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Future gas turbine engines will operate at higher gas temperatures andconsequentially hot-section components such as blades, vanes and combustors,will be subject to higher thermal radiation fluxes than today. Current thermalbarrier coating materials are translucent over the spectral region of the heatflux so future coatings will also have to provide a barrier to thermalradiation. The effects of optical absorption and scattering properties ofcoating materials on the temperatures and heat fluxes through coatings areexplored using a two-flux heat transfer model, and promising combinations areidentified that reduce the coating-alloy interface temperatures. Lowerinterface temperatures occur for thickness normalized absorptions of$\overline{\kappa} L$ $>$1. The effect of both a narrow and a broad bandspectrally selective absorbing Gd${_2}$Zr${_2}$O$_{7}$ based coating materialsare then studied. These show that large values of the product of the normalizedabsorption length and the spectral width of the absorption are required tosignificantly decrease the radiative heat transport through a coating. Theresults emphasize the importance of enhancing the optical absorption of thenext generation barrier materials as a strategy to increase gas turbine engineefficiency by decreasing compressor bleed air cooling requirements.

Optical Absorption Effects in Thermal Radiation Barrier Coating Materials