Conjugate Calculation of Gas Turbine Vanes Cooled with Leading Edge Films

Conjugate calculation methodology is used to simulate the C3X gas turbine vanes cooled with leading edge films of “shower-head” type. By comparing calculated results of different turbulence models with the measured data, it is clear that calculation with the transition model can better simulate the flow and heat transfer in the boundary layers with leading edge film cooling. In the laminar boundary layers, on the upstream suction side, the film cooling flow presents 3D turbulent characteristics before transition, which quickly disappear on the downstream suction side owing to its intensified mixing with hot gas boundary layer after transition. On the pressure side, the film cooling flow retains the 3D turbulent characteristics all the time because the local boundary layersʹ consistent laminar flow retains a smooth mixing of the cooling flow and the hot gas. The temperature gradients formed between the cooled metallic vane and the hot gas can improve the stability of the boundary layer flow because the gradients possess a self stable convective structure.