A critical problem in high pressure turbine of modern engine is the vane and blade reliability as it is subjected to high thermal constraints. Actually the flow entering the turbine presents high level of stagnation temperature as well as great radial and circumferential temperature gradients. Considering that a small variation of the blade temperature leads to a strong reduction of its life duration, accurate numerical tools are required for prediction of blade temperature. Because of the complexity of the flow within a turbomachine, the blade wall temperature is heterogeneous and a fluid/solid coupling may improve wall temperature prediction. This study presents a coupling strategy of a Navier Stokes flow solver and a conduction solver to predict blade temperature. Firstly, the method is applied to the well documented NASA C3X configuration. The influence of the fluid/solid interface boundary condition is studied with regards to the wall temperature and heat flux prediction as well as to the computational efficiency. The predicted wall temperature is in good agreement with the experimental results. The method is finally applied to the prediction of the blade temperature of a high pressure turbine representative of a modern engine. Adiabatic and coupled results are compared and discussed.

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