• Proceedings of the Korea Air Pollution Research Association Conference
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• 1999.10a
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• pp.277-279
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• 1999

대기 중으로 배출되는 $CO_2$, CH$_4$, $N_2$O, $O_3$, CFC 등은 지구온난화에 기여하고, 이러한 온실기체들은 여러 경로를 통해서 대기로 배출되고 있다. 배출원별 온실기체의 기여도를 보면(Green peace, 1997) 화석연료 연소의 경우가 58%로 가장 높고, 농업과 토지이용의 변화에 의해 18%, 17%, 그리고 도시쓰레기의 매립에 의해서도 약 3%정도 기여하는 것으로 보고되었다. 주요 온실기체에 대한 대기 중 농도가 과거보다 현저하게 증가되었음이 확인되고 있고, $CO_2$의 경우 년간 증가율이 0.5%, CH$_4$의 경우는 1%, 그리고 $N_2$O의 경우는 약 0.2% 정도로 보고되고 있다.(Bouwman, 1990).(중략)

• Resources Recycling
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• v.23 no.6
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• pp.47-53
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• 2014

Effective treatment and energy conversion technologies are necessary due to the ban of the dumping of organic waste including the sewage sludge. In this study, the kinetics of pyrolysis and combustion were derived in a TGA and thermobalance reactor, which is essential for thermal conversion of sewage sludge to energy. Three steps are shown for the pyrolysis in TGA and the different pre-exponential factors and activation energies are derived depending on the temperature range. Three models of gassolid reaction were applied to the reaction kinetics analysis for the combustion of sewage sludge char and shrinking core model was an appropriated model. Apparent activation energy and pre-exponential factor were evaluated and the effect of oxygen partial pressure was examined.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.10
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• pp.1011-1016
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• 2008

Jet-A spray and combustion were numerically analyzed in annular type combustor model using KIVA3V. The combustor geometry have 6 dilute holes. Swirl effect and thermal NO were considered in this investigation to analyze mixing and combustion characteristics. Fuel vapor, flame temperature, NO generation were investigated for various spray angle. As increase of spray angle, Jet-A vapor appeared uniformly in primary zone and evaporation rate was increased. Mixing between fuel vapor and ambient gas was enhanced as increase of spray angle. As a result, high temperature region appeared widely and thermal NO generation rate was increased.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.150-155
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• 2010

Liquid rocket injectors play crucial roles on propulsive performance, combustion stability, and heat transfer characteristics. Nevertheless, their developments have mainly relied on empirical methods and expensive hot-firing tests due to lack of fundamental understanding of high pressure combustion phenomena in the near-injector regions. The present study was motivated by recent efforts to develop reliable modeling of liquid rocket combustion. The turbulent combustion model based on the flamelet concept has been extended to take into account real-fluid behaviors occurred at supercritical pressures, and validated against measurements for a cryogenic nitrogen injection, a non-premixed turbulent jet flame at atmospheric pressure, and a LOx/$GH_2$ coaxial shear injector at a supercritical pressure.

• Journal of The Korean Association For Science Education
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• v.31 no.6
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• pp.942-957
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• 2011

The purpose of this research was to examine the concept of elementary school teachers of combustion. The participants were selected from the elementary school teachers who had various career experiences, 6th grade science teaching experiences, and academic backgrounds on science. For the purpose of this study, 12 elementary school teachers took the concept-test formed five questions on combustion and were interviewed. The concept-test was composed with 'The definition of combustion', 'The reason that the candle was blown out when glass was closed.', 'The existence of oxygen and carbon dioxide of before and after combustion in glass', 'Combustion of iron', 'Combustion products'. And the collected data by semi-structured interviews based on responses to the concept-test. During the analysis of the data, additional interviews by phone, e-mail and Internet messenger were conducted if necessary. The answers to each question were classified into three levels: (Scientific-concept(S), Partial-concept(P), Misconcept(M)). The research results showed that all teachers had misconceptions or partial-concept of more than 50 percent of each question. Teachers who had the 6th grade science teaching experience acquired scientific concepts of the combustion more than teachers who did not have the 6th grade science teaching experience. We should develop visualization materials about the change of gases during combustion and use these materials for implementation of the scientific concept.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.88-94
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• 2002

For the pressurized propellant supply system of liquid rocket, feed pressure is determined with respect to the chamber pressure of normal combustion state. However, during ignition period the initial chamber pressure is atmosopheric. This may cause overflow, hard-start and even critical damage for the engine. This paper proposes an improved propellant feed system for the stable combustion of liquid rocket. The proposed system utilizes the cavitating venturi to provide stable mass flow rate. Cavitating venturi offers unique flow control capabilities at normal and abnormal combustion state, because flow rate is soley dependent on the upstream absolute pressure and fluid properties, but independent on th downstream condition. Experimental variables are propellant feed pressure and chamber pressure. The effectiveness of cavitating venturi increased when the ratio of actual feed pressure to the cavitating venturi design pressure is increased. It is also found that Kerosene if more effective to supply stable mass flow rate than LOx.

• Proceedings of the Korean Nuclear Society Conference
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• 2001.05a
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• pp.383.1-383
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• 2001

• Proceedings of the Korean Nuclear Society Conference
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• 1999.10a
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• pp.246-246
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• 1999

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.1
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• pp.95-103
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• 1999

Low pressure combustion characteristics of the composite solid propellants were studied in terms of the propellant burning rate, ignition processes, and the structure of the extinguished surfaces. Optical Vacuum Strand Burner(OVSB) system was designed and configured for this purpose. Burning rates of the propellants were measured at subatmospheric pressure by developed test method in OVSB. The ignition and combustion phenomena of the studied propellants in the combustion chamber of OVSB were recorded and analyzed with the camera and VCR(30 frames/s). Burning surfaces of the propellants were extinguished by rapid depressurization method and analyzed with Scanning Electron Microscope(SEM).

• Journal of the Korean Chemical Society
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• v.43 no.2
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• pp.150-155
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• 1999

The ignition delay times behind reflected shock waves in $C_2H_6-O_2-Ar$ systems containing $CH_3Cl$ were measured for the range of temperatures between 1270 and 1544 K. The measurements indicated that $CH_3Cl$ inhibited the ignition of ethane ignition and the inhibition effects increased with increasing $CH_3Cl$ concentration. To clarify the inhibition effects of $CH_3Cl$ from the viewpoint of the reaction mechanism, computational analyses were performed in $C_2H_6-CH_3CI-O_2-Ar$ mixtures.