Advances in SiC/SiC Composites for Aero‐Propulsion

In the last decade, considerable progress has been made in the development and application of ceramic matrix composites consisting of silicon carbide (SiC) based matrices reinforced by small-diameter, continuous-length SiC-based fibers. For example, these SiC SiC composites are now in the early stages of implementation into hot-section components of civil aero-propulsion gas turbine engines, where in comparison to current metallic components they offer multiple advantages due to their lighter weight and higher temperature structural capability. For current production-ready SiC SiC, this temperature capability for long time structural applications is ∼1250°C, which is better than ∼1100°C for the best metallic superalloys. Foreseeing that even higher structural reliability and temperature capability would continue to increase the advantages of SiC SiC composites, progress in recent years has also been made at NASA toward improving the properties of SiC SiC composites by optimizing the various constituent materials and geometries within composite microstructures. The primary objective of this chapter is to detail this latter progress, both fundamentally and practically, with particular emphasis on recent advancements in materials and processes for the fiber, fiber coating, fiber architecture, and matrix, and in the design methods for incorporating these constituents into SiC SiC microstructures with improved thermo-structural performance.