Abstract
In the present study the film cooling performance in terms of the adiabatic film cooling effectiveness on the scaled suction side model of an actual guide vane was investigated. An infrared thermography measurement system was used to determine highly resolved distribution of models surface temperature. Two different film cooling hole configurations were investigated: a single row of fanshaped holes and a double row of cylindrical holes in staggered arrangement. The influence of blowing rate and mainstream turbulence level on effectiveness was investigated in a wide range for both of the injection configurations.
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