Previous tests simulating the effects of TBC (thermal barrier coating) on an internally and film cooled model turbine vane showed that the insulating effects of TBC dominate over variations in film cooling geometry and blowing ratio. In this study overall and external effectiveness were measured using a matched Biot number model vane simulating a TBC of thickness 0.6d, where d is the film cooing hole diameter. This was a 35% reduction in thermal resistance from previous tests. Overall effectiveness measurements were taken for an internal cooling only configuration, as well as for three rows of showerhead holes with a single row of holes on the pressure side of the vane. This pressure side row of holes was tested both as round holes and as round holes embedded in a realistic trench with a depth of 0.6 hole diameters. Even in the case of this thinner TBC, the insulating effects dominate over film cooling. In addition, using measurements of the convective heat transfer coefficient above the vane surface, and the thermal conductivities of the vane wall and simulated TBC material, the overall effectiveness of the thin TBC thickness can be predicted from the thick TBC data, for an internal cooling only configuration.
Effects of TBC Thickness on an Internally and Film Cooled Model Turbine Vane
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Stewart, WR, Kistenmacher, DA, & Bogard, DG. "Effects of TBC Thickness on an Internally and Film Cooled Model Turbine Vane." Proceedings of the ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. Volume 5B: Heat Transfer. Düsseldorf, Germany. June 16–20, 2014. V05BT13A058. ASME. https://doi.org/10.1115/GT2014-27117
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