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

Impact of Swirl Fluctuations on the Flame Response of a Perfectly Premixed Swirl Burner

[+] Author and Article Information
Thomas Komarek

Lehrstuhl für Thermodynamik, Technische Universität München, D-85747 Garching, Germanykomarek@td.mw.tum.de

Wolfgang Polifke1

Lehrstuhl für Thermodynamik, Technische Universität München, D-85747 Garching, Germanypolifke@td.mw.tum.de

1

Corresponding author.

J. Eng. Gas Turbines Power 132(6), 061503 (Mar 18, 2010) (7 pages) doi:10.1115/1.4000127 History: Received April 09, 2009; Revised July 19, 2009; Published March 18, 2010

Combustion instabilities represent a long known problem in combustion technology. The complex interactions between acoustics and turbulent swirling flames are not fully understood yet, making it very difficult to reliably predict the stability of new combustion systems. For example, the effects of fluctuations of swirl number on the heat release of the flame have to be investigated in more detail. In this paper a perfectly premixed swirl stabilized burner with variable axial position of the swirl generator is investigated. In experiments, the position of the swirl generator has a strong impact on the dynamic flame response, although it does not influence the time-averaged distribution of the heat release significantly. This phenomenon is further investigated using computational fluid dynamics combined with system identification. The generation of fluctuations of swirl number, their propagation to the flame, and their effect on the dynamic flame response are examined. A simple model based on convective time lags is developed, showing good agreement with experiments.

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Copyright © 2010 by American Society of Mechanical Engineers
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Figures

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Figure 4

FTFs for P=70 kW, ϕ=0.77, and three different positions of the axial swirl generator

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Figure 5

Domain A: burner and swirl generator with export planes

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Figure 6

Domain B: combustion chamber with signal plane

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Figure 7

Unit impulse responses of the swirl number in response plane 1: the contributions of the acoustic wave and circulation are highlighted

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Figure 8

Unit impulse responses of the circulation at upstream (top) and downstream (bottom) response planes

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Figure 9

Unit impulse responses: upper plot: response to an axial excitation and lower plot: response to a tangential excitation

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Figure 10

FTF experiment and model Δx=30 mm

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Figure 11

FTF experiment and model Δx=90 mm

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Figure 1

Sketch of the BRS burner

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Figure 2

Axial heat release distribution with swirler in front (Δx=30 mm) and rear position (Δx=130 mm)

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Figure 3

Experimental setup for FTF measurements

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Figure 12

FTF experiment and model Δx=130 mm

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