One potential way to achieve N+3 goals is the introduction of ceramic matrix composite (CMC) materials into turbine engines. The introduction of CMC vanes and/or blades into turbine engines leads to gains in specific fuel consumption by allowing higher operating temperatures, reductions in required cooling, and reductions in vehicle weight. Environmental barrier coatings (EBCs) will play a crucial role in advance gas turbine engines because of their ability to significantly extend the temperature capability of the CMC engine components in harsh combustion environments. Due to the inherent scatter in both EBCs and CMCs, one needs to analyze the CMC/EBC interface with a probabilistic methodology. The proposed work will further develop a software tool that will facilitate the probabilistic/reliability analysis of the CMC/EBC interface, model time-dependent properties such as creep and/or growth of an oxide layer that induces EBC failure, and integrate uncertainty across scales between the interface and component levels in a global/local approach. The software is intended to allow for a more realistic prediction of component life and failure and to aid in design and fabrication of EBC/CMC systems and gas turbine components by government and commercial entities.
Determining important design and fabrication properties in EBC systems used for advanced CMC components for high pressure turbine engines and life/failure of such EBC systems and components.
Any applications that use the advanced CMCs, such as aircraft propulsion or land based gas turbines for power generation, require the development of a robust EBC system. The DOD, DOE, and commercial aeroengine manufacturers would benefit from this EBC system lifing software.