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High-frequency transition characteristics of synthetic natural gas combustion in gas turbine

Published online by Cambridge University Press:  27 February 2019

S. Joo ,
S. Kwak ,
S. Kim ,
J. Lee  and
Y. Yoon
S. Joo*
Affiliation:
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul, South Korea
S. Kwak
Affiliation:
Seoul National University, School of Mechanical and Aerospace Engineering, Seoul, South Korea
S. Kim
Affiliation:
Seoul National University, School of Mechanical and Aerospace Engineering, Seoul, South Korea
J. Lee
Affiliation:
University of Cincinnati, College of Engineering, Cincinnati, OH, USA
Y. Yoon
Affiliation:
Seoul National University, School of Mechanical and Aerospace Engineering, The Institute of Advanced Aerospace Technology, Seoul, South Korea
*
*seongpil@snu.ac.kr
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Abstract

In this study, the combustion instability and emission characteristics of flames of different H2/CH4 compositions were investigated in a partially premixed model gas turbine combustor. A mode shift in the frequency of instability occurred under varying experimental conditions from the first to the seventh mode of longitudinal frequency in the combustor, and a parametric study was conducted to determine the reasons for this shift by using the length of the combustor, a factor that determines the mode frequency of longitudinal instability, as the main parameter. Furthermore, heat load and fuel composition (H2 ratio) were considered as parameters to compare the phenomenon under different conditions. The GRI-3.0 CANTERA code, OH chemiluminescence and the Abel inversion process were applied to analyse the frequency mode shift. NOx emissions, which occurred through the thermal NOx mechanism, increased with increasing heat load and H2 ratio. The instability frequency shifted from the first to the seventh mode as the H2 ratio increased in the H2/CH4 mixture. However, 100% H2 as fuel did not cause combustion instability because it has a higher burning velocity and extinction stretch rate than CH4. Furthermore, the laminar flame speed influenced the frequency mode shift. These phenomena were confirmed by the flame shapes. The Abel inversion process was applied to obtain the cross section of the flames from averaged OH chemiluminescence images. Stable and unstable flames were identified from the radial profile of OH concentration. The combustor length was found to not influence frequency mode shift, whereas the H2 ratio significantly influenced it as well as the flame shape. The results of this experimental study can help in the reliable operation of gas turbine systems in SNG plants.

Keywords

Partially premixed model combustorCombustion instabilityTime lag analysisExhaust gasAbel inversion
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1259 , January 2019 , pp. 138 - 156
Copyright
© Royal Aeronautical Society 2019 

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Footnotes

A version of this paper was presented at the ISABE 2017 Conference, 3–8 September 2017, Manchester, UK.

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