density of 0.8 to 1.0 g / cm 3 (can be any numerical value in this range, for example, can be 0.8g / cm 3 , 0.9g / cm 3 , 1.0g / cm 3 ) porous C / C composite preform.

[0033] The present invention can adopt the CVI densified carbon fiber prefabricated body, place the carbon fiber prefabricated body in a chemical vapor deposition furnace, use the CVI process to chemically deposit the green body, and the carbon source gas diffuses into the pores of the carbon fiber prefabricated body after cracking in a low vacuum environment, And deposited on the hole wall to obtain a porous C / C composite material prefabricated body. The densification process can be propylene as the carbon source gas, nitrogen as the carrier gas, and the deposition te...

Embodiment 1

[0048] (1) The green body is chemically deposited by the CVI process to obtain a porous C / C composite material preform, which is deposited to a density of 0.8g / cm 3 , the densification process uses propylene as the carbon source gas, nitrogen as the carrier gas, and a deposition temperature of 900°C.

[0049] (2) Use polycarbosilane solution to impregnate, solidify, and crack the precursor to prepare a C / SiC composite material, and perform multiple rounds of impregnation and cracking to obtain a density of 1.8g / cm 3 C / SiC composite materials.

[0050] (3) Using chloroform as a solvent, adding polysilazane and boron powder, the proportion of polysilazane in the mixed solution is 35wt%, and the proportion of boron powder in the mixed solution is 20wt%. Stir evenly to obtain a SiBCN precursor solution.

[0051] (4) Using the precursor solution obtained above, the C / SiC composite material prepared in step (2) is impregnated, solidified and cracked. The impregnation is vacuum im...

Embodiment 2 to 4

[0054] Preparation method is basically the same as Example 1, except that:

[0055] For Example 2, in step (2), multiple rounds of dipping and cracking were carried out to obtain a density of 1.9 g / cm 3 ceramic matrix composites.

[0056] For Example 3, in step (2), multiple rounds of dipping and cracking were carried out to obtain a density of 2.0 g / cm 3 ceramic matrix composites.

[0057] For Example 4, in step (2), multiple rounds of dipping and cracking were carried out to obtain a density of 2.5g / cm 3 ceramic matrix composites.

[0058] The test results of the test splines are shown in Table 1.

[0059] Table 1

[0060]

[0061]

[0062] Comparing the test results of Examples 1 to 4, the inventors found that with the increase of the density of the C / SiC composite material, the mechanical properties of the final composite material are getting better and better. The inventor speculates that this is because the relatively dense C / SiC composite material can well p...

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Abstract

The invention relates to a preparation method of an ablation resistant C/SiC ceramic matrix composite material. The method includes the steps of: (1) providing a porous C/C composite preform; (2) making the preform into a C/SiC composite material; (3) mixing polysilazane, boron powder and a solvent, with the mass percentage of polysilazane in the mixture being 30-40% and the mass percentage of boron powder in the mixture being 10-30%, and mixing the mixture uniformly to obtain a SiBCN precursor solution; and (4) using the SiBCN precursor solution for impregnation curing and cracking of the composite material, thus obtaining the ablation resistant C/SiC ceramic matrix composite material. The method provided by the invention can acquire the composite material with high density, low ablationrate and excellent comprehensive properties.

Description

technical field [0001] The invention relates to the technical field of ceramic composite materials, in particular to a preparation method of an ablation-resistant C / SiC ceramic matrix composite material. Background technique [0002] In recent years, high-temperature structural ceramic materials have attracted increasing attention due to their excellent performance. Silicon carbide ceramics have the advantages of high temperature resistance, thermal shock resistance, corrosion resistance, erosion resistance, wear resistance and good thermal conductivity, and have always been an important candidate material for high temperature structural ceramics. However, SiC is a covalent bond material, and its sintering temperature is high. It is difficult to sinter densely by conventional sintering methods. It usually needs to be heated to above 2100 ° C. At the same time, it needs to add Al when sintering. 2 o 3 , Y 2 o 3 Or MgO and other sintering aids, resulting in a decrease in t...

Claims

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Application Information

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IPC IPC(8): C04B35/571C04B35/80C04B35/622
CPCC04B35/571C04B35/622C04B35/806C04B2235/421C04B2235/5248C04B2235/5256C04B2235/616C04B2235/656C04B2235/658C04B2235/9684
Inventor 裴雨辰于艺于新民刘俊鹏宋环君金鑫张宝鹏刘伟王鹏李晓东
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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