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DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.140
page 18

Andreas Lerch
Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, 64287 Darmstadt, Germany

Heinz-Peter Schiffer
Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, 64287 Darmstadt, Germany


The adiabatic film cooling effectiveness on the surface of a symmetrical blade model was measured for eight cylindrical, 59° inclined cooling holes. The holes were fed with different flow types using a cylindrical leading-edge channel. Two configurations were compared: on one hand, a leading-edge channel flow without swirl (datum configuration), using a sharp-edged inlet; on the other hand a new cyclone cooling configuration with positive swirl. The experiments were carried out using the calibrated ammonia diazo technique. The blowing ratios were varied between 0.6 and 1.2, and the film cooling discharge was set to either 20% or 50%. For all these operation points, multiple experiments were conducted and combined using a weighting average method to produce a high fullrange resolution. The lateral and area-averaged adiabatic effectiveness is presented up to 45Ddownstream of the cooling holes. The measurements show a higher area-averaged effectiveness immediately downstream of the cooling holes when using the cyclone cooling configuration. This is due to non-symmetric flow structures inside the cooling holes. Further downstream, however, it decreases faster. With a low film cooling discharge and rising blowing ratios, these effects are more pronounced.

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