Microstructural Optimization of High Temperature SiC/SiC Composites

Abstract

Advanced materials and process approaches are described that have allowed NASA to develop five state-of-the-art silicon carbide (SiC) fiber-reinforced hybrid-SiC matrix composite systems that can operate under mechanical loading and oxidizing conditions for hundreds of hours at upper use temperatures from 1200 to 1450 C. Key data are presented that demonstrate the ability of these materials to meet the first-level property requirements for hot-section components in advanced gas turbine engines.