• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.15-15
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• 1998

마하 수 6 이상인 극초음속 비행에는 스크램제트(SCRamjet : Supersonic Combustion Ramjet) 엔진이 가장 적합한 엔진으로 알려져 있고 현재 미국을 중심으로 이 엔진의 개발에 많은 노력을 기울이고 있다. 스크램제트 엔진의 성공적인 개발을 위해서는 초음속 공기 내에서 연료의 분사를 통한 가장 효율적인 연소를 유도할 수 있어야 한다. 초음속 상태의 공기와 연료의 혼합을 증대시키고 연소안정성을 향상시키는 방법으로 연소기 내에 인위적으로 경사충격파를 발생시키는 방안이 Marble 등에 의해 최초로 도입되었다. 본 연구에서는 스크램제트엔진 내의 연소기를 모델링하여 마하수 2.5의 초음속공기 유동 중앙에 수소 제트를 분사하여 초음속 수소-공기 화염을 만들고 연소기의 측면에 동일한 모양과 크기의 쐐기를 각각 부착시켜 평면 경사충격파를 발생시켰다 본 실험은 충격파가 초음속 화염에 미치는 영향을 연구한 최초의 실험연구이다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.35 no.4
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• pp.431-438
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• 2011

Flame lift-off conditions determine the operating conditions of burners. It is known that a flame can be lifted when the Schmidt number (Sc), which is the ratio of the dynamic viscosity to the mass diffusivity, is greater than unity. In this study, the flame lift-off characteristics of non-premixed flames of propane (Sc > 1) and methane (Sc < 1) in a coaxial outer air tube were experimentally compared. The experimental results indicated that stable lifted flames could be obtained even when Sc < 1 in a confined air tube. On the basis of the results of a simple numerical analysis, it was confirmed that a new flame stabilization mechanism exists in the tube. A velocity field is preferentially developed upstream of the flame, and it results in a new stabilization condition. This result can be very useful in explaining the stabilization of the flames of ordinary burners in which a flame is produced in a confined space.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.8
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• pp.632-638
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• 2013

This paper describes on the flame stability and combustion instability of coal derived synthetic gas especially for gases of Buggenum IGCC in Netherlands and Taean IGCC in Korea. These combustion characteristics were observed by conducting ambient-pressure elevated-temperature combustion tests in GE7EA model combustor when varying heat input and nitrogen dilution ratio. Flame stability map is plotted according to the flame structure by dividing all regimes into six, and only regime I and II are identified to be stable. Both syngases of Taean and Buggenum with nitrogen integration corresponds to regime II in which syngas burnt stably and flame coupled with outer recirculation flow. Stable regime of Buggenum is larger than that of Taean when considering only $H_2$/CO ratio due to higher content of hydrogen. However, when considering nitrogen dilution, syngas of Taean is burnt more stably than that of Buggenum since more nitrogen in Buggenum has negative effect on the stability of flame.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.139-143
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• 2011

금속분말을 청정 에너지원으로 이용하기 위해 금속분말 소형 연소기의 구현이 필요하다. 이를 위한 기초 연구로서 점화성이 뛰어나면서도 경제적인 수십 마이크로 크기의 마그네슘(Mg) 분말을 대상으로 고온 증기(steam)와의 연소 현상 대해 연구하였다. 본 연구에서는 연소실 내 체류시간 및 혼합 효율을 증가시키기 위해 와류 유동을 연소기에 적용하였고 아르곤(Ar) 이송가스를 이용해 마그네슘 분말을 공급하였다. 안정한 화염을 유지시키기 위하여 이송가스의 유량을 변화시켜 공급되는 마그네슘의 양을 조절하였고, 고온 증기의 공급량은 니들 밸브의 개도를 조정하거나 우회시킨 관로로 증기의 일부를 배출함으로써 조절하였다. 고온의 점화원을 사용하여 증기 분위기 내 마그네슘 분말을 점화시켜, 대기압 환경에서 마그네슘/증기/아르곤의 지속적인 화염을 구현하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.4
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• pp.70-80
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• 2019

