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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Comparative Validation Study on Identification of Premixed Flame Transfer Function

[+] Author and Article Information
Luis Tay-Wo-Chong

Lehrstuhl für Thermodynamik,  Technische Universität München, Boltzmannstraße 15, 85748 Garching, Germanytay@td.mw.tum.de

Sebastian Bomberg, Ahtsham Ulhaq, Thomas Komarek, Wolfgang Polifke

Lehrstuhl für Thermodynamik,  Technische Universität München, Boltzmannstraße 15, 85748 Garching, Germany

J. Eng. Gas Turbines Power 134(2), 021502 (Dec 16, 2011) (8 pages) doi:10.1115/1.4004183 History: Received April 26, 2011; Revised April 27, 2011; Published December 16, 2011; Online December 16, 2011

The flame transfer function (FTF) of a premixed swirl burner was identified from a time series generated with computational fluid dynamics simulations of compressible, turbulent, reacting flow at nonadiabatic conditions. Results were validated against experimental data. For large eddy simulation (LES), the dynamically thickened flame combustion model with one step kinetics was used. For unsteady simulation in a Reynolds-averaged Navier–Stokes framework (URANS), the Turbulent Flame Closure model was employed. The FTF identified from LES shows quantitative agreement with experiment for amplitude and phase, especially for frequencies below 200 Hz. At higher frequencies, the gain of the FTF is underpredicted. URANS results show good qualitative agreement, capturing the main features of the flame response. However, the maximum amplitude and the phase lag of the FTF are underpredicted. Using a low-order network model of the test rig, the impact of the discrepancies in predicted FTFs on frequencies and growth rates of the lowest order eigenmodes were assessed. Small differences in predicted FTFs were found to have a significant impact on stability limits. Stability behavior in agreement with experimental data was achieved only with the LES-based flame transfer function.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

CFD/System Identification flow chart

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Figure 2

Low-order model of premix burner test rig

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Figure 3

Scheme of the numerical setup of the burner

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Figure 4

Distribution of reaction rate in combustor middle cross plane (see Fig. 3). Left: Snap shot of instantaneous from LES. Right: Steady state source term from RANS. Zero mean axial velocity isolines in white.

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Figure 5

Normalized spatial distribution of heat release: (a) OH* from experiments, (b) averaged LES, and (c) RANS. Line-of-sight integrated heat release. Dump plane of combustor at axial position = 0m.

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Figure 6

Area normalized axial heat release distribution

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Figure 7

Flame transfer function. Top: Confidence analysis including a histogram of amplitudes from LES at 100 Hz for 1000 sequences.

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Figure 8

Downstream reflection coefficient used in network model

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Figure 9

Eigenfrequencies at different combustor lengths in network model

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Figure 10

Cycle increment in mode b from Fig. 9

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