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Silicon carbide-reinforced refractory ceramic composite manufacture involves chemical vapor impregnation of carbon or silicon carbide preforms with silicon carbide gaseous precursor
Silicon carbide-reinforced refractory ceramic composite manufacture involves chemical vapor impregnation of carbon or silicon carbide preforms with silicon carbide gaseous precursor
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机译：碳化硅增强的耐火陶瓷复合材料的制造涉及将碳或碳化硅预成型坯与碳化硅气态前体进行化学气相浸渍
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摘要
Fabrication of a ceramic fiber composite resistant to high temperatures involves chemical vapor infiltration (CVI) of carbon fiber or silicon carbide preforms with a silicon carbide precursor in a suitable carrier gas. The pressure of the process is at least 600 hPa absolute, and the temperature of the process is at least 1100 degrees C. Preferred Features: The pressure of the process is controlled to be 600-1250 hPa absolute, and the temperature of the process is controlled to be 1100-1200 degrees C. A heat-resistant material having a large surface area, preferably carbon fiber felt, is disposed between the gas supply into the chamber and the layers of fibers to be infiltrated, in order to precondition the processing gas. The carbon fiber preform has a residual porosity between 12 and 15 volume %. Independent claims are given for components produced by the above process, including components for airplanes and space vehicles, and particularly control flaps, forward edges of wings, nose cones, rudders and heat protectors for space vehicles, such as crew return vehicles, and supersonic aircraft.
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