The present study is devoted to the assessment of several heat transfer coefficient correlations applied to multi-perforated walls used in aeronautical combustors. The conjugate heat-transfer problem was solved through the coupling of the thermal code AVTP for the solid wall and the large-eddy simulation solver AVBP for the flow evolution. This numerical approach is applied to a realistic multi-perforated wall geometry. The flow conditions have been chosen in order to be representative of an operating point reproducing the chamber conditions for a specific take-off configuration considered during bench testing of the combustion chamber of an engine under development. This work highlights the potential of such a coupling strategy in the description of heat exchange distribution for combustor liners. At the injection side of the multi-perforated wall, a correction of the promising heat exchange model by Cottin [13] is suggested.