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

Experimental Analysis of the Combustion Behavior of a Gas Turbine Burner by Laser Measurement Techniques

[+] Author and Article Information
Holger Ax1

Institute of Combustion Technology, German Aerospace Center (DLR), Pfaffenwaldring 38-40, D-70563 Stuttgart, Germanyholger.ax@dlr.de

Ulrich Stopper, Wolfgang Meier, Manfred Aigner

Institute of Combustion Technology, German Aerospace Center (DLR), Pfaffenwaldring 38-40, D-70563 Stuttgart, Germany

Felix Güthe

 Alstom Ltd., CH-5401 Baden, Switzerland

1

Corresponding author.

J. Eng. Gas Turbines Power 132(5), 051503 (Mar 05, 2010) (9 pages) doi:10.1115/1.3205033 History: Received April 08, 2009; Revised May 14, 2009; Published March 05, 2010; Online March 05, 2010

Experimental results from optical and laser spectroscopic measurements on a scaled industrial gas turbine burner at elevated pressure are presented. Planar laser induced fluorescence on the OH radical and OH chemiluminescence imaging were applied to natural gas/air flames for a qualitative analysis of the position and shape of the flame brush, the flame front and the stabilization mechanism. The results exhibit two different ways of flame stabilization, a conical more stable flame and a pulsating opened flame. For quantitative results, one-dimensional laser Raman scattering was applied to these flames and evaluated on an average and single-shot basis in order to simultaneously determine the major species concentrations, the mixture fraction, and the temperature. The mixing of fuel and air, as well as the reaction progress, could thus be spatially and temporally resolved, showing differently strong variations depending on the flame stabilization mode and the location in the flame.

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Copyright © 2010 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematic drawing of the burner and the measurement positions of the different laser diagnostic techniques

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Figure 2

Schematic drawing of the experimental setup for OH-PLIF measurements

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Figure 3

Schematic drawing of the setup for 1D-Raman experiments

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Figure 4

Mean distribution of the OH∗ chemiluminescence of flame A (averaged over 200 single shots). The dotted line indicates the position of the radial profile that was measured by 1D-Raman scattering.

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Figure 5

OH-PLIF measurements of flame A. Top: mean OH distribution (averaged over 200 single shots). Bottom: single-shot OH-PLIF measurement.

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Figure 6

Radial profile of the mean mixture fraction in flame A 22 mm downstream from the burner mouth; for comparison, the stoichiometric mixture fraction of the NG is 0.057

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Figure 7

Scatter plots of single-shot Raman measurements in flame A at different radial positions 22 mm downstream from the burner mouth. Adiabatic equilibrium (black) and stoichiometric mixture fraction (light gray) are indicated by lines.

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Figure 8

Scatter plot of H2O versus temperature in flame A at a radius of r=24 mm, 22 mm downstream from the burner mouth. The light gray line indicates the adiabatic equilibrium state.

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Figure 9

Mean distribution of the OH∗ chemiluminescence of flame B (averaged over 200 single shots). The dotted line indicates the position of the radial profile that was measured by 1D-Raman scattering.

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Figure 10

OH-PLIF measurements of flame B. Top: mean OH distribution (averaged over 200 single shots). Bottom: single-shot OH-PLIF measurement.

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Figure 11

Radial profile of mean mixture fraction in flame B 22 mm downstream from the burner mouth

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Figure 12

Scatter plots of single-shot Raman measurements in flame B at different radial positions 22 mm downstream from the burner mouth. The adiabatic temperature (black) and the stoichiometric mixture fraction (light gray) are indicated by lines.

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Figure 13

Scatter plot of H2O versus temperature in flame B at a radius of r=24 mm. The light gray line indicates the adiabatic equilibrium state.

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