Abstract
The normal spectral emittance of a thermal barrier coating system developed at the National Aeronautics and Space Administration Lewis Research Center was measured. This emittance was transformed into the hemispherical total emittance and was correlated to the ceramic coating thickness and temperature using multiple-regression curve-fitting techniques. Equations were obtained which can easily be used by a designer to calculate the coating system hemispherical total absorptance and emittance. The system is highly reflective and therefore can significantly reduce radiation heat loads on cooled gas turbine engine components.
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