• 한국추진공학회지
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• 제12권4호
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• pp.63-77
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• 2008

본 논문에서는 가스터빈에서의 연소불안정 현상과 그 메커니즘에 대해 살펴보았다. 연소불안정 연구를 위한 접근 방법이 논의되었고 전 세계 연소불안정 관련 연구그룹들의 최신 연구동향이 소개되었다. 현재까지도 연소불안정현상은 기관의 성능, 내구성, 작동 등에 영향을 미치는 중요한 문제 중의 하나이다. 덧붙여 가스터빈기관에서 연소불안정 현상은 공기 또는 연료의 섭동과 열방출율 사이의 상호 중첩된 결과로 알려져 있으며, 이는 NOx 감소 전략과도 관련이 있다. 따라서 연소불안정 연구에 대한 현황을 이해하기 위하여 가스터빈에서의 연소불안정 현상에 대하여 정리하여 보았다.

• 한국유체기계학회 논문집
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• 제14권2호
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• pp.41-46
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• 2011

This study investigated the changes in performance and operating characteristics of an F-class gas turbine according to the change of working fluid from air to carbon dioxide. The revised gas turbine is the topping cycle of the semi-closed oxy-fuel combustion combined cycle. With the same turbine inlet temperature, the $CO_2$ gas turbine is expected to produce about 85% more power. The main contributor is the greater compressor mass flow and the added oxygen flow for the combustion. Compressor pressure ratio increases about 50%. However, the gas turbine efficiency reduces about 10 %. Modulation of inlet guide vane to reduce the compressor inlet mass flow, the major purpose of which is to reduce the compressor inlet Mach number, was also performed.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.449-452
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• 2004

“Flameless combustion” of lean to ultra lean mixtures, supported by high-temperature burned gas, can resolve the dilemma between complete combustion versus ultra-low NOx emissions in gas turbine combustors. The characteristics of NOx emissions and combustion in “lean-lean” two-stage combustion were investigated for fuel vapor and droplets / air mixture jets injected from the main injection tube that was placed perpendicular to the combustor wall into the primary hot burned gas prepared by combustion of lean mixtures on a perforated flame holder. The present results clearly show that the ultra-low NOx combustion supported by the reaction of lean mixtures well mixed with the hot burned gas from the primary stage is much more advantageous in achieving ultra-low NOx emissions while maintaining high combustion efficiency.

• 대한안전경영과학회지
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• 제21권2호
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• pp.1-8
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• 2019

Most of gas turbine combined cycle power plants are located in urban areas to provide peak load and district heating. However, NOx(nitrogen oxides) of exhaust gas emission from the power plants cause additional fine dust and thus it has negative impact on the urban environment. Although DLN(dry low NOx) and multi-stage combustors have been widely applied to solve this problem, they have another critical problem of damages to combustors and turbine components due to combustion dynamic pressure. In this study, the effect of different fuel ratio on NOx emission and pressure fluctuation was investigated regarding two variable conditions; combustor stages and power output on M501J gas turbine.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2013년도 제46회 KOSCO SYMPOSIUM 초록집
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• pp.117-119
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• 2013

Combustion stability margin of a model gas turbine has been assessed by utilizing damping ratios of measured dynamic pressure data. It is known that acoustic oscillations in combustion chambers can be described as a superposition of nonlinearly interacting oscillators. Based on this theoretical background, CSMA (Combustion Stability Margin Assessment) code has been developed. The code has been employed into a model gas turbine combustion experiment, focused on the combustion instability, to show its capability to determine the damping ratio of measured dynamic pressure and further to assess combustion stability margin of the experiment, and turned out that the code works well.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2008년도 추계학술대회B
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• pp.2984-2988
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• 2008

Numerical analyses are carried out in order to understand complex thermal characteristics of a gas turbine combustor liner such as combustion gas temperatures, wall temperatures and heat transfer distributions. As results, The maximum internal and external heat transfer is $2218W/m^2K$ and $2358W/m^2K$, respectively. The combustion gas temperatures range is 673K to 1760K. A range of temperature on TBC is 676K to 1382K. Lastly, temperature range on outer surface of combustion liner cooled by compressed air is 676K to 1188K.

