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Experimental Investigation of Rotor Tip Film Cooling at an Axial Turbine with Swirling Inflow Using Pressure Sensitive Paint

Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, Otto-Berndt-Str. 2, 64287 Darmstadt, Germany
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This paper is an extended version of our paper published in Proceedings of the European Turbomachinery Conference, ETC13, Lausanne, Switzerland, 8–12 April 2019; Paper No. 236.
Int. J. Turbomach. Propuls. Power 2019, 4(3), 23; https://doi.org/10.3390/ijtpp4030023
Received: 10 May 2019 / Revised: 24 July 2019 / Accepted: 25 July 2019 / Published: 1 August 2019
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 η at a squealer-type blade tip with cylindrical pressure-side film cooling holes is obtained. The effect of turbine inlet swirl on η 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 η 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, η 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 η . View Full-Text
Keywords: combustor–turbine interaction; rotor blade tip; swirl; film cooling; pressure sensitive paint combustor–turbine interaction; rotor blade tip; swirl; film cooling; pressure sensitive paint
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Wilhelm, M.; Schiffer, H.-P. Experimental Investigation of Rotor Tip Film Cooling at an Axial Turbine with Swirling Inflow Using Pressure Sensitive Paint. Int. J. Turbomach. Propuls. Power 2019, 4, 23.

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