Method for repairing heat damage crackles of ceramic based composite material

A composite material and thermal damage technology, which is applied in the field of repairing thermal damage cracks of ceramic matrix composite materials, can solve the problems that cracks cannot be completely removed and repaired, the oxidation kinetic curve fluctuates greatly, and the grinding process is difficult to effectively control. To achieve the effect of improving the anti-oxidation ability, increasing the bending strength and restoring the anti-oxidation performance

Active Publication Date: 2015-03-25
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this method only improves the microscopic morphology of the coating through ball milling, and cannot completely remove and repair the cracks caused by the thermal environment inside the SiC coating and the substrate and the cracks generated during the preparation process.
Because the grinding process is difficult to effectively control, the wear amount of the sample coating is inconsistent, and even the coating peels off, the fibers are exposed, the oxidation kinetic curve fluctuates greatly, and the oxidation resistance performance is limited.

Method used

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  • Method for repairing heat damage crackles of ceramic based composite material
  • Method for repairing heat damage crackles of ceramic based composite material
  • Method for repairing heat damage crackles of ceramic based composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] Example 1: Repair of sample preparation cracks.

[0027] (1) Two-dimensional carbon fiber cloth is laminated in the same direction to obtain a two-dimensional (2D) laminated fiber preform.

[0028] (2) The fiber preform in (1) is deposited with a PyC interfacial layer with a thickness of about 200 nm. The process conditions are: deposition temperature 800-1000°C, Ar gas flow 150-200ml / min, C 3 h 6 The gas flow is 150-250ml / min, and the deposition time is 72h.

[0029] (3) The preform obtained in (2) is subjected to chemical vapor deposition (CVD) SiC matrix, and the process conditions are: deposition temperature 800-1000°C, pressure 2-4kPa, H 2 Gas flow 150-250ml / min, Ar gas flow 250-350ml / min, trichloromethylsilane temperature 25-35℃, H 2 The molar ratio to MTS is 8-12, and the deposition time is six heats, 120 hours each time. Obtain the original sample master.

[0030] (4) Grind the surface of the sample master plate prepared in (3) with a grinding wheel, open ...

Embodiment 2

[0033] Example 2: Repair of thermally damaged cracks in the sample.

[0034] (1) Two-dimensional carbon fiber cloth is laminated in the same direction to obtain a two-dimensional (2D) laminated fiber preform.

[0035] (2) The fiber preform in (1) is deposited with a PyC interfacial layer with a thickness of about 200 nm. The process conditions are: deposition temperature 800-1000°C, Ar gas flow 150-200ml / min, C 3 h 6 The gas flow is 150-250ml / min, and the deposition time is 72h.

[0036](3) The preform obtained in (2) is subjected to chemical vapor deposition (CVD) of the SiC substrate, and the process conditions are: deposition temperature 800-1000°C, pressure 2-4kPa, H 2 Gas flow 150-250ml / min, Ar gas flow 250-350ml / min, trichloromethylsilane temperature 25-35℃, H 2 The molar mass ratio to MTS is 8-12, and the deposition time is six heats, 120 hours each time. Obtain the original sample master.

[0037] (4) Grind the surface of the sample master plate prepared in (3) w...

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Abstract

The invention relates to a method for repairing heat damage crackles of a ceramic based composite material. According to the method, a whole SiC coating on the surface of a sample with heat damage crackles is directly and thoroughly abraded, and then the SiC coating is re-deposited. A deposition surface is smooth, closed pores of a C/SiC composite material for abrading the whole SiC coating are opened, which is beneficial for ensuring that the subsequent deposition of a matrix and a coating becomes more compact and the density gradient is reduced; and the crackles formed in the SiC matrix can be effectively repaired, so that the oxidation resistance of a sample in a high-temperature environment is improved more efficiently. By adopting the method, density defects and heat damages of C/SiC are effectively repaired, micro-crackles generated in a preparation process of C/SiC can be reduced, the density gradient and porosity of C/SiC from surface to inside are reduced, the crackles generated by the heat damages are gradually repaired, the oxidation resistance recovers and is relatively improved, and the bending strength is greatly improved.

Description

technical field [0001] The invention relates to a method for repairing thermal damage cracks of ceramic matrix composite materials, in particular to a method for repairing thermal damage cracks of continuous fiber reinforced silicon carbide ceramic matrix composite materials. Background technique [0002] Continuous carbon fiber toughened silicon carbide ceramic matrix composite (C / SiC) is a new thermal structure / function integrated material. The main application fields of C / SiC are often related to high-temperature environment, which may affect the occurrence and evolution of subsequent oxidation damage. In addition to thermal mismatch cracks generated during the preparation process, C / SiC will also Thermal damage cracks are generated due to the mismatch of thermal expansion coefficients. These cracks will reduce the high-temperature oxidation resistance of ceramic matrix composites, which will cause premature failure and even catastrophic failure of components during repea...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B41/87
Inventor 成来飞梅辉陈曦孙雨尧
Owner NORTHWESTERN POLYTECHNICAL UNIV
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