This paper presents a numerical investigation of the conjugate heat transfer (CHT) to calculate the steady state aerodynamic and thermal characteristics of a film cooled gas turbine vane. The commercial code ANSYS FLUENT 15.0 is applied as the numerical tool. The turbine configuration selected from NASA Energy Efficient Engine program consists of 46 vanes with two impingement baffles in forward and aft cavities. The periodic boundary condition is used to reduce the calculation cost while maintaining a reasonable accuracy of the numerical results.
Using the commercial software ANSYS ICEM 15.0, steady simulations are based on a structured grid method with the finite volume technique. In the numerical simulations, two two-equation turbulence models, i.e. the Realizable k-epsilon (k-ε) and Shear Stress Transport k-omega (SST k-ω), and a four-equation turbulence model, i.e. the V2-F model, are used. To estimate the numerical strategy, the calculated results of the Mach number distributions obtained by the three turbulence models are compared with the experimental data of Timko (NASA CR-168289). Then the detailed flow and heat transfer characteristics, including the cooling effectiveness, heat transfer coefficient distributions on the vane’s surfaces, static pressure distributions along three span-wise lines and total pressure distributions in the cascade passage are predicted. Through the comparison of the numerical results obtained under adiabatic and CHT conditions, the influences of heat conduction on vane cooling effect are discussed.