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research-article

Large eddy simulation and experimental analysis of combustion dynamics in a gas turbine burner

[+] Author and Article Information
Daniel Moëll

Siemens Industrial Turbomachinery AB, Finspong SE-612 83, Sweden
daniel.moell@siemens.com

Andreas Lantz

Division of Combustion Physics, Lund University, PO Box 118, SE-221 00 Lund, Sweden
andreas.lantz@siemens.com

Karl Bengtson

Siemens Industrial Turbomachinery AB, Finspong SE-612 83, Sweden
karl.bengtson@siemens.com

Daniel Lörstad

Siemens Industrial Turbomachinery AB, Finspong SE-612 83, Sweden
daniel.lorstad@siemens.com

Annika Lindholm

Siemens Industrial Turbomachinery AB, Finspong SE-612 83, Sweden
annika.lindholm@siemens.com

Xue-Song Bai

Department of Energy Sciences, Lund University, PO Box 118, SE-221 00 Lund, Sweden
xue-song.bai@energy.lth.se

1Corresponding author.

ASME doi:10.1115/1.4042473 History: Received July 05, 2018; Revised November 28, 2018

Abstract

Large eddy simulations (LES) and experiments (OH-PLIF and pressure transducer) have been carried out on a gas turbine burner fitted to an atmospheric combustion rig. This burner, from the Siemens SGT-800 gas turbine, is a low NOx, partially premixed burner, where pre-heat air temperature, flame temperature and pressure drop across the burner are kept similar to engine full load conditions. The large eddy simulations are based on a flamelet generated manifold approach for representing the chemistry and the Smagorinsky model for sub-grid turbulence. The experimental data and simulation data are in good agreement, both in terms of time averaged as well as time resolved quantities. From the experiments and LES, three bands of frequencies of pressure fluctuations with high power spectral density are found in the combustion chamber. The first two bands are found to be axial pressure modes, triggered by coherent flow motions from the burner, such as the flame stabilization location and the precessing vortex core (PVC). The third band is found to be a cross flow directional mode interacting with two of the four combustion chamber walls in the square section of the combustion chamber, triggered from general flow motions. This study shows that LES of real gas turbine components is feasible and that the results give important insight into the flow, flame and acoustic interactions in a specific combustion system.

Siemens AG
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