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Int. J. Turbomach. Propuls. Power 2017, 2(2), 6; doi:10.3390/ijtpp2020006

Hot Streak Evolution in an Axial HP Turbine Stage

Laboratorio di Fluidodinamica delle Macchine, Dipartimento di Energia, Politecnico di Milano, Via Lambruschini, 4, 20158 Milano, Italy
This paper is an extended version of our paper in Proceedings of the European Turbomachinery Conference ETC’12, 2017, Paper No. 182.
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Academic Editor: Marcello Manna
Received: 24 March 2017 / Revised: 24 March 2017 / Accepted: 18 April 2017 / Published: 27 April 2017
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Abstract

This paper presents the results of an experimental study on the evolution of hot streaks generated by gas turbine burners in an un-cooled high-pressure turbine stage. The prescribed hot streaks were directed streamwise and characterized by a 20% over-temperature with respect to the main flow at the stage inlet. The hot streak was injected in four different circumferential positions with respect to the stator blade. Detailed temperature and aerodynamic measurements upstream and downstream of the stage, as well as in-between the blade rows, were performed. Measurements showed a severe temperature attenuation of the hot streaks within the stator cascade; some influence on the aerodynamic field was found, especially on the vorticity field, while the temperature pattern resulted in severe alteration depending on the injection position. Downstream of the rotor, the jet spread over the pitch above the midspan and was more concentrated at the hub. Rotor secondary flows were also enhanced by hot streaks. View Full-Text
Keywords: hot streaks; axial turbine; turbine performance; combustor-turbine coupling hot streaks; axial turbine; turbine performance; combustor-turbine coupling
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This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

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Gaetani, P.; Persico, G. Hot Streak Evolution in an Axial HP Turbine Stage. Int. J. Turbomach. Propuls. Power 2017, 2, 6.

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Int. J. Turbomach. Propuls. Power EISSN 2504-186X Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
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