• Journal of the Korean Applied Science and Technology
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• v.30 no.2
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• pp.320-332
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• 2013

The feed air to MSW incinerator influences on the residence time of combustion gas, removal of unburnt ash and exiting gas temperature. Thus the secondary air volume could present sufficient residence time which can maintain the exiting temperature over $850^{\circ}C$. The secondary air also relates directly with the turbulence in the inside of combustion chamber, which finally provide the stable combustion condition. The present study designed a modern incinerator for a field scale, and evaluation of the potential amount of primary air based on the daily combustible quantity. From the evaluated primary air volume, the secondary air flow rate could be estimated, and its dynamic behavior was verified. In addition, the obtained air volume enables to find an optimum operation condition of the combustion. As a result of the CFD simulation, the air ratio 75 : 25 between primary and secondary air amount was optimum ratio than design criteria 72 : 28. And the flow velocity ratio of front-back of secondary air jet nozzle was found excellent at 1 : 3. In addition, the result of applied to the plant, the removal efficiency of NOx and CO generation would concentration of CO.

• Nuclear Engineering and Technology
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• v.21 no.4
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• pp.294-301
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• 1989

The Axial Power Distribution Monitoring System(APDMS) program was developed to calculate a detailed axial power distribution using two-level excore detector, cold leg temperature and control rod position signals. The unnormalized two-level excore detector signals were corrected for the rod shadowing factor determined by control rod position and for the temperature shadowing factor calculated based on cold leg temperature. A shape annealing matrix was then applied to the corrected excore detector response to yield peripheral power. After the core average power was obtained using linear relationship bet-ween core average and peripheral power, the boundary point power correction coefficient was applied to core average power in order to obtain boundary power for both upper and lower core axial boundaries. Then, the axial power distribution was synthesized by spline approximation. In spite of burnup, power level, control rod postion and axial offset changes, the comparisons of axial power distributions between BOXER simulation program and APDMS results showed good agreements within 5% root mean square error for Kori Unit 3 Cycle 4.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.3
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• pp.258-263
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• 2012

In this paper the Chemical Propulsion Subsystem of COMS is briefly explained and some telemetries acquired by a series operations of CPS during the Launch and Early Operation Phase of COMS are presented. The pressure and temperature of pressurant tank telemetries are compared with the results of the developed computer program. The changes in pressure are due to the two major phases. The first one is the initialization phases of CPS composed of the venting phase to vent the helium gas in the pipe network from the downstream of the propellant tanks to the thrusters for safety, the priming phase to fill the vented pipe network with oxidizer and fuel respectively and then the pressurization phase to pressurize the ullage of propellant tank to regulated pressure. And the other is the apogee engine firings in which COMS CPS is in the orbit raising phase to use helium as a pressurant to keep the pressure of propellant tank as the liquid apogee engine get fired until COMS reached to the target orbit. This program can be applicable to prepare basis design data of the next Geostationary Satellite CPS.

• Asia-pacific Journal of Multimedia Services Convergent with Art, Humanities, and Sociology
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• v.7 no.4
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• pp.243-250
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• 2017

A fire phenomenon of a solid such as wood involves a phenomenon in which solid is heated from the outside and the gas generated through the thermal pyrolysis process of the material is burnt. The thermal pyrolysis phenomenon of the solid is a phenomenon in which the amount of energy incident from the outside, the amount of heat dissipation of the solid material, the heat transfer between the solid material and the surroundings including the amount of heat transfer to the air adjacent to the solid surface, and the fraction of oxygen in the air. In this paper, we calculate the required ignition temperature to simulate the fire phenomenon as simple as possible. By using cone calorimeter, the ignition time was measured by variously controlling the heat flux flowing into the wood specimen by using various wood specimens. The user friendly program is developed for calculation of the ignition temperature. Five different woods such as low density MDF, high density MDF, plywood, douglas fir and PB with various thickness are considered. The ignition temperatures suggested in this paper can be used for fire propagation analysis for woods.

• Journal of Korean Elementary Science Education
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• v.28 no.4
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• pp.467-475
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• 2009

This study is to enquire about ideals on combustion and to propose of teaching program using the history a science in '5. Combustion and Extinguishing' unit of elementary school science textbook in 6th grade. For this purpose, investigation questionnaires based on preceding research and science textbook are developed. The reliability of the questionnaires is .784, and the questionnaires are applied to 247 students in T elementary school in Busan. Through the results of the investigation, scientific conceptions existed in some parts. But some misconceptions still existed especially (question 1), substance's changes (question 7), formation process of product (question 13), combustibles among requirements of combustion. The patterns of the misconception are similar to historical misconceptions about combustion. Besides, the discoveries and inventions of combustion have some points about correcting misconceptions. Thus the five step teaching programs on combustion which were applied to history of the science are suggested. The confidence of the developed programs was verified as being 'excellent' by specialists. This program will be applied to think deeply about combustion in elementary school lesson and useful to introduce the history of science.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 2008.04a
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• pp.179-186
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• 2008

