Short duration studies of heat transfer and film cooling effectiveness were made using a shock tunnel and a blowdown facility. In these short duration tests, flow and temperature modeling were used to determine the Nusselt number for a given set of Reynolds number, Mach number and temperature ratios representative of turbine operating conditions. Shock tunnel techniques were used to determine the isothermal effectiveness of coolant injection through slots and patterns of holes located in flat and curved surfaces. In the turbine blowdown facility, the Nusselt number at the shroud (engine seal) was determined for a wide range of operating conditions. Strong secondary flow and centrifugal effects were found to increase the Nusselt number significantly over the level associated with one-dimensional convectional heat transfer for a turbulent flow. Using shock tunnel and uncooled turbine data, a particular film cooling configuration was selected for the turbine shroud under investigation. The investigation on the film cooled stationary shroud gave encouraging results as to the applicability of two-dimensional film cooling data to the three-dimensional heat transfer at the shroud and as to the use of film cooled shrouds in advanced turbines.
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