• 한국항공우주학회지
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• 제41권8호
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• pp.639-648
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• 2013

본 논문은 부게넘 및 태안 IGCC플랜트의 연료를 대상으로 석탄으로부터 생성된 합성가스의 NOx/CO배출 특성, 온도특성, 화염의 구조에 대해 기술하였다. GE7EA 모사 가스터빈 연소기를 대상으로 상압 고온 연소시험을 수행하여 입열량 및 질소희석에 따른 연소특성을 관찰하였다. 입열량이 감소하고, 희석제량이 증가할 때 단열화염온도의 감소로 NOx가 감소하였고, 저부하에서는 희석량이 증가할수록 불완전 연소로 인해 CO가 증가하였다. 이러한 NOx 감소 및 CO발생은 각각 $1500^{\circ}C$ 와 $1250^{\circ}C$의 특정 화염온도에서 관찰되었다. 또한 질소 희석이 증가할수록 단열화염온도 및 연소기 라이너의 온도가 감소했고, 화염 부상과 같은 화염구조의 변화로 인해 특이점이 관찰되었다. 본 연구결과를 통해 질소희석이 NOx/CO배출 및 온도, 화염구조에 미치는 영향이 검토되었으며, 시험 데이터는 향후 태안 IGCC 플랜트의 운전시 최적 조건 선정을 위한 기초자료로 활용될 예정이다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제37회 추계학술대회논문집
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• pp.685-693
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• 2011

에너지기후시대에 신에너지원 발굴, 저탄소 녹색성장의 일환으로 석탄 IGCC기술이 개발 중에 있다. 본 연구는 IGCC기술 중 가스화기에서 생산된 합성가스를 가스터빈에 직접 주입시 생길 수 있는 문제점을 미리 파악하고, 그 연소특성자료를 축적하기 위해 수행되었다. GE7EA연소기를 대상으로한 상압 및 고압연소실험을 통해 합성가스의 기본적인 연소특성을 파악하였으며, 수소화염이 과다한 NOx발생의 원인임을 파악하고, 질소희석을 통해 NOx배출량을 제어할 수 있음을 확인하였으며, 연소진동은 크게 발생치 않음을 확인하였다. 본 연구를 통해 축적된 시험 데이터는 2015년에 국내 최초로 준공예정인 태안 IGCC플랜트에 연소진단시스템 및 최적화 기술적용시 활용된 예정이다.

• 한국에너지공학회:학술대회논문집
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• 한국에너지공학회 2003년도 춘계 학술발표회 논문집
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• pp.513-516
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• 2003

가스터빈 복합발전은 우리나라 총 발전설비 용량의 약 25%를 차지하고 있다. 따라서 이들 가스터빈의 안정적인 운전을 위한 연소관리기술의 개발이 필요하며, 특히 발전설비의 대기오염물 배출기준이 점차 강화됨에 따라 가스터빈의 저NOx 연소 운영기술의 확보가 필수적이다. 국내에는 서인천복합, 신인천복합, 울산복합 및 보령복합 발전소 등에 건식 저 NOx 연소기가 설치되어 운영 중에 있으며 신규 건설중인 복합발전소에는 모두 이들이 설치될 예정이다.(중략)

• 대한기계학회논문집B
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• 제36권3호
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• pp.251-257
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• 2012

본 연구에서는 이중원추형 버너가 장착된 고압연소기를 이용하여 입구공기온도, 공기비 그리고 연소실 압력조건에 따른 NOx 배출 특성을 실험적으로 조사하였다. 배기가스 온도와 NOx 배출량은 동일한 연소실 끝단지점에서 측정되었다. NOx 배출량은 공기비가 증가함에 따라 감소하는 경향을 나타내었으며, 입구공기 온도와 연소실의 압력이 높아질수록 증가하는 경향을 나타내었다. 특히 입구공기 온도의 증가는 희박 영역에서 가연한계를 증가시켜 높은 단열화염 온도를 가짐에도 불고하고 저감된 NOx 배출 수준을 얻을 수 있었다. 연소실 압력이 증가할수록 Thermal NOx의 영향을 받는 영역에서의 NOx 배출은 큰 폭의 상승을 보였으나, 공기비가 1.8이상인 영역에서는 적은 연료량으로 인하여 적은 상승폭을 나타내었다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2012년도 제44회 KOSCO SYMPOSIUM 초록집
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• pp.7-8
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• 2012

The effects of interaction between partially premixed and premixed swirl flames on CO and NOx emissions were experimentally investigated using a hybrid/dual swirl jet combustor for a micro-gas turbine. Under the condition of constant angle ($45^{\circ}$) for outer swirl vane, the angle and direction of inner swirl vane installed for a partially premixed flame were varied as main parameters with a constant fuel flow rate for each nozzle. It was found that for all conditions, CO and NOx emissions were measured below 4 ppm and 15 ppm at 15% $O_2$, respectively, in a wide range of equivalence ratio (0.6~0.9). For co-swirl flows, CO emission increased dramatically as the angle of inner swirl vane increased from $15^{\circ}$ to $45^{\circ}$ near lean-flammability limit (i.e. equivalence ratio of 0.5). On the other hand, the case of swirl $angle=45^{\circ}$ provided the lowest NOx emission at higher equivalence ratios than 0.6. For counter-swirl flows, the case of swirl $angle=45^{\circ}$ extended the lean-flammability limit but higher NOx emissions were found compared to those of co-swirl flows. These results could be inferred by interaction between (inner) partially premixed and (outer) premixed swirl flames. However, these estimations were not clear yet because there was insufficient data on turbulent flow structure and fuel-air mixing in the present experimental approach.

