Film cooling remains a critical tec

Film cooling remains a critical technique for cooling turbinecomponents in the “hot section” of gas turbine engines. Consequently, there are numerous studies of various parameter effectson film cooling performance, with many new studies being published each year. Decreased temperatures for turbine componentsare also achieved by incorporating thermal barrier coatings(TBCs) on the external surfaces of the turbine components. ATBC, which typically has a thermal conductivity that is an orderof magnitude smaller than the metal alloy body of the turbinecomponents, can significantly reduce the “metal temperature” ofthese components. In practice, the operating temperature of turbine components is a function of the internal cooling, externalfilm cooling, and TBC used. However, there are very few studiesof the integrated effects of internal/external cooling and TBC.Another consideration when designing turbine cooling configurations is the degradation that occurs over the lifetime of the components. In particular, contaminants in the intake air or fuel canlead to deposition of contaminants on turbine components, resulting in rougher walls and the possible blockage of coolant holes.The review paper by Hamed et al. [1] describes the experimentalbackground and predictive tools for estimating erosion and deposition in turbomachinery components and provides examples ofdeposition on turbine components from different contaminants.Experimental simulations of the depositions that might occur dueto contaminant from syngas have been conducted by Crosby et al.[2] and Ai et al. [3]. For these studies a special facility was