• 설비공학논문집
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• 제21권2호
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• pp.126-130
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• 2009

The present study describes an investigation into the characteristics of combustion oscillation and its suppression instability of a silo type gas turbine combustor in commercial power plant. Combustion oscillation is occurred the combustor in near full load during operation. As a result of FFT analysis of the combustion dynamics, the frequency of the oscillation is analyzed as the 1'st longitudinal mode of acoustic resonance of the combustor. For suppress of the instability, combustion tuning with adjust of fuel valve schedule is carried out, which changes equivalent ratio of each burners. As the result, the oscillation is successfully reduced with meeting the level of NOx emission regulation.

• 한국연소학회지
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• 제20권1호
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• pp.32-42
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• 2015

The combustion instability was experimentally investigated in model gas turbine combustor with dual swirl burner. When such instability occurs, a strong coupling between pressure oscillation and unsteady heat release excites a self-sustained acoustic wave which results in a loud sound, and can even cause fatal damage to the combustor and entire system. In present study, to understand the combustion instability with a premixed mixture, the detailed periods of pressure and heat release data in unstable flame mode were investigated by various measurement methods at relatively rich condition and lean condition near flammable limits. Also, to prepare the utilization of synthetic natural gas (SNG) fuel in gas turbine system, an investigation was conducted using a simulated SNG including methane as a reference fuel to examine the effects of $H_2$ content on flame stability. These results provide that the instability due to flash-back behaviour like CIVB phenomenon occurred at rich condition, while the repetition of relighting and extinction caused the oscillation of lean condition near flammable limit. From the analysis of $H_2$ content effects, it is also confirmed that the instability frequency is proportional to the laminar burning velocity at both rich and lean condition.

• 에너지공학
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• 제12권1호
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• pp.1-10
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• 2003

가압유동층 연소 유닛은 1~1.5 MPa, 연소 온도 850~87$0^{\circ}C$ 조건으로 운전된다. 가압 석탄 연소 시스템은 전열관을 통한 열전달로 증기를 생산하며 가스터빈으로 공급될 고온 가스를 생산한다. 가스 중의 고체 잔류물에 의한 가스터빈의 성능 저하 때문에 가스 정제가 매우 중요하며 석탄과 흡수제 및 연소 공기를 가압하여야 하고 배가스와 회 제거 시스템에서는 감압을 해야 하기 때문에 운전이 다소 복잡하다. 증기터빈 대 가스터빈에서 생산되는 전력의 비율은 약 80:20이고 모든 부하 범위에서 연소기와 가스터빈이 서로 적절히 조화를 이루어야 하기 때문에 PFBC와 복합 사이클 발전 루트는 독특한 제어 방식을 갖는다. 유동층에 적용할 수 있는 가스의 최대 온도는 회 융점에 의해 제한을 받기 때문에 가스터빈은 일반 가스터빈에 비해 좀 특별하다고 할 수 있다. 회의 용융이 일어나지 않도록 하기 위한 최대 허용 가스 온도는 약 90$0^{\circ}C$이다. 가스터빈의 높은 압력비 때문에 압축시 인터쿨링을 사용하며 이는 상대적으로 낮은 터빈 입구의 온도를 상쇄하기 위한 것이다.

• 설비공학논문집
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• 제13권12호
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• pp.1255-1265
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• 2001

A numerical study has been conducted to characterize the transient flow in a utility gas turbine burning natural gas. The solution domain encompasses the supply gas pressure regulator to the combustor of the gas turbine that employs multi-nozzle fuel injectors. Some results produced for verification in the present study agree suite well with the experimental ones. It is found that the total gas flow may decrease noticeably during its combustion mode change, which would be the reason of momentary combustion upset, when a reference case of opening ratios of control valves in the system is applied. Several parameters are then varied in order to make the total gas flow stable over that period of time. Results of this study may be useful to understand the unsteady behavior of combustion system burning natural gas.