Preparation method of ultrahigh-temperature silicon carbide ceramic-based composite material and ultrahigh-temperature silicon carbide ceramic-based composite material
A technology of silicon carbide ceramic matrix and composite materials, which is applied in the field of preparation of ultra-high temperature silicon carbide ceramic matrix composite materials and ultra-high temperature silicon carbide ceramic matrix composite materials, can solve problems such as lack of matrix, achieve strong synergistic effects, and improve oxidation resistance Performance and anti-ablation performance, effect of increasing specific surface area and ceramic activity
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[0028] A method for preparing an ultra-high temperature silicon carbide ceramic matrix composite material, comprising the following steps:
[0029] ① Cut the two-dimensional plain silicon carbide fiber cloth into a rectangle of 300mm*250mm;
[0030] ② Laminate the cut silicon carbide fiber cloth to a thickness of 2-5 mm, and sew it into a whole with silicon carbide fiber suture thread, and use graphite mold to shape the silicon carbide fiber prefabricated body;
[0031] ③Put the silicon carbide fiber prefabricated body into a chemical vapor deposition furnace to prepare the pyrolytic carbon interface layer. The precursor is: propane, the deposition temperature: 800-1150°C, the holding time: 8-16h, the pressure in the furnace: 1-2kPa, Interface thickness: 60~800nm;
[0032] ④ Ceramic powder containing anti-ablation components, such as Si 3 N 4 , SiC, ZrB 2 , ZrC, H f C.H f B 2 , BN and B 4 One or more of C and the polycarbosilane precursor solution are prepared into an ...
Embodiment 1
[0038] ① Cut the two-dimensional plain silicon carbide fiber cloth into a rectangle of 300mm*250mm;
[0039] ② Laminate the cut silicon carbide fiber cloth to a thickness of 2-5 mm, and sew it into a whole with silicon carbide fiber suture thread, and use graphite mold to shape the silicon carbide fiber prefabricated body;
[0040] ③Put the silicon carbide fiber preform into a chemical vapor deposition furnace to prepare the pyrolytic carbon interface layer. The precursor is propane, deposition temperature: 1000°C, holding time: 10h, furnace pressure: 1.2kPa, propane interface thickness: 100nm;
[0041] ④ ZrB 2 The ceramic powder and the polycarbosilane precursor solution (solvent is xylene) are formulated into an impregnation slurry, wherein the content of the ceramic powder is 10wt%, and the viscosity is controlled at 80mPa·s;
[0042] ⑤ Put the prefabricated part in ③ into a vacuum high-pressure impregnation tank, inject the impregnating solution in ④ to submerge the pref...
Embodiment 2
[0047] ① Cut the two-dimensional plain silicon carbide fiber cloth into a rectangle of 300mm*250mm;
[0048] ② Laminate the cut silicon carbide fiber cloth to a thickness of 2-5 mm, and sew it into a whole with silicon carbide fiber suture thread, and use graphite mold to shape the silicon carbide fiber prefabricated body;
[0049] ③Put the silicon carbide fiber preform into a chemical vapor deposition furnace to prepare the pyrolytic carbon interface layer. The precursor is propane, deposition temperature: 1000°C, holding time: 10h, furnace pressure: 1.2kPa, propane interface thickness: 100nm;
[0050]④ Prepare ZrC ceramic powder and polycarbosilane precursor solution (solvent is xylene) to prepare impregnation slurry, wherein the content of ceramic powder is 10wt%, and the viscosity is controlled at 80mPa·s;
[0051] ⑤ Put the prefabricated part in ③ into a vacuum high-pressure impregnation tank, inject the impregnating solution in ④ to submerge the prefabricated part, evac...
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