• 에너지공학
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• 제10권3호
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• pp.188-194
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• 2001

정유공장으로부터 발생하는 중잔사유를 이용하는 가스화 복합발전 플랜트에 대한 공정모사를 수행하였다. 가스화 복합사이클의 발전계통을 모델링하기 위해 본 연구는 MS7001FA 가스터빈이 공기분리장치와 연계되어 있고, 공기분리장치를 위한 공기 추출과 공기분리장치로 부터의 질소희석이 이루어진다고 가정하였다 가스터빈의 폐열은 삼중압력의 페열회수 증기발생장치로부터 회수하였다. 가스터빈의 합성가스 연료는 중잔사유가 Shell 가스화 및 Sulfinol-SCOT-Claus 공정을 거쳐 발생되는 것으로 가정하였다. 공정 최적화 결과로부터, 가스화 복합사이클의 효율이, 질소 희석이 없는 경우와 있는 경우에 대해, 공기추출비 20% 또는 40∼60%에서 가장 우수했다. 그리고, 연소지의 질소희석은 NOx 저감에 매우 바람직하고 현저한 효과를 가져오나, 반면에 가스터빈의 운전조건을 써지 조건에 가깝게 이동시킴을 알 수 있었다.

• Journal of Mechanical Science and Technology
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• 제17권6호
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• pp.906-913
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• 2003

Lean premixed combustion has been considered as one of the promising solutions for the reduction of NOx emissions from gas turbines. However, unstable combustion of lean premixed flow becomes a real challenge on the way to design a reliable, highly efficient dry low NOx gas turbine combustor. Contrary to a conventional diffusion type combustion system, characteristics of premixed combustion significantly depend on a premixing degree of combusting flow. Combustion behavior in terms of stability has been studied in a model gas turbine combustor burning natural gas and air. Incompleteness of premixing is identified as significant perturbation source for inducing unstable combustion. Application of a simple convection time lag theory can only predict instability modes but cannot determine whether instability occurs or not. Low frequency perturbations are observed at the onset of instability and believed to initiate the coupling between heat release rate and pressure fluctuations.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2004년도 유체기계 연구개발 발표회 논문집
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• pp.462-468
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• 2004

Large eddy simulation(LES) methodology used to model isothermal non-swirling and swirling flows in a model gas turbine combustor. The LES solver was implemented on parallel computer consisting 16 processors. To verify the capability of LES code and characterize swirling flow, the results was compared with that of Reynolds Averaged Navier-Stokes(RANS) using k -$\epsilon$ model as well as experimental data. The results showed that the LES and RANS well predicted the mean velocity field of a non-swirling flow. Specially, the LES showed a very excellent prediction performance for the corner recirculation zone. In swirling flow, comparing with the results obtained by RANS, LES showed a better performance in predicting the mean axial and azimuthal velocities, and the central recirculation zone. Finally, unsteady phenomena of turbulent flow was examined with LES methodology.

• 한국전자통신학회논문지
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• 제18권5호
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• pp.841-852
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• 2023

국내 전력계통의 주파수 조정용 발전기로 사용되고 있는 가스터빈은 탄소중립 정책과 더불어 신속한 기동·정지 및 높은 열효율 등으로 인해 이용률이 증가하고 있다. 가스터빈은 고온의 화염을 이용하여 터빈을 회전시키기 때문에 터빈 입구온도가 기기의 성능과 수명을 좌우하는 핵심요소로 작용하고 있다. 하지만 입구온도는 직접적인 측정이 불가능함에 따라 제작사가 산출한 온도를 이용하거나, 현장 경험을 토대로 하여 예측된 온도를 적용하고 있어서 가스터빈의 안정적인 운전 및 유지관리에 많은 어려움을 겪고 있다. 이에 본 연구에서는 인공신경망에서 많이 사용되고 있는 DNN(: Deep Neural Network) 기반으로 하는 재열 가스터빈의 입구온도를 예측할 수 있는 모델을 제시하고 실측 데이터를 기반으로 제안된 DNN의 성능을 검증하고자 한다.

• 한국가시화정보학회지
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• 제17권1호
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• pp.78-84
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• 2019

A gas turbine is the main equipment of a power plant that generates electricity by high-speed rotation of the rotor in a high-temperature environment. In particular, in the case of medium to large-sized gas turbines, the rotor is composed of a plurality of stages, and each component is exposed to different physical environments. Especially, in the case of the tip clearance of the turbine, it is a very important factor in the performance of the design items and the operation of the stable turbine, and a design considering the physical behavior of all major parts should be done. In this study, we will discuss the process of visualizing the physical behavior of turbine operating conditions and the method of designing tip clearance for stable operation by using commercial finite element analysis program for gas turbine assembly model and single product.

