Thermal Barrier Coating Environmental Durability Enhancement (CMAS) Navy SBIR FY2006.1 Sol No.: Navy SBIR FY2006.1 Topic No.: N06-032 Topic Title: Thermal Barrier Coating Environmental Durability Enhancement (CMAS) Proposal No.: N061-032-0286 Firm: Directed Vapor Technologies International, Inc. 2 Boar's Head Lane Charlottesville, Virginia 22903 Contact: Derek Hass Phone: (434) 977-1405 Web Site: www.directedvapor.com Abstract: Advanced thermal barrier coating systems are desired for naval gas turbine engines. These coatings will increase the durability of hot-section engine components to significantly improve the time "on-wing", safety and readiness of these engines. In this work, we will use novel coating synthesis techniques that enable the deposition of advanced compositions and microstructures to achieve a comprehensive thermal barrier coating system that provides vastly improved resistance to damage from CMAS. A low cost, high throughput processing approach for the application of this TBC system is also envisioned. The proposed Phase I effort will identify CMAS protection concepts that are anticipated to meet the performance goals at both current and future engine operating temperatures and demonstrate the feasibility of applying these concepts using our advanced processing techniques. The successful completion of the Phase I work will lead to a follow-on Phase II program focused on down-selecting candidate approaches for optimization and applying the new coating onto real aircraft components. Success in this objective will offer the military a pathway toward production implementation of these advanced coatings and the new deposition processing capabilities required for applying coatings of this type onto engine components. Benefits: This research is anticipated to result in a thermal barrier coating system that provides unprecedented protection from CMAS induced failures. This will help enable the realization of many advanced gas turbine engine designs leading to thrust improvement or specific fuel consumption reduction for current turbine engines. These advances will not only benefit military engines, but also commercial and industrial gas turbines. In addition, the innovative approach proposed here will reduce the time and expense for refurbishing and repairing blades during engine overhauls, thus improving military readiness and reducing the cost of maintaining commercial aircraft. Return