This parametric study investigates the feasibility of cooling of silicon nitride plates with thermal/environmental barrier coatings (TBC/EBC) for high-temperature gas turbine components. Heat transfer analysis coupled with coolant flow analysis, using the ESC task of 1-DEAS package, has been conducted for modeling a flat ceramic plate with changing airflow parameters as well as coating configurations. The parametric study was conducted by varying the airflow rate, inlet air temperature, passage surface roughness, and coating configurations including thickness and thermal conductivity. The results include ceramic material and air temperatures, cooling effectiveness, heat transfer coefficient on cooling passage surfaces and heat convected to air. Results with respect to the study key design parameters include variation of ceramic material and air temperatures, cooling effectiveness, heat transfer coefficient on cooling passage surfaces, and heat convected to air. The potential for air-cooled ceramic gas turbine components was demonstrated from the thermal and fluid flow standpoints. Additional work is necessary to further investigate the structural and material aspects for ceramic gas turbine components under engine operating conditions.
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