• 한국연소학회지
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• 제15권1호
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• pp.12-21
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• 2010

The main objective of this study was investigation of combustion instability characteristics in a lean partially premixed gas turbine dump combustor. Dynamic pressure transducers were located on combustor and inlet section to observe combustion pressure oscillation and difference at each measurement places. Also flame shape and $CH^*$ chemiluminescence were measured using a high speed ICCD camera. The combustor length was varied in order to have different acoustic characteristics from 800 to 1090 mm. The first section of this paper shows the stability map in model gas turbine combustor. And the effects of combustor length, mixture velocity in the mixing section and equivalence ratio were studied by the pressure perturbation and heat release oscillation. Also, the instability frequency and mode analysis were studied in last two sections. We observed two dominant instability frequencies in this study. Lower frequencies were obtained at lower equivalence ratio region and it was associated with a fundamental longitudinal mode of combustor length. Higher frequencies were observed in higher equivalence ratio conditions. It was related to secondary longitudinal mode of combustor and mixing section. In this instability characteristics, pressure oscillation of mixing section part was larger than pressure oscillation of combustor. As a result, combustion instability was strongly affected by acoustic characteristics of combustor and mixing section geometry.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2008년도 추계학술대회B
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• pp.2862-2867
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• 2008

High-temperature components of gas turbine operated for certain period of time can be reused by being repaired or rejuvenated. In case of the gas turbine combustion liners, the biggest and the most important one in the high-temperature components, come in a repair shop after operated for 8,000 or 12,000 hours according to the model and go through the repair and rejuvenation in order to be reused. A stated combustion liner is the first channel which has the combustion gas reached a nozzle from a fuel nozzle. Materials and coating properties of old and new model combustion liners were investigated. To repair these components after the visual inspection, the coatings of combustion liners were removed and then FPI(Fluorescent Penetrant Inspection), a kind of the NDI(Non-Destructive Inspection), was conducted. Damage patterns and the number of the damaged components were classified and analyzed based on data provided from the visual inspection over a long period of time. Focusing on the difference between old model and new model combustion liners, we analyzed the damage distribution and changes and consequently concluded that new model combustion liner would increase repair rate.

• 한국전자통신학회논문지
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• 제18권3호
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• pp.483-494
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• 2023

최근 가스터빈 발전기는 전력계통의 주파수 조절용으로 널리 사용되고 있다. 가스터빈의 입구온도는 기기의 성능과 수명에 관련된 핵심요소이지만 터빈구조 및 운전환경 등의 이유로 입구온도를 직접 측정하지 않고 가스터빈 배기가스 온도 측정값을 이용하여 입구온도의 추정 값을 구해 이를 연소제어에 사용하고 있다. 특히 재열 가스터빈의 입구온도는 안정적 운전관리에 있어서 매우 중요하지만 제작사가 산출 식에 대한 정보를 제공하지 않고 있어 현장 실무자들은 많은 어려움을 겪고 있다. 이에 본 연구에서는 폴리트로픽 과정식의 기반 위에 머신러닝 기반의 선형회귀 분석기법을 사용하여 가스터빈의 입구온도를 추정할 수 있는 방법을 제시하고자 한다. 또한 선형회귀분석을 통해 얻어진 입구온도 산출 모델식의 유용성 분석과 검증을 통해 입구온도 산출 알고리즘을 제안함으로서 재열 가스터빈 연소튜닝 기술수준 향상에 도움이 되고자 한다.

• 한국해양공학회지
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• 제14권3호
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• pp.84-89
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• 2000

The purpose of this study is to investigate the combustion emission characteristics by the effect of secondary air injection and variation of the excess air ratio in combustion field of model gas turbine combustor. For this purpose, mean temperature, CO, $CO_2$, $O_2$ and HC concentrations were measured by changing excess air ratio and secondary air injection. As a result of this study, mean temperature was decreased and CO, HC emission increased by increasing the excess air ratio of secondary air. Therefore, this results showed the secondary air injection effected strongly on the flame structure and combustion emission characteristics.

• 한국해양공학회:학술대회논문집
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• 한국해양공학회 2000년도 춘계학술대회 논문집
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• pp.171-176
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• 2000

This purpose of this study is to investigate the combustion emission characteristics on the effect of secondary air injection in combustion field of model gas turbine combustor changing excess air ratio. For this purpose, meantemperature, CO, CO2, O2 and HC concentration were measured by changing excess air ratio and secondary air injection. As a result of this study, meantemperature, CO2 emission was decreased and CO emission increased by increasing the excess air ratio of secondary air. therefore, This paper showed the effect of Secondary air injection on flame structure, combustion emission characteristics.