• 신재생에너지
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• 제7권3호
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• pp.67-73
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• 2011

MGT fuelled by landfill gas was tested to asses feasibility of its exhaust gas application for $CO_2$ enrichment. The exhaust gas was analyzed during start-up and normal operation with different MGT load conditions. Due to the changes of air/fuel ratio and combustion mode, $O_2$, $CO_2$, CO and NOx concentration were varied within wide ranges during the MGT start-up. Especially, NOx emissioin level was increased up to 20.01 ppmv. Different tendencies of $O_2$, $CO_2$, CO and NOx concentrations were observed with MGT output changes. $O_2$ and CO concentrations were shown to be decreased and NOx and $CO_2$ concentrations were shown to have opposite trends. NOx emission level (0.8~1.88 ppmv) was very low compared to other types of combustion based power generation equipment. Unburned hydrocarbon emission level was substantially decreased with MGT load increase. Especially, $C_2H_4$ concentration was below the detection limit(0.2 ppmv) around the nominal load condition. The exhaust gas from landfill gas fuelled MGT system was shown to be feasible for $CO_2$ fertilization. Concentrations of major components were within or below the maximum allowable ranges.

• 한국수소및신에너지학회논문집
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• 제28권5호
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• pp.570-576
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• 2017

Gas turbine system with steam injection has shown outstanding advantages such as high specific power and NOx reduction. In the present work, a comparative exergetic analysis was carried out for Steam Injected Gas Turbine (STIG), Regenerative Steam Injected Gas Turbine (RSTIG), and Regenerative After Fogging Gas Turbine (RAF). Effects of pressure ratio, steam injection ratio and steam injection method on the system performance was theoretically investigated. The results showed that the order of the highest exergy efficiency is RSTIG, RAF, and STIG for low pressure ratios but STIG, RSTIG, and RAF for high pressure ratios. In each arrangement, the combustion chamber has the highest exergy destruction and the compressor has the second one.

• 항공우주기술
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• 제6권1호
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• pp.29-34
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• 2007

On the stage of combustor development process, many aerodynamic and combustion characteristics are found out not by only ideal design concept but by only useful tests which are top confidentiality of technically advanced engine development companies, RR and GE, etc. In this study, test techniques of one of that company are analysed and described about some unique tests for test low emission combustors.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집D
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• pp.66-70
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• 2001

The combustion characteristics have been investigated to develop the low $NO_{x}$ gas turbine combustor. The lean premixed combustion technology was applied to reduce the $NO_{x}$ emission. Also, the conventional combustor was designed and tested for the baseline of low $NO_{x}$ combustor performance. The test was conducted at the condition of high temperature and ambient pressure. The combustion air which has the temperature of 500K were supplied to the combustor through the air preheater. The temperature and emissions of $NO_{x}$ and CO were measured at the exit of combustor. The premixing chamber can be operated very lean condition of equivalence ratio around 0.35. The $NO_{x}$ was decreased with decreasing the equivalence ration. The CO was decreased with decreasing the equivalence ratio, but the CO was increased with decreasing the equivalence ratio below 0.45. But, at the very lean condition of equivalence ratio below 0.35 both NOx and CO were increased because of the flame unstability. The $NO_{x}$ was decreased slightly and CO was increased with increasing inlet air flowrate. This results can be used to determine the size of combustor. The low $NO_{x}$ combustor has lower values of $NO_{x}$ and CO compared with conventional one. Consequently the performance of combustor shows the possibility of the application to the gas turbine system.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2012년도 제44회 KOSCO SYMPOSIUM 초록집
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• pp.201-202
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• 2012

The isothermal flow structure and mixing characteristics of a hybrid/dual swirl jet combustor for micro-gas turbine were numerically investigated. Location of pilot nozzle, angle and direction of swirl vane were varied as main parameters with constant fuel flow rates for each nozzle. As a result, the variation in location of pilot nozzle resulted in significant change in turbulent flow field near burner exit, in particular, center toroidal recirculation zone (CTRZ) as well as turbulent intensity, and thus flame stability and emission characteristics might be significantly changed. The swirl angle of $45^{\circ}$ provided similar recirculating flow patterns in a wide range of equivalence ratio (0.5~1.0). Compared to the co-swirl flow, the counter-swirl flow leaded to the reduction in CTRZ and fuel-air mixing near the burner exit and a weak interaction between the pilot partially premixed flame and the lean premixed flame. With the comparison of experimental results, it was confirmed that the case of co-swirl flow and swirl $angle=45^{\circ}$ would provided an optimized combustor performance in terms of flame stability and pollutant emissions.