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      환형노즐을 모사한 캔 연소기에서 Symmetry Breaking에 의한 종-방향 연소불안정성 제어 연구

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      https://www.riss.kr/link?id=A107426315

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      다국어 초록 (Multilingual Abstract)

      In this study, the effect of Symmetry Breaking was compared according to the equivalent ratio condition and the number of nozzles where combustion instability occurs in an annular combustor. Generally, due to the relatively short combustor length, a longitudinal instability was less likely to occur in the annular combustor, but the combustion instability sometimes happens when ducts such as transition piece in gas turbine power station are present. In this case, due to the duct, only the longitudinal instability mode is observed. The characteristics of Symmetry Breaking were investigated according to the number of five lean nozzles and the equivalent ratio combination, and as the equivalent ratio decreased, the effect of Symmetry Breaking rapidly occurred, and the instability was dramatically disappeared and the amplitude was greatly reduced. In addition, it was confirmed that as the number of lean nozzles increased, a phenomenon such as a reduction in the equivalent ratio appeared.
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      In this study, the effect of Symmetry Breaking was compared according to the equivalent ratio condition and the number of nozzles where combustion instability occurs in an annular combustor. Generally, due to the relatively short combustor length, a l...

      In this study, the effect of Symmetry Breaking was compared according to the equivalent ratio condition and the number of nozzles where combustion instability occurs in an annular combustor. Generally, due to the relatively short combustor length, a longitudinal instability was less likely to occur in the annular combustor, but the combustion instability sometimes happens when ducts such as transition piece in gas turbine power station are present. In this case, due to the duct, only the longitudinal instability mode is observed. The characteristics of Symmetry Breaking were investigated according to the number of five lean nozzles and the equivalent ratio combination, and as the equivalent ratio decreased, the effect of Symmetry Breaking rapidly occurred, and the instability was dramatically disappeared and the amplitude was greatly reduced. In addition, it was confirmed that as the number of lean nozzles increased, a phenomenon such as a reduction in the equivalent ratio appeared.

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      참고문헌 (Reference)

      1 이지호, "상호작용하는 두 스월 안정 화염에서 발생하는 준임계 분기 현상" 한국연소학회 24 (24): 17-24, 2019

      2 문기훈, "다중 가스터빈 연소기의 음향 상호작용 시계열 분석" 한국연소학회 25 (25): 36-43, 2020

      3 O’Connor, J, "Transverse combustion instabilities : Acoustic, fluid mechanic, and flame processes" 49 : 1-39, 2015

      4 Schulz, O, "Thermoacoustic instability in a sequential combustor: Large eddy simulation and experiments" 37 : 5325-5332, 2019

      5 Dawson, J. R, "The effect of baffles on self-excited azimuthal modes in an annular combustor" 35 : 3283-3290, 2015

      6 Evesque, S, "Spinning and azimuthally standing acoustic modes in annular combustors" 1-8, 2003

      7 Baillot, F, "Response of a lamina premixed V-flame to a high-frequency transverse acoustic field" 161 : 1247-1267, 2014

      8 Poinsot, T, "Prediction and control of combustion instabilities in real engines" 36 : 1-28, 2017

      9 Worth, N. A, "Modal dynamics of self-excited azimuthal instabilities in an annular combustion chamber" 160 : 2476-2489, 2013

      10 Pirk, R, "Liquid rocket combustion chamber acoustic characterization" 2 : 269-278, 2010

      1 이지호, "상호작용하는 두 스월 안정 화염에서 발생하는 준임계 분기 현상" 한국연소학회 24 (24): 17-24, 2019

      2 문기훈, "다중 가스터빈 연소기의 음향 상호작용 시계열 분석" 한국연소학회 25 (25): 36-43, 2020

      3 O’Connor, J, "Transverse combustion instabilities : Acoustic, fluid mechanic, and flame processes" 49 : 1-39, 2015

      4 Schulz, O, "Thermoacoustic instability in a sequential combustor: Large eddy simulation and experiments" 37 : 5325-5332, 2019

      5 Dawson, J. R, "The effect of baffles on self-excited azimuthal modes in an annular combustor" 35 : 3283-3290, 2015

      6 Evesque, S, "Spinning and azimuthally standing acoustic modes in annular combustors" 1-8, 2003

      7 Baillot, F, "Response of a lamina premixed V-flame to a high-frequency transverse acoustic field" 161 : 1247-1267, 2014

