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research-article

Experimental Investigation of Self-Excited Combustion Instabilities in a Lean, Premixed, Gas Turbine Combustor at High Pressure

[+] Author and Article Information
Timo Buschhagen

Graduate Research Assistant School of Aeronautics & Astronautics Purdue University West Lafayette, IN
tbuschha@purdue.edu

Rohan Gejji

Post-Doctoral Research Associate School of Aeronautics & Astronautics Purdue University West Lafayette, IN
rgejji@purdue.edu

John Philo

Graduate Research Assistant School of Aeronautics & Astronautics Purdue University West Lafayette, IN
jphilo@purdue.edu

Lucky Tran

Graduate Research Assistant Mechanical & Aerospace Eng. Dept. University of Central Florida Orlando, FL
luckytran@knights.ucf.edu

J. Enrique Portillo Bilbao

Principal Engineer, Combustion Siemens Energy, Inc. Orlando, FL
juan.portillo@siemens.com

Carson D. Slabaugh

Assistant Professor School of Aeronautics & Astronautics Purdue University West Lafayette, IN
cslabau@purdue.edu

1Corresponding author.

ASME doi:10.1115/1.4039760 History: Received December 05, 2017; Revised March 01, 2018

Abstract

Self-excited combustion instabilities in a high pressure, single-element, lean, premixed, natural gas dump-combustor are investigated. The combustor is designed for optical access and instrumented with high frequency pressure transducers at multiple axial locations. A parametric survey of operating conditions including inlet air temperature and equivalence ratio has been performed, resulting in a wide range of pressure fluctuation amplitudes (p') of the mean chamber pressure (p). Two representative cases, Flame A and B with p'/p = 23% and p'/p = 12% respectively, both presenting self-excited instabilities at the fundamental longitudinal (1L) mode of the combustion chamber, are discussed to study the coupling mechanism between flame-vortex interactions and the acoustic field in the chamber. 10 kHz OH*-chemiluminescence imaging was performed to obtain a map of the global heat release distribution. Phase conditioned and Rayleigh index analysis as well as Dynamic Mode Decomposition (DMD) is performed, to highlight the contrasting mechanisms that lead to the two distinct instability regimes. Flame interactions with shear layer vortex structures downstream of the backward-facing step of the combustion chamber are found to augment the instability magnitude. Flame A engages strongly in this coupling, whereas Flame B is less affected and establishes a lower amplitude limit cycle.

Siemens AG
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