• 한국연소학회:학술대회논문집
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• 한국연소학회 2012년도 제45회 KOSCO SYMPOSIUM 초록집
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• pp.229-231
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• 2012

A numerical analysis of a lean premixed combustor in a micro gas turbine was carried out to investigate the correlation between the turbulent mixing and emission characteristics on the combustor geometries. The interaction between the burners, by flow direction and momentum, significantly influenced on the turbulent mixing and combustion characteristics. The vortex which was generated by thermal expansion was observed during the combustion process, this was distinguished from the combustor geometries. The results showed that these characteristics can affect the NOx emission.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 춘계학술대회
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• pp.1292-1297
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• 2004

Acoustic characteristics in an industrial gas-turbine combustor are numerically investigated by adopting linear acoustic analysis. Spatially non-homogeneous temperature field in the combustor is considered in the numerical calculation and the characteristics are analyzed in view of acoustic instability. Acoustic analysis are conducted in the combustors without and with acoustic resonator, which is one of combustion stabilization devices. It has been reported that severe pressure fluctuation frequently occurs in the adopted combustor, and the measured signal of pressure oscillation is compared with the acoustic-pressure response from the numerical calculation. The numerical results are in a good agreement with the measurement data. In this regard, the phenomenon of pressure fluctuation in the combustor could be caused by acoustic instability. The acoustic effects of the resonators are analyzed in the viewpoints of both the frequency tuning and the damping capacity.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 춘계학술대회 논문집
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• pp.285-288
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• 2009

APU 가스터빈 연소기 내에서 공기 유동이 있는 경우의 연료 분무 특성을 알기 위하여 ND-Yag 레이저를 이용한 분무가시화 연구를 수행하였다. 분무형상 가시화를 하기 위하여 실물 연소기 1/6 크기의 분할 연소기를 제작하였으며, 연소기 부의 공기유속 조건을 모사하기 위하여 터보 블로워를 이용한 풍동장치를 제작하였다. 75 m/s 공기 유속 조건에서 분무가시화 결과 공기가 없는 경우에 비해 분무 각이 증가되었고 분무 입자도 넓게 분포됨을 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.

• 한국안전학회지
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• 제2권3호
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• pp.37-43
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• 1987

The combustion process in gas turbine combustor mainly influenced by flow pattern in combustor, and especially the flow pattern near the nozzle and the shape of recirculation zone affect strongly on the flame stabilization, temperature distribution and combustion efficiency in combustor. In this paper, the author has designed and manufactured transparent simplified model combustors on the basis of K. Suzuki's combustor design method to investigate the effects of swirl number and secondary air hold arrays in axial position on the flow characteristics by adopting the tuft method and 5 hole pitot tube.

• 대한기계학회논문집
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• 제18권1호
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• pp.240-249
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• 1994

The basic experiments for designing the effective gas turbine combustor were performed. There are several factors that define the characteristics of gas turbine combustor. Among them, experiment was focused on swirl effects by three types of swirler with different swirl numbers(0.0, 0.38, and 0.62). Particularly, an interest was concentrated on primary zone where the flame characteristics of total combustor was dominated strongly and secondary zone where the remaining unburned gas was reacted again or cooling effect was done according to degree of swirl intensity. For this study, following measurements have been carried out, that is, time mean and fluctuating temperature, exhaust gas composition including NO concentration, and ion current. From this study, it was found that swirl intensity affects largely not only flame style but also emission formation, furthermore that it is important to select proper swirl intensity.

• 한국연소학회지
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• 제13권4호
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• pp.37-46
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• 2008

Performance test of 5MW class gasturbine combustor was carried out at combustor test facility of KARI(Korea Aerospace Research Institute). The combustor is dry low NOx type premixed combustor and fuel is natural gas. The characteristics of combustor were measured including emission, pressure pulsation and exit temperature distribution. Optimum operation point of combustor was found by changing parameters like fuel ratio between pilot and main burner. The test result showed that the combustor performance is sufficient to satisfy the gasturbine system requirement.

• 한국연소학회:학술대회논문집
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• 대한연소학회 2003년도 제27회 KOSCO SYMPOSIUM 논문집
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• pp.265-272
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• 2003

Some catalytic reactors for industrial/generation gas turbines were reviewed and investigated to understand the current status and future prospect for ultra low NOx catalytic gas turbine combustor. Catalytic reactor which was applied to 1${\sim}$10MW class gas turbine has achieved the ultra low emission corresponding to less than 3ppm NOx and 10ppm CO. But the durability and sizing flexibility of catalyst is needed to improve the catalyst performance for commercial gas turbine operation.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집D
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• pp.115-120
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• 2001

The present study examined the possibility of $NO_{x}$ reduction in the high temperature industrial furnaces. duct burner of gas turbine cogeneration and two-stage gas turbine combustor. The experimental study was carried out for the diffusion flame of second stage combustor with the variations of oxygen concentration and supplying rate of hot exhaust gas from first stage combustor. It also examined the flammability range and $NO_{x}$ formation of the second stage combustor in which the fuel is supplying into the mixture of oxygen hot exhaust gas from first stage combustor. The results show that the enrichment of oxygen and increase of exhaust gas lead to increase the $NO_{x}$ up to 50 ppm with 23% $O_{2}$ condition.

• Journal of Mechanical Science and Technology
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• 제19권9호
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• pp.1811-1820
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• 2005

Thermo-acoustic instability of methane/ air flames in an industrial gas-turbine combustor is numerically investigated adopting CFD analysis. The combustor has 37 EV burners through which methane and air are mixed and then injected into the chamber. First, steady fuel! air mixing and flow characteristics established by the burner are investigated by numerical analysis with single burner. And then, based on information on the flow data, the burners are modeled numerically via equivalent swirlers, which facilitates the numerical analysis with the whole combustion system including the chamber and numerous burners. Finally, reactive flow fields within the chamber are investigated numerically by unsteady analysis and thereby, spontaneous instability is simulated. Based on the numerical results, scaling analysis is conducted to find out the instability mechanism in the combustor and the passive control method to suppress the instability is proposed and verified numerically.