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Experiments were conducted to examine the effects of film cooling on a gas turbine engine's high-pressure turbine section. The focus for this effort was in the tip/shroud region of a rotor stage and a high pressure turbine vane. A primary goal was to understand the unsteady flow effects. Attempts were also made to characterize the effects as caused by the fully-cooled rotor stage. Data for this investigation was taken at the U.S. Air Force's Turbine Research Facility (TRF), a transient blowdown facility with instrumentation fitted to a full-scale, high-speed, fully-cooled vane and rotor stage of proprietary design. Measurements of pressure, temperature, and heat flux were taken at flow conditions non-dimensionally matched to actual engine operation.