On the Effect of Inlet Swirl and Temperature Profiles on the Aero-Thermal Performance of a Heavily Film-Cooled Vane

A linear cascade of high-pressure vanes equipped with a realistic film-cooling configuration has been studied. The aim is to provide an accurate analysis of a heavily cooled high-pressure vane subjected to aggressive inlet swirl. The analyzed vane is characterized by the presence of multiple rows of fan-shaped holes along pressure and suction side while the leading edge is protected by a showerhead system. Numerical simulations have been performed on hybrid unstructured grids using a steady approach with the commercial code ANSYS Fluent®. The transitional kT-kL-ω model by Walters and Cokljat has been selected as turbulence closure. A realistic computational domain that mimic a combustor/vane count of 1:2 has been used. The classical analysis approach with uniform inlet flow has been compared with an approach that takes into account inlet swirl motion considering two clocking positions of such velocity distortion. This latter have been obtained through a non-reacting swirl generator experimented during the EU-funded TATEF2 Project and representative of modern aeroengines. Results highlight the importance of considering realistic boundary conditions for cooling system analysis and quantify the effects of swirl in affecting external heat transfer.