Accurate prediction of film-cooling performance remains a major challenge in turbomachinery. The interaction of turbulent boundary layers, strong pressure gradients, and jet–crossflow mixing generates a wide range of spatial and temporal scales that are not reliably captured by (unsteady) Reynolds-averaged Navier–Stokes (RANS/URANS) methods. While large-eddy simulation (LES) offers the fidelity required to resolve these multi-scale phenomena, wall-resolved LES (WRLES) of realistic turbine components remains prohibitively expensive for routine design workflows. Bridging the gap between predictive accuracy and computational feasibility requires a systematic assessment of wall-modeling strategies in configurations representative of gas-turbine cooling. This work presents a hierarchy of high-fidelity simulations of the canonical 7-7-7 fan-shaped film-cooling hole configuration [1], progressively increasing the complexity to mimic conditions encountered in turbine vanes. First, a baseline WRLES of the flat-plate 7-7-7 configuration is performed to establish a reference database for jet-in-crossflow and near-wall heat transfer [1]. The study is then extended to curved surfaces, introducing streamwise pressure gradients that influence coolant jet attachment, mixing, and effectiveness. Finally, the methodology is applied to a generic nozzle guide vane (NGV) profile section equipped with cooling-holes, thereby providing a step toward application-relevant geometries. The WRLES will serve as a baseline. Established wall-modeling approaches based on RANS and Detached Eddy Simulations will be compared with the reference simulations to assess their limitations. The comparison will focus on adiabatic film-cooling effectiveness, heat-transfer coefficients, and near-wall turbulence statistics. By systematically quantifying the deviations between wall-modeled approaches and WRLES, this study aims to identify the physical mechanisms responsible for model breakdown in film-cooling flows. The resulting high-fidelity dataset provides a foundation for assessing alternative near-wall scalings and turbulence-closure assumptions in strongly non-equilibrium boundary layers, thereby informing future developments in wall modeling for turbomachinery applications. REFERENCES [1] Schroeder, R.P., Thole, K.A., 2022. Adiabatic Effectiveness Measurements for a Baseline Shaped Film Cooling Hole. J. Turbomach. 144. https://doi.org/10.1115/1.4055271