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

Comparison of the Flow Field of a Swirl Stabilized Premixed Burner in an Annular and a Single Burner Combustion Chamber

[+] Author and Article Information
D. Fanaca, P. R. Alemela, T. Sattelmayer

Lehrstuhl für Thermodynamik, TU München, 85748 Garching, Germany

C. Hirsch

Lehrstuhl für Thermodynamik, TU München, 85748 Garching, Germanyhirsch@td.mw.tum.de

1/12 of the ACC area is about 8% larger than the SCC area.

xx encodes the nozzle diameter D, yy encodes the center body diameter d, and zz encodes the swirler slot length leff, all in mm,

J. Eng. Gas Turbines Power 132(7), 071502 (Apr 07, 2010) (7 pages) doi:10.1115/1.4000120 History: Received April 08, 2009; Revised July 28, 2009; Published April 07, 2010; Online April 07, 2010

An experimental investigation of the flow field of a 12 burner annular combustor and a single burner combustor with the same burner was performed. It has revealed the aerodynamic effect, which causes the discrepancies in the flame transfer function behavior measured at the same operating conditions in the single and the annular combustion chambers. The results have shown significant differences in the flow field. In particular, it is seen that for the investigated system in the annular combustor a free swirling jet flow forms, while in the single burner configuration, a swirling wall jet flow regime exists. In this paper, we discuss the physical mechanism and show how to generalize an earlier finding, which identified a critical confinement value for a given swirler. We propose a new correlation for coswirling burners, which explains the changes found for the investigated system. It compares also well with the experimental data from other burner geometries. The correlation should allow to design single burner tests as to match the annular combustor flow regime.

FIGURES IN THIS ARTICLE
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Copyright © 2010 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

OH∗-chemiluminescence distribution in the annular (left) and single (right) combustion chamber with the EV burner

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Figure 3

Schematic of the PIV experimental setup in the ACC

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Figure 5

Schematic of the PIV experimental setup in the SCC

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Figure 6

PIV in the ACC without flame

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Figure 7

PIV in the SCC without flame

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Figure 8

PIV in the annular combustor with flame

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Figure 9

Schematic of jet swirl balance

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Figure 10

Comparison of confinement theory Eq. 13 with experimental data from various burners in the SCC and ACC, as well as from previous axial jet theory (17)

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Figure 11

Schematic of the TD1 burner

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Figure 12

OH∗-chemiluminescence distribution in the annular (left) and single (right) combustion chamber with the TD1-321608 burner

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Figure 13

Schematic flow field kinematics for a point P on the interface between two burners at M and L. (a) Global situation. (b) Detail at point P.

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