Conjugate Heat Transfer in a Turbine Vane and Thermal Barrier Coating (original) (raw)

2018, Proceedings of the 5th International Conference of Fluid Flow, Heat and Mass Transfer (FFHMT'18)

The high pressure (HP) turbine is subject to high temperature inlet flow non-uniformities resulting from the combustion chamber. This paper presents a new fluid-solid interface treatment for conjugate heat transfer (CHT) applied to two configurations of interest in the design of high pressure turbine blades to accurately estimate the temperature in the blade. The computational fluid dynamics (CFD) solver elsA, and a solid conduction solver, Zset, both developed at the French Aerospace Lab (ONERA), have been used for all simulations. Two problems, typical of a high pressure turbine, are studied: (1) a turbine vane with a hot-streak to present the validity of the coupling process during the design phase of a blade turbine. Results will be compared to CFD only simulation and experimental data. (2) A conjugate heat transfer simulation with a thermal barrier coating (TBC) on the solid side has also been studied. The TBC is known to better withstand high temperature but taking it into account in a CHT simulation is really difficult because of the strong fluid-solid interaction. This two configurations have really different characteristics in a coupled problem based on the Biot number, and the coupled methodology presented attempt to solve both of them using a Dirichlet-Robin interface condition.