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

Experimental Investigation of Thermoacoustic Instabilities for a Model Combustor With Varying Fuel Components

[+] Author and Article Information
Hao Zhang, Xiaoyu Zhang

Key Laboratory for Thermal Science and Power Engineering, Department of Thermal Engineering,   Tsinghua University, Beijing 100084, China

Min Zhu1

Key Laboratory for Thermal Science and Power Engineering, Department of Thermal Engineering,   Tsinghua University, Beijing 100084, Chinazhumin@tsinghua.edu.cn

1

Corresponding author.

J. Eng. Gas Turbines Power 134(3), 031504 (Dec 30, 2011) (12 pages) doi:10.1115/1.4004212 History: Received April 22, 2011; Revised May 09, 2011; Published December 30, 2011; Online December 30, 2011

In this study, a combustion facility was constructed that includes a flexible fuel supply system to produce synthesis gas using a maximum of three components. The rig with lean premixed burner is able to operate at up to five bars. The length of the inlet plenum and the outlet boundary conditions of the combustion chamber are adjustable. Experiments were carried out under a broad range of conditions, with variations in fuel components including hydrogen, methane and carbon monoxide, equivalence ratios, thermal power and boundary conditions. The dynamic processes of self-excited combustion instabilities with variable fuel components were measured. The mechanisms of coupling between the system acoustic waves and unsteady heat release were investigated. The results show that instability modes and flame characteristics were significantly different with variations in fuel components. In addition, the results are expected to provide useful information for the design and operation of stable syngas combustion systems.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Schematic of the experimental apparatus

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Figure 2

Sketch of the swirling injector

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Figure 3

Measurement system used for the combustion instability studies

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Figure 4

Resonance frequencies in the plenum and the combustor

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Figure 5

Variations of frequency and SPL with the equivalence ratio at the air flow rate 40 g/s under open outlet condition

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Figure 6

Time traces and spectra of dynamic pressure and OH* chemiluminescence at the air mass flow 40 g/s and the equivalence ratio 0.65 with open outlet

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Figure 7

Time traces and spectra of dynamic pressure and OH* chemiluminescence at the air mass flow 40 g/s and the equivalence ratio 0.74 with open outlet

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Figure 8

Flame images with digital camera at (a) stable mode (b) unstable mode

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Figure 9

High speed camera images from a cycle of the acoustic waves at the air mass flow 40 g/s and the equivalence ratio 0.65 with open outlet

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Figure 10

High speed camera images from a cycle of the thermoacoustic oscillation at the air mass flow 40 g/s and the equivalence ratio 0.74 with open outlet

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Figure 11

ICCD images from a cycle of the acoustic waves at the air mass flow 40 g/s and the equivalence ratio 0.62 with open outlet

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Figure 12

ICCD images from a cycle of the thermoacoustic oscillation at the air mass flow 40 g/s and the equivalence ratio 0.68 with open outlet

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Figure 13

Variations of SPL with the size of exit nozzle at the air flow rate 30 g/s

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Figure 14

Stable flame images with the variations of the fuel compositions listed in Table 1

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Figure 15

Stability map with the equivalence ratio and the hydrogen content of the CH4/H2/N2 blended fuels

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Figure 16

Time traces and spectra of dynamic pressure and OH* chemiluminescence at the air mass flow 35 g/s and the equivalence ratio 0.80 with the H2 40 Vol % of CH4/H2/N2 blended fuels

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Figure 17

Time traces and spectra of dynamic pressure and OH* chemiluminescence at the air mass flow 50 g/s and the equivalence ratio 0.41 with the H2 60 Vol % of CH4/H2/N2 blended fuels

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Figure 18

ICCD images from a cycle of the thermoacoustic oscillation with the H2 60 Vol % of the CH4/H2/N2 blended fuel

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Figure 19

Stable flame images with the variations of the fuel compositions listed in Table 2

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Figure 20

Variations of frequency and SPL with the equivalence ratio for the blended fuel H2:CO=1:6

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Figure 21

Time traces and spectra of dynamic pressure and OH* chemiluminescence at the air mass flow 38 g/s and the equivalence ratio 0.22 for the blended fuel H2:CO=1:6

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Figure 22

High speed camera images from a cycle of the thermoacoustic oscillation for the blended fuel H2:CO=1:6

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Figure 23

Time traces and spectra of dynamic pressure and OH* chemiluminescence at the air mass flow 30 g/s and the equivalence ratio 0.23 for the blended fuel H2:CO=3:2

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Figure 24

Stability map with the equivalence ratio and the hydrogen content of the CO/H2 blended fuels

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Figure 25

Stable hydrogen flame images with the equivalence ratios of (a) 0.2 (b) 0.1

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Figure 26

Variations of frequency and SPL with the equivalence ratio of the hydrogen flames

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Figure 27

Time traces and spectra of dynamic pressure and OH* chemiluminescence at the air mass flow 30 g/s and the equivalence ratio 0.2 of the hydrogen flame

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Figure 28

Time traces and spectra of dynamic pressure and OH* chemiluminescence at the air mass flow 30 g/s and the equivalence ratio 0.37 of the hydrogen flames

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Figure 29

Variations of frequency and SPL with the caloric values of the H2/N2 blended fuels

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