Bogard, David G.2011-07-112017-05-112011-07-112017-05-112011-05May 2011http://hdl.handle.net/2152/ETD-UT-2011-05-3427textComputations were run to study heat transfer coefficient augmentation with film cooling for a simulated gas turbine blade leading edge. The realizable k-[epsilon] turbulence model (RKE) and Shear Stress Transport k-[omega] turbulence model (SST) were used for the computational simulations. RKE computations completed at a unity density ratio were confirmed to be consistent with experimental measurements conducted by Yuki et al.(1998) and Johnston et al. (1999) whereas SST computations exhibited significant discrepancies. Moreover the effect of the density ratio on heat transfer coefficient augmentation was studied because experimental measurements of heat transfer coefficient augmentation with film cooling are generally constrained to unity density ratio tests. It was shown that heat transfer coefficient augmentation can be simulated using unity density ratio jets, but only when scaled with the momentum flux ratio of the coolant jets.application/pdfengFilm coolingGas turbineTurbine bladeHeat transfer coefficient augmentationCFDRANS simulationsTurbulencethesis2011-07-112152/ETD-UT-2011-05-3427