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

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dc.contributor.authorAhn, Byeongukko
dc.contributor.authorLee, Jeongjaeko
dc.contributor.authorJung, Seungchaiko
dc.contributor.authorKim, Kyu Taeko
dc.date.accessioned2018-08-20T06:47:52Z-
dc.date.available2018-08-20T06:47:52Z-
dc.date.created2018-07-26-
dc.date.created2018-07-26-
dc.date.created2018-07-26-
dc.date.created2018-07-26-
dc.date.issued2018-10-
dc.identifier.citationCOMBUSTION AND FLAME, v.196, pp.424 - 438-
dc.identifier.issn0010-2180-
dc.identifier.urihttp://hdl.handle.net/10203/244644-
dc.description.abstractLow-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.-
dc.languageEnglish-
dc.publisherELSEVIER SCIENCE INC-
dc.titleLow-frequency combustion instabilities of an airblast swirl injector in a liquid-fuel combustor-
dc.typeArticle-
dc.identifier.wosid000445848100038-
dc.identifier.scopusid2-s2.0-85049989892-
dc.type.rimsART-
dc.citation.volume196-
dc.citation.beginningpage424-
dc.citation.endingpage438-
dc.citation.publicationnameCOMBUSTION AND FLAME-
dc.identifier.doi10.1016/j.combustflame.2018.06.031-
dc.contributor.localauthorKim, Kyu Tae-
dc.contributor.nonIdAuthorLee, Jeongjae-
dc.contributor.nonIdAuthorJung, Seungchai-
dc.description.isOpenAccessN-
dc.type.journalArticleArticle-
dc.subject.keywordAuthorAirblast injector-
dc.subject.keywordAuthorCombustion instability-
dc.subject.keywordAuthorGas turbine combustion-
dc.subject.keywordAuthorHelmholtz mode-
dc.subject.keywordAuthorLow frequency-
dc.subject.keywordAuthorSpray combustion-
dc.subject.keywordPlusPRECESSING VORTEX CORE-
dc.subject.keywordPlusGAS-TURBINE COMBUSTOR-
dc.subject.keywordPlusEQUIVALENCE RATIO FLUCTUATIONS-
dc.subject.keywordPlusEXCITED AZIMUTHAL MODES-
dc.subject.keywordPlusPREMIXED FLAME RESPONSE-
dc.subject.keywordPlusHEAT RELEASE RATE-
dc.subject.keywordPlusANNULAR COMBUSTOR-
dc.subject.keywordPlusTHERMOACOUSTIC OSCILLATIONS-
dc.subject.keywordPlusVELOCITY FLUCTUATIONS-
dc.subject.keywordPlusNONLINEAR RESPONSE-
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AE-Journal Papers(저널논문)
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