Lower pressure drop turbine blade trailing-edge cooling configuration

Abstract

Numerical results for a proposed turbine blade trailing-edge cooling configuration are presented. This proposed configuration is meant to result in the same or higher heat transfer performance but with a reduced pressure drop through the passage. The most common trailing-edge cooling configuration is composed of circular pin fin which increases heat transfer due to increased turbulence levels. The configuration proposed in the present investigation is based on short flat plate fins and the heat transfer enhancement is based on the constant restart of a laminar boundary layer over the staggered plates arrangement. This arrangement will produce less turbulence and therefore lower pressure drop. The number of plates necessary to result in the same level of heat transfer as the circular pin fins is determined and the pressure losses between the two configurations are compared. The proposed configuration results in reduced losses and lower cooling air pumping power.