      8 Poinsot, T, "Prediction and control of combustion instabilities in real engines" 36 : 1-28, 2017

      9 Worth, N. A, "Modal dynamics of self-excited azimuthal instabilities in an annular combustion chamber" 160 : 2476-2489, 2013

      10 Pirk, R, "Liquid rocket combustion chamber acoustic characterization" 2 : 269-278, 2010

      11 Noiray, N, "Investigation of azimuthal staging concepts in annular gas turbines" 15 : 585-606, 2011

      12 Poinsot, T, "Identification of azimuthal modes in annular combustion chambers" Center for Turbulence Research Annual Research Briefs 249-258, 2011

      13 Dawson, J. R, "Flame dynamics and unsteady heat release rate of self-excited azimuthal modes in an annular combustor" 161 : 2565-2578, 2014

      14 Hoeijmakers, M, "Flame dominated thermoacoustic instabilities in a system with high acoustic losses" 169 : 209-215, 2016

      15 Balachandran, R, "Experimental investigation of the nonlinear response of turbulent premixed flames to imposed inlet velocity oscillations" 143 : 37-55, 2005

      16 Xia, Y, "Experimental investigation of the flame front propagation characteristic during light-round ignition in an annular combustor" 103 : 247-269, 2019

      17 Yoon, J, "Effects of convection time on the high harmonic combustion instability in a partially premixed combustor" 36 : 3753-3761, 2017

      18 Worth, N. A, "Effect of equivalence ratio on the modal dynamics of azimuthal combustion instabilities" 36 : 3743-3751, 2017

      19 Kheirkhah, S, "Dynamics and mechanisms of pressure, heat release rate, and fuel spray coupling during intermittent thermoacoustic oscillations in a model aeronautical combustor at elevated pressure" 185 : 319-334, 2017

      20 Moon, K, "Combustion-acoustic interactions through cross-talk area between adjacent model gas turbine combustors" 405-416, 2019

      21 Ferguson, D, "Characterization of instabilities in a low-swirl injector with exhaust gas recirculation" 2011-2517, 2011

      22 Guan, Y, "Chaos, synchronization, and desynchronization in a liquid-fueled diffusion-flame combustor with an intrinsic hydrodynamic mode" 29 : 053124-, 2019

      23 Worth, N. A, "Azimuthally forced flames in an annular combustor" 36 : 3783-3790, 2017

      24 Bauerheim, M, "Analytical methods for azimuthal thermo-acoustic modes in annular combustion chambers" Center for Turbulence Research 77-88, 2015

      25 Li, C, "An analytical study of the effect of flame response to simultaneous axial and transverse perturbations on azimuthal thermoacoustic modes in annular combustors" 37 : 5279-5287, 2019

      26 Wang, J, "A model to predict acoustic resonant frequencies of distributed helmholtz resonators on gas turbine engines" 9 : 1419-, 2019

      27 Prieur, K, "A hysteresis phenomenon leading to spinning or standing azimuthal instabilities in an annular combustor" 175 : 283-291, 2017

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      학술지 이력
      연월일 이력구분 이력상세 등재구분
      2021 평가예정 계속평가 신청대상 (등재유지)
      2018-01-01 평가 등재학술지 유지 (등재유지) KCI등재
      2015-01-01 평가 등재학술지 유지 (등재유지) KCI등재
      2011-01-01 평가 등재학술지 유지 (등재유지) KCI등재
      2009-01-01 평가 등재학술지 유지 (등재유지) KCI등재
      2006-01-01 평가 등재학술지 선정 (등재후보2차) KCI등재
      2005-02-28 학회명변경 영문명 : The Korean Society Of Propulsion Engineers -> The Korean Society of Propulsion Engineers KCI등재후보
      2005-01-01 평가 등재후보 1차 PASS (등재후보1차) KCI등재후보
      2003-01-01 평가 등재후보학술지 선정 (신규평가) KCI등재후보
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      기준연도 WOS-KCI 통합IF(2년) KCIF(2년) KCIF(3년)
      2016 0.23 0.23 0.21
      KCIF(4년) KCIF(5년) 중심성지수(3년) 즉시성지수
      0.2 0.19 0.397 0.1
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