Modern gas turbines require an active cooling system with fluid taken from the compres-
sor to withstand the high turbine inlet temperature. CFD is a useful tool to estimate
the effects of different cooling configurations on the blade aerodynamics and the thermal
loads. However, this usually requires resolving every cooling hole with a high number of
grid cells. To reduce the computational cost of such simulations, a reduced order model
using source terms was implemented in TRACE. Different variants are tested on a cylin-
drical and a laid back fan shaped cooling hole to address issues with accuracy and grid
dependency known from the literature. Additionally, two different turbulence and heat
flux model combinations are compared to each other. Overall, a differential Reynolds
Stress Model with an algebraic heat flux model combined with the simplest approach to
modeling film cooling holes, introducing a constant source term at the wall, provided the
best results for the considered geometries and blowing ratios. The different strategies to
improve the predictions were only able to provide a benefit for some of the cases, while
usually having a detrimental effect in other cases
