Abstract: The aerothermal performance of a typical turbine blade three-pass turbulated cooling circuit geometry was investigated in a 10X plexiglass test model. The model closely duplicated the blade’s ...

Abstract: A warm (315°C) wind tunnel test facility equipped with a linear cascade of film cooled vane airfoils was used in the simultaneous determination of the local gas side heat transfer ...

Abstract: Aerodynamic flow path losses and turbine airfoil gas side heat transfer are strongly affected by the gas side surface finish. For high aero efficiencies and reduced cooling requirements, airfoil ...

Abstract: Heavy-duty gas turbine combustion systems have a “reverse flow” combustion-cooling air network. High-temperature gradients have been observed in some combustion liners around the plain holes, or ...