• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.67-70
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• 2008

Production and dissipation of turbulent structure in a swirl stabilized combustor was investigated using three-dimensional Large Eddy Simulation analysis. The combustor of concern is the LM6000, lean premixed dry low-NOx annular combustor, developed by GEAE. Inlet condition was based on experimental data. Strong vortex breakdown in main stream, vortex ring proceeding downstream, and the turbulent structure periodically oscillating have been observed. Reasonable agreement was obtained by comparison of the results with experiments and previous LES studies.

• Journal of Korean Institute of Fire Investigation
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• v.11 no.1
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• pp.111-126
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• 2007

In this study, we drew identification techniques of cigarette fires through the cases analyses of the combustion characteristics, the combustion time, the combustion temperature, the combustion test of smoldering materials and the reappearance experiments of cigarette fires. To initiate fires by cigarette fire, the conditions of oxygen supply, combustible materials must be satisfied. On the other hand, fires were not spreaded easily under the insufficient combustion conditions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.05a
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• pp.131-137
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• 1996

HTPB/AP/Al이 주성분인 2종의 혼합형 추진제를 대상으로 4종의 금속선(Ag, Cu, Al, Ni-Cr)윰 각각 삽입하여 금속선의 직경(0.1~0.8mm)과 연소 압력에 따른 금속선에 인접한 고체 추진제의 연소 속도 증가비($r_w$/$r_sb$)와 압력 지수(n)의 변화를 고찰하였다. 금속선을 추진제에 삽입함으로써 추진제의 $r_w$/$r_sb$ 는 크게 중가하였고, 1000 psia의 압력에서의 최대 6.59배 증가하였다. 그러나 녹는 점이 비교적 낮은 Al 선이나 Ag선은 금속선 직경이 작아짐에 따라 한계 직경에서 $r_w$가 급격히 감소하는 최대값이 존재하였다. 자연 발화 온도와 금속선으로 전달되는 열원인 연소 기체 불꽃 온도로 구성된 무차원군을 Buckingham pi 정리에 의해 구해진 $r_w$/$r_sb$ 에 대한 기존의 무차원 실험식에 추가로 적용하여 계산해 본 결과, 자연 발화 온도는 고려하지 않고 금속선의 녹는 점과 연소 기체의 불꽃 온도를 무시한 Hsing 의 실험식에 의해 계산된 결과보다 표준 편차가 45%이상 줄어듬을 알 수 있었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.450-459
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• 2010

고체추진제의 첨가제 또는 연료로써 주로 사용되는 알루미늄 단일 입자 연소시험 장비를 제작하고 연소 실험을 수행하였다. 산화 알루미늄으로 피복된 금속입자는 약 30~100 ${\mu}m$의 크기를 사용하였다. 단일 입자는 Electrodynamic Balance (EDB) 방법에 의해 공중 부양된 상태로, 중력에 의한 영향이 배제되어 금속입자 고정용 또는 측정용 장치들의 접촉에 의한 열손실을 제거시켜 실험 정확도를 높였다. Standard Hyperbolic Electrodynamic Levitator (SHEL) 내에서 부양된 입자에 $CO_2$ 레이저를 사용하여 점화시킨 후, 입자로부터 방사되는 열복사를 이용한 two wavelength pyrometry를 적용하여 알루미늄 입자 크기에 따른 연소시간, 평균 화염온도, 점화온도, 점화시간을 획득하였으며, 단일 알루미늄 입자의 점화-연소특성을 평가하였다.

• Journal of Korean Society of Environmental Engineers
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• v.31 no.6
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• pp.442-448
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• 2009

To evaluate the combustion mechanism of each droplet cluster downstream of the premixed spray flame, the simultaneous time-series measurements were conducted by using optical measurement system consisting of laser tomography, multi-color integrated Cassegrain receiving optics (MICRO) and phase Doppler anemometer (PDA). Furthermore, the group combustion number of droplet cluster was estimated experimentally, and the combustion mechanism of droplet cluster was examined applying the theoretical analysis. The group combustion number, $G_c$, was experimentally estimated about all droplet cluster verified by planar images, and it was classified into the internal group combustion mode and the external group combustion mode according to the theoretical analysis. It is found that there are cases in which the group combustion number estimated experimentally for droplet cluster agree or disagree with the classification by theoretical analysis. The reason of disagreement is considered due to that the group combustion number was only estimated by the geometrical arrangement of droplets in cluster, and that the actual phenomenon is three-dimensional but the measurement system is two-dimensional.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.263-266
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• 2009

