Repair method for ceramic matrix composite material
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A composite material and repair method technology, which is applied in the field of ceramic matrix composite material repair, and achieves the effects of simple repair process, short cycle, and improved high-temperature oxidation resistance.
Active Publication Date: 2014-11-19
SUZHOU HONGJIU AVIATION THERMAL MATERIALS TECH CO LTD
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Problems solved by technology
However, the coating and interface can only improve the thermal oxidation ability of the composite to a limited extent.
Method used
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Embodiment 1
[0020] (1) Ultrasonic cleaning of the worn ceramic matrix composite material sample, the cleaning time is 20 minutes;
[0021] (2) Composite material after drying;
[0022] (3) Use carbon fiber prepreg cloth to fill the defective parts, mold and solidify at a pressure of 30MPa;
[0023] (4) The temperature is 100°C, and the curing time is 3 hours;
[0024] (5) Put the above solidified sample into the reaction furnace, slowly rise to high temperature pyrolysis under vacuum atmosphere, the pyrolysis temperature is 1100°C, and the pyrolysis time is 2h;
[0025] (6) After the prepreg is decomposed, it is coated with boron carbide and silicon nitride nanopowder slurry, and enters the large gap between the fiber bundles;
[0026] (7) In a vacuum atmosphere, the temperature is raised to the reaction temperature, trichloromethylsilane gas is introduced, hydrogen is used as a carrier gas, and argon is used as a diluent gas to infiltrate silicon carbide with chemical vapor phase, and ...
Embodiment 2
[0028] (1) Ultrasonic cleaning of the worn ceramic matrix composite material sample, the cleaning time is 30 minutes;
[0029] (2) After drying, the unrepaired part of the composite material is pasted with graphite paper;
[0030] (3) Use carbon fiber prepreg cloth to fill the defective parts, mold press and cure, and the pressure is 50MPa;
[0031] (4) The temperature is 120°C, and the curing time is 4 hours;
[0032] (5) Put the above solidified sample into the reaction furnace, slowly rise to high temperature pyrolysis under vacuum atmosphere, the pyrolysis temperature is 1000°C, and the pyrolysis time is 4h;
[0033] (6) After the prepreg is decomposed, it is coated with boron carbide and silicon nitride nanopowder slurry, and enters the large gap between the fiber bundles;
[0034] (7) In a vacuum atmosphere, the temperature is raised to the reaction temperature, trichloromethylsilane gas is introduced, hydrogen is used as a carrier gas, and argon is used as a diluent g...
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Abstract
The invention discloses a repair method for a ceramic matrix composite material. The repair method is characterized by comprising the following steps: performing ultrasonic washing on a worn ceramic matrix composite material sample; attaching graphite paper to an unrepaired part of the dried composite material; filling a defective part by adopting a carbon fiber prepreg; molding and curing, wherein the pressure is 10 MPa to 100 MPa, the temperature is 80 to 160 DEG C and the curing time is 3 to 6 hours; slowly rising the temperature to a high temperature for performing pyrolysis in a vacuum atmosphere; coating boron carbide and silicon nitride nano-powder slurry after the prepreg is decomposed, wherein the boron carbide and silicon nitride nano-powder slurry enter large gaps among fiber bundles; rising the temperature to a reaction temperature in the vacuum atmosphere, and introducing trichloromethyl silane gas and hydrogen serving as a carrier gas, and argon serving as a dilution gas, wherein a chemical gas phase permeates silicon carbide, and the composite material is densified. According to the repair method for the ceramic matrix composite material, the chemical gas phase permeates the silicon carbide; a repair layer and the original base material are combined tightly; the high-temperature oxidation resistance of the ceramic matrix composite material is improved; a repair process is simple; the cycle is shorter.
Description
technical field [0001] The invention relates to a method for repairing composite materials, in particular to a method for repairing ceramic matrix composite materials. Background technique [0002] High thrust-to-weight ratio aeroengines are the basis for developing a new generation of fighter jets. Increasing the operating temperature of the engine and reducing the structural weight are effective ways to increase the thrust-to-weight ratio. It is urgent to develop a new generation of high-temperature-resistant, low-density, high-performance thermal structural materials. With its unique advantages of high temperature resistance and low density, ceramic matrix composites (CMC) overcome metals and are widely used in high-temperature equipment, but structural ceramics are brittle and poor in reliability, and carbon / carbon composites (C / C) have poor oxidation resistance. and low strength, and poor creep resistance of oxide ceramic matrix composites. As a necessary thermal struct...
Claims
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Application Information
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Patent Type & Authority Applications(China)
IPC IPC(8): C04B41/80
Inventor 陈照峰余盛杰
Owner SUZHOU HONGJIU AVIATION THERMAL MATERIALS TECH CO LTD
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