SBIR-STTR Award

Although ceramic matrix composites (CMCs) have been a material of interest for gas turbine components with operating temperatures 100-150 °C higher than typical superalloy materials, the temperature capability of CMCs is still limited by the lack of environmental durability of coatings. One of the main degradation mechanisms at high temperature (>1200 °C) is due to calcia-magnesia-alumina-silicate (CMAS) deposit. Under this SBIR program, QuesTek Innovations LLC will utilize its expertise in Integrated Computational Materials Engineering (ICME) and Materials by Design® approach to design multilayer thermal-environmental barrier coatings (T-EBCs) with improved environmental durability for enhanced performance of advanced CMC engine components. While EBC such as ytterbium disilicate is promising for protection against volatilization of thermally grown oxide, it is ineffective as a long-term protection against CMAS attack. Phase I will focus on development of a multiphase TBC with desired properties such as high reactivity with CMAS, high fracture toughness, low thermal conductivity and small coefficient of thermal expansion. This multiphase TBC acts as sacrificial layer by promoting reactive crystallization to mitigate CMAS infiltration and protect underlying materials from CMAS attack. QuesTek will leverage computational thermodynamic models and databases to predict CMAS-coating interactions and develop a CMAS-resistant multilayer T-EBC capable of extended performance at temperatures at or above 1482°C by the end of Phase II. The proposed integrated computational and experimental approach will accelerate material and architecture design to balance multiple competing performance requirements by reducing the need for time-consuming experiments. Potential NASA Applications (Limit 1500 characters, approximately 150 words): Potential NASA applications will be propulsion components (nozzles, turbine vanes and blades, combustor liner, exhaust nozzle) for subsonic and supersonic fixed and rotary wing aircrafts and combustor panel components on hypersonic vehicles. Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words): Potential non-NASA applications will be turbine components in future civilian aircraft propulsion systems (e.g. future generations of turbofan engines similar to CFM LEAP and GE9X) and turbine components in industrial gas turbine plants. Duration: 6

Although ceramic matrix composites (CMCs) have been a material of interest for gas turbine components with operating temperatures 100-150 °C higher than typical superalloy materials, the temperature capability of CMCs is still limited by the lack of environmental durability of coatings. One of the main degradation mechanisms at high temperature (>1200 °C) is due to calcia-magnesia-alumina-silicate (CMAS) deposit. Under this SBIR Phase II program, QuesTek Innovations LLC will continue leveraging its expertise in integrated computational materials engineering (ICME) to design multilayer thermal-environmental barrier coatings (T-EBCs) with improved environmental durability for enhanced performance of CMC engine components. QuesTek will develop/apply its advanced computational thermodynamic models and databases to predict CMAS-coating interactions and design a CMAS-resistant multilayer oxide coating system capable of extended performance to help increase CMC operating temperatures to or above 1482 °C. Partnership with Prof. David Poerschke at University of Minnesota (UMN), an expert in T-EBC material and CMAS-induced degradation, will continue in Phase II. UMN will also perform targeted experiments to process, test, characterize, and validate the elements of the designed coating subsystems. Such integrated computational and experimental approach proposed by the QuesTek-UMN team could enable intelligent and accelerated design of T-EBC materials/architecture with balanced performance requirements by reducing the need for time-consuming experiments. Raytheon Technologies Research Center (RTRC) has provided a Letter of Support for the Phase II program (attached at the end of the document), which will provide industrially relevant guidance on the technical tasks and assist in future commercialization of the developed materials/technology. Potential NASA Applications (Limit 1500 characters, approximately 150 words): Potential NASA applications will be propulsion components (nozzles, turbine vanes and blades, combustor liner, exhaust nozzle) for subsonic and supersonic fixed and rotary wing aircrafts, and combustor panel components on hypersonic vehicles. Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words): Potential non-NASA applications will be turbine components in future civilian aircraft propulsion systems (e.g., future generations of turbofan engines similar to CFM LEAP and GE9X), and turbine components in industrial gas turbine plants. Duration: 24