To predict the aerothermal behaviour of transpiration cooled gas turbine components, a multiscale approach based on the homogenization method of periodic material structures is developed. This method allows to calculate effective equivalent thermophysical properties either for each layer or for the multilayer of superalloy, bondcoat and thermal barrier coating. From the 3-D conjugate fluid flow and heat transfer analysis, the stationary state is extracted and transferred to the microscale unit cell discretized by finite elements. Effective permeabilities of different designs of the cooled multilayer are determined and analyzed in detail for the TBC layer. For two efficient shaped cooling designs different hot gas velocities and blowing rates of the cooling gas are analyzed. The influence of the corresponding aerothermal results on the effective thermal conductivities of each monolayer and the multilayer are then discussed for both shaped cooling configurations.

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