Combustion tests using six bi-swirl coaxial injectors with different shapes and recess lengths were performed in a model combustion chamber capable of flame visualization. By utilizing gaseous methane and gaseous oxygen instead of actual propellants, the effects of injector design and experimental conditions on the flame structure and combustion stability were analyzed. It was found that not only the experimental conditions but also the injector geometry such as the recess length and orifice diameter had a considerable influence on the combustion stability. In addition, it was confirmed that the heat release pattern changed with the occurrence of combustion instability.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.119-122
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• 2007

The present study employs experimental approach to identify combustion stability characteristics of fuel-rich gas generators. The gas generator of interest, fueled by LOx and Jet A-1, experienced combustion instability coupled to a longitudinal resonant mode of the combustion chamber at about 1200 Hz. The occurrence of instability is strongly associated with acoustic boundary condition at the exit .and axial location of maximum heat release. As a result, stretching heat release zone in the axial direction by increase of the fuel nozzle diameter has dramatically stabilized combustion.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.787-790
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• 2017

This study is a preliminary research on characterization of methane - oxygen combustion used in bipropellant thruster. The limit of combustion stability and flame shape of methane - oxygen non-premixed flame injected by shear coaxial injector in the model combustion chamber Experimental studies have been carried out. A direct image of the flame was photographed using a DSLR camera, and combustion characteristics and flame length were quantified through image post-processing. As a result, it was confirmed that the stabilized flame was generated at the stoichiometric ratio as the oxidizer Reynolds number ($Re_o$) was increased, and the length of the turbulent flame was increased under the same injector diameter condition.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.6
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• pp.32-40
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• 2012

For predicting eigenfrequency and initial growth rate of combustion instabilities in lean premixed gas turbine combustor, linear thermoacoustic analysis model was developed in the current paper. A model combustor was selected for the model validation, which has well-defined inlet and outlet conditions and a relatively simple geometry, compared to the combustor in the previous works. Analytical linear equations for thermoacoustic waves were derived for a given combustion system. It was found that the prediction results showed a good agreement with the measurements, even though there was underestimation for instability frequencies. This underestimation was more obvious for a longer flame (i.e. wider temperature distribution) than for a shorter flame.

• Transactions of the Korean Society of Mechanical Engineers
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• v.11 no.1
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• pp.145-153
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• 1987

Stability limits of a double concentric jets flame and the structure of recirculation zone formed behind a thick burner rim were investigated. To control the flame stability, swirled secondary air flow ranging 0.13-0.71 of swirl number, and air, fuel, and mixture gas injection from an injection coaxial slit set on burner rim were examined. Flame stability limits, flame shapes, lengths of recirculation zone, temperature distributions, residence times, air ratios in the recirculation zone were measured. The following results were obtained. (1) Lean limits were considerably widened by a strong swirl because the recirculation zone was enlarged. (2) At fuel injection as well as mixture injection, lean limits were also extended. But, air injection had no effect on stability limits. (3) Injected gas seems to diffuse into the recirculation zone through its outer boundary surrounded the secondary air. Therefore, chemical structure in the recirculation zone with air injection coincides with that without injection. (4) Injection position had no effect on flame stability limits.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.9
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• pp.829-836
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• 2013

The combustion characteristics with variations in synthetic natural gas (SNG) compositions were studied in a lab-scale combustor. The objective of the current study is to investigate the flame stabilization, flame structure, and spectrometry in a non-premixed SNG flame with varying fuel compositions. For the analysis of light emission in SNG flames, we used a spectrometer. As experimental conditions, the fuel jet velocity at the nozzle exit $u_F$ was varied from 5 to 40 m/s and the coaxial air velocity $u_A$ was varies from 0 to 0.43 m/s. The experiments showed that the flame stability increased with the hydrogen component in SNG.