C/C composites are the emerging materials of choice for aero-engine hot-end components that will bear impact loading in thermal-oxidizing environments. For the components run for extended periods, the safe operation of components depends on how to evaluate damages under a dynamic load. In this study, Charpy impact tests at a temperature range of 25 to 1 200? were carried out on C/C composites to verify the effects of temperature induced thermal expansion and oxidation on their impact performance. Below 800?, oxidation was negligible and composites expanding played a leading role, resulting in the remarkable increase infi ber/matrix interface strength and impact energy. However, when the temperature was above 800?, the release of CO or CO2 due to oxidation resulted in a lower impact energy.
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