Low-frequency combustion instabilities of an airblast swirl injector in a liquid-fuel combustor

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Low-frequency combustion dynamics of a prefilming airblast injector were experimentally investigated in a laboratory-scale liquid-fuel combustor operated with Jet A-1 fuel and air at atmospheric pressure and elevated temperatures. Our measurements reveal that multiple modes – ranging from 45 to 292 Hz – can be excited in the non-premixed combustion system, including the Helmholtz, longitudinal, and hydrodynamic instabilities. The system's propensity for mode selection depends strongly on combustor length and pilot equivalence ratio. A strong Helmholtz mode with a peak-to-peak amplitude of ∼14 kPa occurs, provided that the combustor length is relatively short and the pilot equivalence ratio is high. A high-amplitude, intermittent burst at approximately 12 Hz always develops when the system is on the verge of transition to the Helmholtz instability. With a longer combustor length, on the other hand, the system transitions to the ¾-wave longitudinal mode via a discontinuous mode-hopping process. The system undergoes well-defined, limit cycle oscillations with an extremely large pressure amplitude of ∼30 kPa, but the global OH* fluctuation amplitude is limited to merely 8.3%. Phase-resolved flame imaging measurements demonstrate that a ring-like partially-premixed flame emerges periodically in the dump region, when the non-premixed flame wrapping around the central recirculation zone is lifted off the fuel nozzle. The mutual interaction between the partially-premixed and non-premixed reaction zones is the dominant mechanism for intense sound generation. Under certain conditions, superposition of the Helmholtz and longitudinal modes occurs, leading to nonlinear interactions manifested by additional spectral peaks at the sum and difference of the two frequencies. In contrast to the other two cases, this superimposed tone is not characterized by limit cycle behavior, but by a noise-driven unsteadiness.
Publisher
ELSEVIER SCIENCE INC
Issue Date
2018-10
Language
English
Article Type
Article
Keywords

PRECESSING VORTEX CORE; GAS-TURBINE COMBUSTOR; EQUIVALENCE RATIO FLUCTUATIONS; EXCITED AZIMUTHAL MODES; PREMIXED FLAME RESPONSE; HEAT RELEASE RATE; ANNULAR COMBUSTOR; THERMOACOUSTIC OSCILLATIONS; VELOCITY FLUCTUATIONS; NONLINEAR RESPONSE

Citation

COMBUSTION AND FLAME, v.196, pp.424 - 438

ISSN
0010-2180
DOI
10.1016/j.combustflame.2018.06.031
URI
http://hdl.handle.net/10203/244644
Appears in Collection
AE-Journal Papers(저널논문)
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