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DETAILED EXAMINATION OF A MODIFIED TWO-STAGED MICRO GAS TURBINE COMBUSTOR

[+] Author and Article Information
Andreas Schwärzle

German Aerospace Center (DLR), Institute of Combustion Technology, Pfaffenwaldring 38-40, 70569 Stuttgart, Germany
andreas.schwaerzle@dlr.de

Thomas Monz

German Aerospace Center (DLR), Institute of Combustion Technology, Pfaffenwaldring 38-40, 70569 Stuttgart, Germany
thomas.monz@dlr.de

Andreas Huber

German Aerospace Center (DLR), Institute of Combustion Technology, Pfaffenwaldring 38-40, 70569 Stuttgart, Germany
andreas.huber@dlr.de

Manfred Aigner

German Aerospace Center (DLR), Institute of Combustion Technology, Pfaffenwaldring 38-40, 70569 Stuttgart, Germany
manfred.aigner@dlr.de

1Corresponding author.

ASME doi:10.1115/1.4037749 History: Received July 05, 2017; Revised July 18, 2017

Abstract

Jet-stabilized combustion is a promising technology for fuel flexible, reliable, highly efficient combustion systems. The aim of this work is a reduction of NOx emissions of a previously published two-stage MGT combustor, where the pilot stage of the combustor was identified as the main contributor to NOx emissions. The geometry optimization was carried out regarding the shape of the pilot dome and the interface between pilot and main stage in order to prevent the formation of high temperature recirculation zones. Both stages have been run separately to allow a detailed understanding of the flame stabilization within the combustor, its range of stable combustion, the interaction between both stages and the influence of the modified geometry. The flame was analyzed in terms of shape, length and lift-off height, using OH* chemiluminescence images. Emission measurements for NOx and CO emissions were carried out. At a global air number of 2, a fuel split variation was carried out from 0 (only pilot-stage) to 1 (only main stage). The modification of the geometry lead to a decrease in NOx and CO emissions throughout the fuel split variation in comparison with the previous design. Unsteady RANS simulations were carried out at fuel splits of 0.93 and 0.78, respectively, using the DLR in-house code THETA with the k-w SST turbulence model and the DRM22 detailed reaction mechanism. The numerical results showed a strong influence of the recirculation zones on the pilot stage reaction zone.

Copyright (c) 2017 by ASME
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