Numerical simulation of heat transfer distribution over the surface of internally cooled nozzle guide vane in an annular cascade

A key factor in improving turbine efficiency is higher turbine front temperature. Accurate simulation of the heat transfer coefficient remains a challenge for the prediction of external heat transfer on nozzle guide vane in aero turbine engine. In this paper the shear stress transport turbulence model results are compared against the measured data from Hylton et al., as well as the predictions from a 2-D boundary layer code-STAN5. The heat transfer distribution over the surface of two internally cooled nozzle guide vanes in a transonic annular cascade are investigated. Computational fluid dynamics model of the MARK II vane and the C3X vane were built and several modeling parameters are varied in order to obtain good agreement with the measured data. In addition, the influence of the exit Mach number and the turbulence intensity to the heat transfer of nozzle guide vane were invested.