Affordable CMAS -Resistant Thermal Barrier Coatings Navy STTR FY2012.A Sol No.: Navy STTR FY2012.A Topic No.: N12A-T019 Topic Title: Affordable CMAS -Resistant Thermal Barrier Coatings Proposal No.: N12A-019-0140 Firm: QuesTek Innovations LLC 1820 Ridge Avenue Evanston, Illinois 60201 Contact: Abhijeet Misra Phone: (847) 425-8233 Web Site: www.questek.com Abstract: A notable failure mechanism in thermal barrier coatings (TBCs) is the attack by calcium-magnesium-alumino silicate (CMAS) deposits resulting from the ingestion of siliceous minerals with the intake of air. Existing TBC systems such as yittria partially stabilized zirconia (YSZ) are highly susceptible to CMAS infiltration. In this STTR program, QuesTek Innovations LLC, a leader in the field of computational materials design, proposes to expand its computational Materials by Designr technology by developing a "design toolkit" that enables the subsequent design and development of novel CMAS-resistant, high performance thermal barrier coatings for aeroengine components (e.g., turbine blades). The focus of the Phase I program will be the development of the ICME (Integrated Computational Materials Engineering) based materials design toolkit, especially robust thermodynamic descriptions that forms the backbone for almost all ICME tools. Additionally, relevant process-structure-property tools that are necessary to enable design of high performance TBCs will be implemented. These tools will be exercised to design a CMAS-resistant TBC composition and microstructure. To support design of high performance CMAS-resistant TBCs, QuesTek will partner with a leading TBC expert as university partner. Furthermore, this program will involve a leading turbine engine manufacturer, to ensure a strong commercialization path for the coating solutions. Benefits: CMAS-resistant thermal barrier coatings will alleviate premature thermomechanical fatigue failure of aeroengine components such as blade alloys and significantly reduce maintainence costs, while improving fleet readiness and increased time on wing. Furthermore, minimizing CMAS-induced damage will permit increase in the service temperature of the coated aeroengine blade alloys that would result in enhanced efficiency and provide superior performance benefits at reduced fuel costs. Successful design and development of coating solutions following ICME protocol will provide the project stakeholders (NAVY) considerable cost savings. In summary, the proposed thermal barrier coating systems will enable development of more efficient, longer-life aerospace turbines representing a revolutionary performance increase and potential cost savings for both commercial and military aerospace applications. Return