• Journal of Soil and Groundwater Environment
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• v.8 no.1
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• pp.27-34
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• 2003

In this study, potential degradation of MTBE and other gasoline oxygenates by pure culture ENV425 and mixed culture isolated from gasoline contaminated soil using butane as the sources of carbon and energy was examined and compared. Butane monooxygenases(BMO) of butane-grown ENV425 and mixed culture generated 1-butanol as a major metabolite of butane oxidation and addition of acetylene, specific inhibitor of monooxygenase, inhibited both butane oxidation and 1-butanol production. The results described in this study suggest that alkanes including propane, pentane, and butane are effectively utilized as a growth substrate to oxidize MTBE cometabolically. And also BTEX compounds could be the potential substrate of the MTBE cometabolism. Cell density also affected on the MTBE degradation and transformation capacity(Tc). Increasing cell density caused increasing MTBE degradation but decreased transformation capacity. Other result demonstrated that MTBE and other gasoline oxygenates, ETBE and TAME, were degraded by butane-grown microorganism.

• Proceedings of the Korean Institute of Industrial Safety Conference
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• 1998.05a
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• pp.7-11
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• 1998

고체추진제(solid propellant)는 연료와 산화제가 혼합/결합되어 있어 폭발적인 연소반응을 통하여 많은 에너지를 빠른 시간에 방출한다. 많은 에너지가 급격히 변환되는 과정에서 소량의 에너지가 음향에너지(acoustic energy)로 변환되는 것은 피할 수 없다. 이와 같이 원하지 않는 에너지의 변환이 어느 정도 이상을 넘을 때, 연소 불안정(combustion instability) 현상이 발생했다고 한다. 상당히 많은 로켓 모타들이 연소불안정현상으로 인하여 개발기간의 지연과 설계변경 등으로 경제적 손실을 야기하고 있다. (중략)

• Proceedings of the Korean Institute of Industrial Safety Conference
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• 2002.11a
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• pp.322-327
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• 2002

산화성고체는 우리 생활에 아주 유용한 화학물질로서, 표백제, 화약류, 산소발생제, 화공품, 합성 원료, 농약등의 여러 방면에 사용되고 있다. 한편, 반응성이 큰 것이 많고, 단독으로 또는 가연물과의 혼합에 의해서 폭발성 또는 폭발적 연소성을 가지는 경우가 있다. 이러한 위험성을 바르게 인식하고 안전한 취급을 하는 것 이산화제로 인한 사고를 예방하는데 중요한 요인이 된다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.217-220
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• 2009

This paper presents experimental results of Recess Characteristic of Swirl Coaxial Injector of fuel-rich gas generators. It was revealed that the internal impinging phenomenon played an important role in the spray characteristics, such as spray angle and breakup length.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.4
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• pp.82-91
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• 2003

Experiments to investigate the mixing performance of unlike doublet impinging jets are conducted. Reynolds number of simulants used in this study rages from 1.0 to 1.5 Cold flow test is performed to investigate the hydrodynamic effect and spray of the impinging jets are collected locally and calculated by using Rupe's mixing efficiency equation. Momentum exchanges and relative velocity ratio between two jets are taken as the main parameter to represent the effect of enlargement of the orifice diameter. As diameter ratio increases, the corresponding momentum ratio where maximum mixing efficiency occurs and relative velocity at the maximum mixing efficiency ranges 0.6 to 0.7, respectively. Penetration depth can be taken as a prominent parameter to estimate the mixing efficiency.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.5
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• pp.37-46
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• 2013

The gas jet from a coaxial porous injector for two-phase flows is discharged radially from the porous surface, which encloses the center liquid jet. Several hot-firing test using ethanol/nitrous oxide propellants was conducted to analyze the effect of oxidizer/fuel ratio on the combustion performance, and the uncertainty analysis was performed for the results. The characteristic velocity was affected by oxidizer/fuel ratio similarly with the results of CEA calculation except that the maximum characteristic velocity was appeared in the stoichiometric ratio. The characteristic velocity efficiency was increased as the oxidizer/fuel ratio increases.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.383-386
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• 2006

