%0 Journal Article
%T Experimental Investigation of Rotor Tip Film Cooling at an Axial Turbine with Swirling Inflow Using Pressure Sensitive Paint£¿
%J International Journal of Turbomachinery, Propulsion and Power | An Open Access Journal from MDPI
%D 2019
%R https://doi.org/10.3390/ijtpp4030023
%X Rotor tip film cooling is investigated at the Large Scale Turbine Rig, which is a 1.5-stage axial turbine rig operating at low speeds. Using pressure sensitive paint, the film cooling effectiveness ¦Ç at a squealer-type blade tip with cylindrical pressure-side film cooling holes is obtained. The effect of turbine inlet swirl on ¦Ç is examined in comparison to an axial inflow baseline case. Coolant-to-mainstream injection ratios are varied between 0.45% and 1.74% for an engine-realistic coolant-to-mainstream density ratio of 1.5. It is shown that inlet swirl causes a reduction in ¦Ç for low injection ratios by up to 26%, with the trailing edge being especially susceptible to swirl. For injection ratios greater than 0.93%, however, ¦Ç is increased by up to 11% for swirling inflow, while for axial inflow a further increase in coolant injection does not transfer into a gain in ¦Ç . View Full-Tex
%U https://www.mdpi.com/2504-186X/4/3/23