N&R ENGNERING MGT SUPPORT SVCS — National Aeronautics and Space Administration SBIR Phase I: A1

Description

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 lead to gains in specific fuel consumption (SFC) by allowing higher operating temperatures, reductions in required cooling, and reductions in vehicle weight. Thermal barrier and environmental barrier coatings (TBCs and EBCs) will play a crucial role in future advanced 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.nbsp; The proposed work will develop a software tool that will facilitate the probabilistic/reliability analysis of the CMC/EBC interface. This software tool will compute input sensitivities of the CMC/EBC interface and propagate uncertainties to component models of turbomachinery parts (vanes/blades) with complex geometries.