Table of Contents
Int. J. Turbomach. Propuls. Power, Volume 4, Issue 3 (September 2019)
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Cover Story (view full-size image) Rotor tip film cooling is investigated at the Large Scale Turbine Rig, which is a 1.5-stage axial [...] Read more. 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 at a squealer-type blade tip with cylindrical pressure-side film cooling holes is obtained. The effect of turbine inlet swirl 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. View this paper.