Coated Ceramic Matrix Composite (CMC) Low Pressure Turbine (LPT) Blade Development

The objective of this Phase I SBIR is to assess feasibility of developing, validating and marketing a methodology and software for timely and cost effective implementation of advanced Ceramic Matrix Composite CMC technology in the design and life prediction of hot section flow path CMC components, such as vanes, with and without environmental barrier coatings. Besides providing an immediately needed tool for JSF, VAATE and IHPTET, the product will be readily marketable to military and industrial gas turbine engine manufacturers. The R&D effort will directly build upon the research already performed by RAI and other organizations under various DoD and NASA funded programs.  Specifically, the effort will focus on developing and validating a mechanism based (mechanistic) modeling method to describe deformation and damage behavior of CMCs and EBCs under general multiaxial stress states, severe thermal gradients, and engine environment conditions. The models will be validated against benchmark and sub-element test data involving three dimensional stress states.  Predictions will be compared with experimental measurements to assess the modeling approach and feasibility for a comprehensive methodology development in Phase II.  The main focus of the development will be on a SiC/SiC CMC selected by Pratt & Whitney (PW).  However, the models will be applicable to a broader variety of CMCs. BENEFIT: Due to the proliferation in potential applications of ceramic matrix composites in military and commercial aerospace engines and in industrial gas turbine industries, the proposed dual-use high technology product has an immediate and expanding market.  RAI will market the methodology, the software and technical expertise (services) to these and other industries.