Several HTPB/AP and HTPB/AP/HMX propellants were investigated experimentally for ignition characteristics in subatmospheric pressure. The threshold ignition pressure was 4psia for HTPB/AP composite propellant. The partial replacement of AP in HTPB/AP composite propellant by $5\sim15%$ of HMX, HNIW showed improvements in the threshold pressure was below 0.4psia. This appears to be due to the exothermic dissociation characteristics of HMX and HNIW at lower temperature $(\sim220^{\circ}C)$ than that of AP. The ignition substance B/KNO3 was coated thinly on the propellant surface for better ignition effect. As a result, ignition delay time of 15% was improved. NC is applied to $B/KNO_3$ ignition substance as a secondary binder and $NC-B/KNO-3$ suspension solution is coated to the propellant surface.

• Journal of Life Science
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• v.2 no.2
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• pp.91-96
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• 1992

효소에 의한 carotenoid의 co-oxidationgus상은 lipoxygenasechrao하에서 지방산인 linoleic acid가 산화되어 이때 만들어진 free radical에 의해 carotenoid가 쉽게 산화되기 때문에 일어나는 현상이다. 이화같이 carotenoid의 co-oxidation에서 lipoxygenase는 free radical을 만들면서 반응속도를 빠르게 하는 촉매제의 역할을 다음과 같이 담당하고 있다고 할 수 있다. Lipoxygenase에 의한 carotenoid의 co-oxidation 현상을 처음 발견한 것은 대두가루를 밀가루와 혼합하여 사용할 때였다. 대두가루 속에 다량 함유된 lipoxygenase에 의해 밀가루의 carotenoid 색소가 표백되는 것을 보고 이 현상은 lipoxygenase에 의해 기질은 지방산이 산화되는 동안 caroenoid가 쉽게 co-oxidation되기 때문이라는 것을 알아내었다. 즉, carotenoid는 지질이 존재하는 반응시스템에서 항산화제로서 혹은 secondary substrate로서 작용한다고 할 수 있다.

• Fire Science and Engineering
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• v.13 no.4
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• pp.7-12
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• 1999

Thermal properties of EVA dust and its risks of coexisting with oxidizer were investigated by a pressure vessel. The decomposition of EVA dust with temperature using DSC and the weight loss with temperature using TGA were also investigated to find the thermal hazard of EVA dust. Using the pressure vessel which can estimate ignition and explosion of EVA dust coexisting with oxidizer by bursting of a rupture disc, many experiments have been conducted by varying the orifice diameter, heating rate, the weight ratio of the sample coexisting with oxidizer, and the species of oxidizer. According to the results of the thermal analysis of EVA dust, a little change of the decomposition initiation temperature with the heating rate could be found and the decomposition temperature zone of EVA dust was 250 to 50$0^{\circ}C$. The risk of EVA dust coexisting with oxidizer was increased as the orifice diameter was decreased. On the other hand, it was increased as the heating rate and the weight ratio of the sample coexisting with oxidizer were increased. In addition, the risk of EVA dust coexisting with oxidizer was affected by the decomposition temperature of the sample and oxidizer, respectively, at slow heating rate, but it was affected by the oxygen weight percent of oxidizer at fast heating rate.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.3
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• pp.67-72
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• 2006

Several propellants were investigated experimentally for ignition characteristics in subatmospheric pressure. The threshold ignition pressure was 4 psia for HTPB/AP composite propellant. The partial replacement of AP in HTPB/AP propellant by $5{\sim}l5%$ of HMX, HNIW showed that the improvements in ignition delay was over 50% and the threshold pressure was below 0.4 psia. This appears to be due to the characteristics of HMX and HNIW exothermic dissociated at the temperature(${\sim}220^{\circ}C$) love. than that of AP. The ignition substance $B/KNO_3$ was coated thinly on the propellant surface for better ignition performance. As a result, ignition delay time of 15% was improved. NC is applied to $B/KNO_3$ ignition substance as a secondary binder and $NC-B/KNO_3$ suspension solution is coated to the propellant surface.