Resistance to oxidation and ablation of SiC coating on graphite prepared by chemical vapor reaction

A simple way to prepare silicon carbide reinforced graphite composite lubricating materials

“…SiC, with high intensity, excellent oxidation resistance, high coefficient of thermal conductivity and wear resistance, is one of the common reinforcing phases for many composites. Another advantage of SiC is the similar thermal expansion coefficient to graphite [7][8][9] . Few researches have been done on siliconized graphite to increase the strength and the wear resistance of graphite [10] .…”

Microstructure and ablation behavior of C/C–HfC composites prepared by precursor infiltration and pyrolysis

“…However, applications of C/C composites are restricted to rapid oxidation and ablation in the extreme environment of high-pressure airflow and hyper-thermal flux [4][5][6]. It is fundamental to improve the oxidation and ablation resistance of C/C composites.…”

Influence of infiltration temperature on the microstructure and oxidation behavior of SiC–ZrC ceramic coating on C/C composites prepared by reactive melt infiltration

“…Small cubic specimens (10×10×10 mm) to be used as substrates were cut from a 3D C/C composite bulk with a density of about 1.60 g/cm 3 . Before the process of RMI, each specimen was hand-polished with 400 grit SiC paper, then cleaned ultrasonically with ethanol and dried at 100 o C for 1 h. The powder mixture used as the infiltrator was composed of Si (300 mesh), Zr (300 mesh) and C (300 mesh) with a mass ratio Si: Zr: C of 1: 1: 0.3.…”

“…Nevertheless, the rapid oxidation of C/C composites above 773 K limits their high temperature applications in oxygen containing environments [3]. Therefore, the key to extending applications of C/C composites is to develop reliable oxidation protection.…”

“…The UHTCs modified SiC coated C/C composites have retained strength and good ablation resistance at temperatures over 1600 C, which allow them to be used as the potential candidates for extreme environments associated with the hypersonic flight and rocket propulsion [10,11]. Among those UHTCs, ZrC has been given much attention because of its high melting point (3540 C), relatively low density (6.73 g/cm 3 ), high thermal conductivity, excellent chemical stability and thermal shock resistance [12,13]. In addition, the zirconia (ZrO 2 ) formed by the oxidation of ZrC has a melting point as high as 2700 C.…”