With the ever increasing operating temperatures of gas turbine engines, the surface cooling of hot section components remains a primary consideration in propulsion system design. At the same time, numerical tools are being used more extensively for hot-section flow-path design. Recognizing the need for detailed data to help develop and validate these numerical tools, the present study focuses on characterizing near-wall mixing and heat transfer in a canonical 2D slot film cooling configuration. The lack of comprehensive and detailed experimental film cooling data under realistic temperature and blowing ratio conditions has led the authors to develop and implement a unique experimental facility that will allow measuring velocity and temperature profiles as well as surface temperatures and heat transfer at the wall under adiabatic and isothermal conditions. This hot wind tunnel facility provides optical access for Laser Doppler Velocimetry (LDV) near the wall and wall surface temperature distribution with infrared (IR) thermography. In addition to these non-intrusive diagnostics, the gas-phase temperature is measured with a minimally intrusive micro-thermocouple probe with fast response time and high frequency sampling. The performance of selected film cooling effectiveness scaling laws is analyzed. The thermal and momentum mixing of the film described in terms of temperature and velocity profiles and associated statistics. These detailed measurements are hoped to provide guidance and validation for CFD model developers.

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