현재 대부분의 산업용 열기관은 효율을 높이기 위하여 연소에 사용되는 공기를 예열하는 방법을 사용한다. 하지만, 산업용 열기관에서 평균적으로 발생되는 $1000^{\circ}C$ 이상의 배기가스는 일반 금속 열교환기에는 적합하지 않다. 이에 반해 세라믹 열교환기의 경우 고온에서 견디는 장점이 있다. 본 연구에서는 기본적인 열교환기 설계 이론을 이용하여 설계프로그램을 제작하였다. 또한 세라믹 열교환기 내 열 유체 거동을 CFD 상용코드인 FlUENT 6.2를 이용한 전산해석을 수행하여 설계결과를 비교 검증하였다. 설계 결과에서 휜의 형태 변화에 따라 열전달율과 온도구배는 무시할 수 있을 정도로 작았으나, 압력강하는 크게 변동되는 결과가 도출되었다. 제한된 모듈 크기에서 휜 간거리는 휜의 두께에 비해 약 3배 이상 클 경우가 적당하며, 판(plate)의 두께는 작을수록 압력손실이 적고, 열전달율이 상승하지만 두께가 너무 얇게 된다면 제작상의 어려움이 생긴다. 향후 연구에서는 단순한 구조에서 벗어나 off-set이나 판형구조를 고려하여 설계함으로서 열전달 면적을 넓히거나 난류유동을 발생시켜 열전달율을 높이는 연구를 진행 할 필요가 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.1
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• pp.79-85
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• 2008

Generally Solid Rocket Motor(SRM) has advantages like this - safety, simplicity and flexibility in design and manufacturing process. However, once propellant grain shape and nozzle throat area are determined, modification of thrust magnitude is nearly impossible. Recently, methods for controlling the thrust magnitude of SRM are vigorously developed. This paper predicts internal ballistic performance variation, especially thrust of SRM by means of Linear Approximation according as chamber pressure or nozzle throat area is changed. The results predicted by the proposed method are good agreement with the those of exclusive Ballistic Performance Prediction Program(SPP).

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.289-292
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• 2005

Because of accumulation of operation time, the performance of main components(compressor, combustor, turbine, etc.) come to be deteriorated in gas-turbine engine. So, high reliability and minimun of expense are important problem for engine manufacturer and user in operation of gas-turbine engine. In this study, the diagnostic code of the engine performance using the thermodynamic sensitivity between the sensed parameters and the health parameters has been developed without an application of the commercial program. The single performance deterioration of the turbo-shaft engine has been estimated with this code.

• Proceedings of the KIEE Conference
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• 2006.07d
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• pp.1815-1816
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• 2006

소음은 환경 오염원의 하나로서 사람에게 육체적, 정신적 피해를 발생시킨다. 이에 소음 제어 기술의 필요성이 증대하였고, 그 중에서 제어가 까다롭고 고비용을 요구하는 저주파 소음 제어 기술의 개발이 확대되고 있다. 따라서 본 연구에서는 저주파의 주기적인 특성을 가지는 1차원 평면파 소음에 대한 능동 제어를 위해 기존의 적응 피드포워드 방법의 단점을 보완하는 적응 피드백 방법을 이용한 능동 소음 제어 시스템을 구성하고 능동 소음 제어 실험을 수행하였다. 이를 위해 소음원과 제어 음원을 가지는 덕트 형상의 실험 장치를 구성하였다. 제어기 설계를 위해 전파 소음을 예측하는 선형 예측법을 적용한 적응 디지털 필터를 구성하였으며 적응 알고리즘으로 Filtered-X LMS 알고리즘을 이용하였다. 제어기는 제어 알고리즘을 프로그램화하여 DSP에 입력함으로써 구성하였다. 실험에 사용된 소음은 500[Hz] 이하의 단일 주파수의 정현파 소음을 사용하였으며, 실험결과 음압 감소의 효과를 볼 수 있었다. 능동 소음 제어의 기술을 개발하여 하드웨어(덕트)의 모양 및 구조, 제어기의 종류 및 처리 속도, 주파수나 크기와 같은 특성이 급격히 변하는 소음의 경우에 능동적으로 소음을 제어할 수 있으며, 저주파 소음을 발생시키는 관형 연소기와 같은 장치 및 여러 분야에 응용이 가능하도록 하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.303-306
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• 2008

After the successful flight test of X-43A, U.S. Airforce is developing missile-type X-51A SED (Scramjet Engine Demonstrator-Wave Rider). X-51A using PWR (Pratt and Whitney Rocketdyne) X-1 hydrocarbon fueled scramjet engine will have a ground test in 2008 and flight test in 2009. Technologies established though the X-51A program will be transferred to DARPA's Falcon program developing HTV (Hypersonic Test Vehicle)-3X and HCV (Hypersonic Cruise Vehicle). Present paper is an overview of propulsion core technologies of X-51 such as regenerative cooling of engine structures and combustion using liquid/supercritical JP-7 fuel.