ABSTRACT To maintain acceptable turbine airfoil temperatures, filmcooling is typically used whereby coolant, extracted from the compressor, is injected through component surfaces. In manufacturing a turbine, the first stage vanes are cast in either single airfoils or double airfoils. As the engine is assembled, these singlets or doublets are placed in a turbine disk in which there are inherent gaps between the airfoils. The turbine is designed to allow outflow of high pressure coolant rather than hot gas ingestion. Moreover, it is quite possible that the singlets or doublets become misaligned during engine operation. It has also become of interest to the turbine community as to the effect of corrosion and deposition of particles on component heat transfer. This study uses a largescale turbine vane in which the following two effects are investigated: the effect of a mid-passage gap on endwall filmcooling and the effect of roughness on endwall film-cooling. The results indicate that the mid-passage gap was found to have a significant effect on the coolant exiting from the combustorturbine interface slot. When the gap is misaligned, the results indicate a severe reduction in the film-cooling effectiveness in the case where the pressure side endwall is below the endwall associated with the suction side of the adjacent vane
