가스터빈 연소기에서 스월 수와 연소실 길이에 따른 연소불안정 특성
Combustion Instability Characteristics according to Swirl Number and Combustion Chamber Length in a Gas Turbine Combustor
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Combustion instability characteristics were investigated through combustion tests using ethylene and air in a model gas turbine combustor. At various flow conditions, the swirl number and combustion chamber length were changed independently. Dynamic pressure transducer and photomultiplier tube with a bandpass filter were used to measure pressure oscillations and heat release fluctuations. Analysis of phase difference and flame structure showed that the unstable mode had resonant frequencies of the combustion chamber and the inlet mixing section. When the swirl number increased, it was confirmed that the instability mode corresponding to the resonance frequency of the inlet mixing section disappeared. In addition, resonance mode analysis was performed using the OSCILOS code and compared with the experimental results.
Abstract
Combustion instability characteristics were investigated through combustion tests using ethylene and air in a model gas turbine combustor. At various flow conditions, the swirl number and combustion chamber length were changed independently. Dynamic pressure transducer and photomultiplier tube with a bandpass filter were used to measure pressure oscillations and heat release fluctuations. Analysis of phase difference and flame structure showed that the unstable mode had resonant frequencies of the combustion chamber and the inlet mixing section. When the swirl number increased, it was confirmed that the instability mode corresponding to the resonance frequency of the inlet mixing section disappeared. In addition, resonance mode analysis was performed using the OSCILOS code and compared with the experimental results.
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