Flow field and thermal film cooling parameters are analysed and compared for different blowing ratios
for a 10°-10°-10° laidback fan-shaped film cooling hole geometry with an inclination angle of 35° and a
wide spacing of P/D = 8 to ensure the absence of jet interaction. The influence of the coolant ejection
on the aerodynamics of the hot gas is investigated and stationary as well as non-stationary vortex
structures are identified. The present study uses an existing test rig at the Institute of Thermal
Turbomachinery (ITS) at the Karlsruhe Institute of Technology (KIT) designed for generic film cooling
studies with high spatial resolution applying stereoscopic particle image velocimetry (SPIV) as well
as infrared thermography (IRT). Operating conditions of hot gas and cooling air inlet and exit are
uniquely compliant with scaled engine-realistic conditions, including temperature ratio, turbulence
intensity and coolant flow configuration
