Mechanical properties of ceramic-matrix composites for aeroengine applications

摘要

The use of ceramic-matrix composites as structural materials in aeroengine components requires a detailed characterization of their mechanical behaviour in service. This task was carried out though flexure and fracture tests at 20 deg.C and 1200 deg.C on several ceramic-matrix composites bidirectionally-reinforced with SiC fibers. The effects of thermal exposure at elevated temperature (100 hours at 1200 deg.C) and of several thousand of thermal shocks between 400 deg.C and 1200 deg.C on these mechanical properties were also analyzed.