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Rapid preparation method of ceramic matrix composite material

A composite material and ceramic-based technology, which is applied in the field of rapid preparation of ceramic-based composite materials, can solve problems such as affecting the bearing capacity, prolonging the preparation period, affecting the self-healing effect, etc., and achieves the effect of improving the service life and improving the compactness.

Active Publication Date: 2016-03-16
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the traditional CVI combined with PIP process will not only prolong the preparation cycle, but also the self-healing layer will produce holes and cracks under the dual effects of high temperature expansion of CMCs and polymer cracking and shrinkage, making it difficult to maintain integrity, which will affect the self-healing effect , will affect the carrying capacity

Method used

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  • Rapid preparation method of ceramic matrix composite material
  • Rapid preparation method of ceramic matrix composite material
  • Rapid preparation method of ceramic matrix composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] Step 1: The surface of the C / SiC composite material deposited by the CVI process for 4 furnaces was polished with sandpaper at room temperature, cleaned ultrasonically, and dried.

[0026] Step 2: The dried sample is impregnated with polysilaborazane (PSNB) at room temperature to fill the cavities and cracks inside the material. After impregnation, cure at 120-250°C for 2-5 hours to achieve preliminary sealing of micro-cracks in the SiC matrix;

[0027] Step 3: Put the cured sample in the CVI deposition furnace, so that the cracking of the SiBCN precursor is carried out during the heating process, and the additive cracking and ceramicization of the SiBCN precursor are completed during the substrate deposition process;

[0028] The process conditions of the CVI method are as follows: MTS is used as a precursor, hydrogen is used as a carrier gas and a dilution gas, and argon is used as a protective gas; the total pressure is 0.1-10kPa, the deposition temperature is 800-12...

Embodiment 2

[0031] Step 1: The surface of the C / SiC composite material deposited by the CVI process for 4 furnaces was polished with sandpaper at room temperature, cleaned ultrasonically, and dried.

[0032] Step 2: The dried sample is impregnated with polyborosilazane (PBSZ) at room temperature to seal the cavities and cracks inside the material. After impregnation, cure at 120-250°C for 2-5 hours to achieve preliminary sealing of micro-cracks in the SiC matrix;

[0033] Step 3: Put the cured sample in the CVI deposition furnace, so that the cracking of the SiBCN precursor is carried out during the heating process, and the additive cracking and ceramicization of the SiBCN precursor are completed during the substrate deposition process;

[0034] The process conditions of the CVI method are as follows: MTS is used as a precursor, hydrogen is used as a carrier gas and a dilution gas, and argon is used as a protective gas; the total pressure is 0.1-10kPa, the deposition temperature is 800-12...

Embodiment 3

[0037] Step 1: Polish the surface of the C / SiC composite material deposited by the CVI process for 6 furnaces at room temperature with sandpaper, clean it ultrasonically, and dry it.

[0038]Step 2: The dried sample is impregnated with polysilaborazane (PSNB) at room temperature to fill the cavities and cracks inside the material. After impregnation, cure at 120-250°C for 2-5 hours to achieve preliminary sealing of micro-cracks in the SiC matrix;

[0039] Step 3: Put the cured sample in the CVI deposition furnace, so that the cracking of the SiBCN precursor is carried out during the heating process, and the additive cracking and ceramicization of the SiBCN precursor are completed during the substrate deposition process;

[0040] The process conditions of the CVI method are as follows: MTS is used as a precursor, hydrogen is used as a carrier gas and a dilution gas, and argon is used as a protective gas; the total pressure is 0.1-10kPa, the deposition temperature is 800-1200°C,...

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Abstract

The invention relates to a rapid preparation method of a ceramic matrix composite material. A polymer of C / SiC and SiC / SiC semi-finished product composite materials after CVI at a room temperature is subjected to dipping and curing, so that preliminary sealing and filling of microcracks in SiC matrix are achieved; splitting of an SiBCN precursor is carried out in the heating process of a CVI process; additive splitting and ceramization of the SiBCN precursor are finished in the matrix deposition process; contraction of a self-healing layer is inhibited; final sealing and filling of micro-cracks in the SiC matrix are finished; and holes and cracks in the self-healing layer and the SiC matrix are reduced. The holes and the cracks in the ceramic matrix composite material obtained by the invention are filled with the SiBCN; the material compactness is improved; and meanwhile, the service lifetime of the composite material in a high-temperature water and oxygen coupled environment is prolonged.

Description

technical field [0001] The invention belongs to the field of rapid preparation of ceramic-based composite materials, in particular to a rapid preparation method of ceramic-based composite materials, and is a method for improving the service life of ceramic-based composite materials in a high-temperature water-oxygen environment. Background technique [0002] The hot end environment of an aero-engine is a typical coupling environment of long time (hundreds to thousands of hours), heat (700-1650°C), force (fatigue, creep, complex loads), oxidation (oxygen, water, molten salt) . Long-term thermal oxidation is a slow oxidation process of ceramic matrix composites (CMCs) by an oxidizing medium under certain temperature and load. The dominant factor of fiber and interface damage is thermal oxidation, and force is the factor that widens cracks and promotes oxidation. Therefore, to protect the fiber and interface layer from damage, the first step is to prevent the invasion of oxid...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B41/87C04B35/565
Inventor 栾新刚王建强成来飞
Owner NORTHWESTERN POLYTECHNICAL UNIV
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