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Int. J. Turbomach. Propuls. Power 2017, 2(3), 12; doi:10.3390/ijtpp2030012

The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

1
Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, Otto-Berndt-Str. 2, 64287 Darmstadt, Germany
2
Turbine Aerodynamics and Cooling, Rolls-Royce Deutschland, Eschenweg 11, 15827 Blankenfelde-Mahlow, Germany
This paper is an extended version of our paper in Proceedings of the European Turbomachinery Conference, ETC12, 2017, Paper No. 139.
*
Author to whom correspondence should be addressed.
Academic Editor: Giovanna Barigozzi
Received: 10 April 2017 / Revised: 28 July 2017 / Accepted: 21 August 2017 / Published: 25 August 2017
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Abstract

The aerothermal interaction of the combustor exit flow on the first vane row has been examined at the Large Scale Turbine Rig (LSTR) at Technische Universität Darmstadt (Darmstadt, Germany). A baseline configuration of axial inflow and a variation of swirling combustor inflow have been studied. The nozzle guide vane (NGV) featured endwall cooling, airfoil film cooling and a trailing edge slot ejection as well as NGV-rotor wheel space purge flow. CO2 is injected for coolant flow tracing. The results are compared to five hole probe (5HP) measurements. The experiments for the baseline configuration are accompanied by numerical simulations using a passive scalar tracking method to validate the results and study the propagation of the coolant flow. The endwall coolant injection is detected to influence the pressure losses in the NGV. It has an impact on the Trailing Edge (TE) coolant ejection as well. For swirling combustor inflow, increased NGV pressure losses and increased mixing of Rear Inner Discharge Nozzle (RIDN) coolant and main flow is observed. An influence of the clocking position of the swirler to the vane is detected. Additional losses within the NGV row can be assigned to the swirler by means of flow tracing. View Full-Text
Keywords: combustor–turbine interaction; flow tracing; swirl; film cooling; scalar tracking method combustor–turbine interaction; flow tracing; swirl; film cooling; scalar tracking method
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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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MDPI and ACS Style

Werschnik, H.; Schneider, M.; Herrmann, J.; Ivanov, D.; Schiffer, H.-P.; Lyko, C. The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation. Int. J. Turbomach. Propuls. Power 2017, 2, 12.

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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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