The mainly objectives of this study was a combustion dynamics and instability characteristics in a model gas turbine dump combustor which is the scale down of GE 7FA+e DLN 2.6 gas turbine combustor. Model gas turbine injector has 2-stage swirl vane and it’s reduced 1/3 size of the original one. The shape of plenum and combustor were designed for similar acoustic characteristics. Inlet air was preheated to $200{\sim}400^{\circ}C$. The flow velocity at mixing nozzle was 30 to 75 m/s and equivalent ratio was 0.4 to 1.2. The combustor length was varied for different acoustic characteristics to $375{\sim}700\;mm$. As the result, this research have been show the combustion instability was observed at lower equivalence ratios ($\Phi$ < $0.5{\sim}0.6$) and higher equivalent ratios ($\Phi$ > $1.1{\sim}1.2$).

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.5
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• pp.24-31
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• 2010

Combustion-stability rating of impinging-jet injector is conducted numerically using hot-fire simulation in a subscale chamber with the five-element injector head. A sample F(fuel)-O(dxidizer)-O-F impinging-jet injector is adopted. In this work, instantaneous chemical reaction is adopted for hot-fire simulation based on the assumption that mixing process of fuel and oxidizer streams is controlling. The model chamber was designed based on the methodologies proposed in the previous work regarding geometrical dimensions and operating conditions. The present stability boundaries are in a good agreement with air-injection and hot-fire experimental data. The proposed numerical method can be applied cost-effectively to stability rating of jet injectors when mixing of fuel and oxidizer jets is the dominant process in instability triggering.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.9
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• pp.703-709
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• 2020

Pintle injector is known to have been adopted as injector of Lunar Module Descent Engine (LMDE) and contributed to success of the Apollo program and recently used in merlin engine. In this study, 500N Lab-Scale pintle injector thruster was manufactured and the combustion experiment with LOx/GCH4 was conducted. However, the proto-type thruster was showed some problems, such as low combustion efficiency and melting of pintle tip. To solve these problems, the flow guide in pintle tip was suggested through the CFD simulation. After addition of flow guide module, the combustion efficiency increased and pintle tip did not melt until the end of combustion.

• Fire Science and Engineering
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• v.25 no.3
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• pp.1-7
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• 2011

This paper studied analysis of deflagration rapid propagation of burning through only a few second and fire cause into the Busan indoor shooting range. We carried out combustion experiment of sound-absorbing materials extensively used, to analyze propagation path of burning in indoor shooting range. From the experimental results, general sound-absorbing materials were rapid burned simultaneously with ignition and in case of attached gunpowder residue, they were burning about tripled by comparison with general sound-absorbing materials. The incombustibility sound-absorbing materials had all gone out simultaneously with ignition, but they were burning similar to general type materials in case of attached gunpowder residues. In order to analysis of the cause of fire, we calculated kinetic energy of bounced off bullet, from result, if the bounced off bullet impacted gunpowder residues, the gunpowder residues were possible to ignite by the bullet.

• 한국연소학회:학술대회논문집
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• 2002.06a
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• pp.237-246
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• 2002

가압유동층연소로(bed dia. 0.17m, freeboard dia. 0.25, total height 5m)에서 국내무연탄을 연소시켜 이에 대한 탈황특성을 고찰하였다. 실험은 압력($2{\sim}6atm$), 요동층온도(($850{\sim}950^{\circ}C$), 과잉공기(10, 20, 30,%)등의 조건과, 탈황을 위한 Ca/S몰비(($0.8{\sim}4.8$)가 탈황특성에 미치는 영향을 고찰하였다. 결과적으로, 본 연구의 실험범위에서 연소효율은 $80{\sim}99%$를 보였고, 연소온도, 압력 그리고 과잉공기가 증가 할수록 증가하였다. 배가스중의 $SO_2$배출농도는 압력, Ca/S몰비가 증가함에 따라 감소하였다. 탈황율은 상압에서 층(bed)온도의 증가에 따라 감소하였다. 운전압력이 증가함에 따라 탈황율의 감소폭이 둔화되었다. 과잉공기가 증가함에 따라 탈황율은 증가하는 경향을 나타냈다. 각각의 운전압력에서 과잉공기의 증가에 따라 약 10%의 증가폭을 보였다. 국내무연탄을 연소하는 경우 운전압력 4atm일 때 Ca/S몰비는 4이상 주입하여야 하고, 6atm일 때 Ca/S 몰비가 2.5이상주입하여야 150ppm이하를 보여 배출규제치를 만족하는 것을 보였다.