Abstract
Modern low-emission combustor concepts, such as lean combustion, pose challenges to turbine designers, among them a flatter temperature profile with increased thermal load to the endwalls and a three-dimensional inflow. The complexity of the flowfield make numerical investigations and rules for turbine thermal design under swirling inflow a delicate task. An experimental investigation is conducted to evaluate a film-cooling design for a stator endwall in respect to its robustness to swirling combustor inflow and its limitations. The experiments were conducted at the Large Scale Turbine Rig at the Technische Universität Darmstadt, operating at low-Mach-number, cold-flow conditions. A swirler module is used to generate an engine-realistic whirl-angle distribution with averaged values of 14 deg in the upper main annulus and 11 deg in the lower annulus. Spatially resolved Nusselt numbers and film-cooling effectiveness data are acquired by infrared thermography with the auxiliary wall method for swirling inflow. The comparison to the axial inflow baseline case highlights the robustness of the design. Swirling inflow increases Nusselt numbers until at 2.9% injection the level remains similar to the baseline, whereas film-cooling effectiveness is reduced by 30%.
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