• 산업기술연구
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• 제20권B호
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• pp.45-53
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• 2000

A numerical study is done on the thrust vector control using gaseous secondary injection in the rocket nozzle. A commercial code, PHOENICS, is used to simulate the rocket nozzle flow. A $45^{\circ}-15^{\circ}$ conical nozzle is adopted to do numerical experiments. The flow in a rocket nozzle is assumed a steady, compressible, viscous flow. The exhaust gas of the rocket motor is used as an injectant to control the thrust vector of rocket at the constant rate of secondary injection flow. The injection location which is on the wall of rocket is chosen as a primary numerical variable. Computational results say that if the injection position is too close to nozzle throat, the reflected shock occurs. On the other hand, the more mass flow rate of injection is needed to get enough side thrust when the injection position is moved too far from the throat.

• 동력기계공학회지
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• 제16권3호
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• pp.10-15
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• 2012

Recently we have a growing interest in environmental pollution and alternative energy. Diesel engine is generally used to produce the power on the ground and the sea. However, the combustion characteristics are changed on account of the wear of fuel system and the altered ambient condition of the combustion chamber by the increment of the engine operation hour. Therefore combustion characteristics on fuel injection timing are experimentally investigated to find out the optimum fuel injection timing in the case of the aged diesel engine using biodiesel blend oil. Cylinder pressure, rate of pressure rise, rate of heat release and combustion gas temperature are risen by the advancing fuel injection timing, while the exhaust gas temperature and soot emission level are decreased by the advancing of fuel injection timing. The least specific fuel oil consumption is indicated at BTDC $26^{\circ}$ CA on the 75%load and at 1800rpm.

• 한국해양공학회:학술대회논문집
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• 한국해양공학회 2006년 창립20주년기념 정기학술대회 및 국제워크샵
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• pp.265-268
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• 2006

The preliminary design of a deep-sea injection system for carbon dioxide ocean sequestration is performed. Common functional requirements for a deep-sea injection system of mid-depth type and lake type are determined, Liquid transport system, liquid storage system and liquid injection system are conceptually determined for the functional requirements. For liquid injection system, the control of flow rate and temperature of liquid $CO_2$ in the injection pipe is needed in the view of internal flow. The function of depressing VIV(Vortex Induced Vibration) is also required in the view of dynamic stability of the injection pipe. A case study is performed for $CO_2$ sequestration capacity of 10 million tons per year. In this study, the total number of injection ships, the flow rate of liquid $CO_2$ and the configuration of a injection pipe are designed. The static structural analysis of the injection pipe is also performed. Finally the preliminary design of a deep-sea injection system is proposed.

• Journal of Advanced Marine Engineering and Technology
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• 제34권1호
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• pp.37-45
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• 2010

본 논문에서는 박용 디젤엔진에서 NOx와 Soot의 배출량을 동시에 줄이기 위해 파일럿 분사의 특성을 알아보기 위해서 수치해석을 수행하였다. 수치해석결과의 압력 선도는 실험 결과와 일치시켜 1.6% 범위의 적은 오차에서 예측함으로써 수치해석의 신뢰성을 검증하였고 총 분사량이 고정된 상태에서 분사시기, 분사휴지 기간, 분사율을 주요 파라미터로 적용하였다. 파일럿 분사시기의 변화는 연료의 자발화와 열발생률에 영향을 주는 것을 결과로부터 알 수 있었다. 결과로부터 분사휴지기간이 $10^{\circ}$CA, 분사율이 0.022kg/s인 경우에 실린더의 압력 손실이 없는 범위에서 NOx와 Soot를 동시에 저감하는 결과를 얻을 수 있었다.

• 오토저널
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• 제7권1호
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• pp.35-42
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• 1985

This paper describes an experimental study of the effect of injection timing on the combustion characteristics in four stroke cycle diesel engine with direct injection type combustion chamber. The effect of injection timing and compression ratio of engine on the combustion characteristics are investigated. Experimental results of combustion characteristics in cylinder show that the combustion pressure and the rate of pressure rise decrease in accordance with the retard of fuel injection timing. It is observed that the rate of pressure rise in cylinder is increased an increase in the compression ratio of engine. The effect of the fuel injection timing on the frequency of cylinder pressure brings about the same trend of the maximum rate of pressure rise in cylinder.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.551-554
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• 2006

Inhibition of propellant temperature rising in liquid propulsion rocket using cryogenic fluid as a propellant is very important. Especially propellant temperature rising during stand-by after filling and pre-pressurization can bring into cavitation in turbo-pump. One of the method preventing propellant temperature rising in cryogenic feeding system is recirculating propellant through the loop composed of propellant tank, feed pipe, and recirculation pipe. The circulation of propellant is promoted through gas-lift effect by gas injection to lower position of recirculation pipe. In this experiment liquid oxygen and gas helium is used as propellant and injection gas. Under atmospheric and pressurized tank ullage condition, helium injection flow-rate is varied to observe the variation of recirculating flow-rate and propellant temperature in the feed pipe. There is appropriate helium injection flow-rate for gas-lift recirculation system.

• 한국농업기계학회:학술대회논문집
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• 한국농업기계학회 1996년도 International Conference on Agricultural Machinery Engineering Proceedings
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• pp.500-510
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• 1996

A Direct injection -mixing total -flow -control sprayer was developed and evaluated . The system provided precise application rates and minimized operator exposure to chemicals as well as providing a possibility for recycling container so f unused chemicals that can causes environmental contamination. Chemicals were metered and injected proportionally to the diluent flow rate to provide constant concentrations. The main diluent flow was varied in response to changes in travel speed. Experimental variables of the sprayer were the control interval, the sensitivity of flow regulating valve, the tolerance of control object and the sensitivity of the injection pump system. The optimal performance of the flow control system was with an average response time of 8.5 sec at an absolute steady state of error of 0.067 L/min (0.8% of flow rate). The average response time of the injection rate was -0.53 sec and the coefficient of variation (CV) of concentration was 3.2%.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2010년도 춘계학술대회 논문집
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• pp.503-504
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• 2010

• 한국수소및신에너지학회논문집
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• 제27권2호
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• pp.211-219
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• 2016

To develop an ash separator for the solid fuel chemical looping combustion system, effects of operating variables such as solid injection nozzle velocity, diameter of solid injection nozzle, gap between solid injection line and vent line, vent line inside diameter, and solid intake height on solid separation rate and solid separation efficiency were measured and discussed using heavy and coarse particle and light and fine particles mixture as bed material in an acrylic fluidized bed apparatus. The solid separation rate increased as the solid injection nozzle velocity and the diameter of solid injection nozzle increased. However, the solid separation rate decreased as the gap between solid injection line and vent line, the vent line inside diameter, and the solid intake height increased. The solid separation efficiency was in inverse proportion to the solid separation rate. In this study, we could get high solid separation rate up to 2.39 kg/hr with 91.6% of solid separation efficiency.

• 한국산학기술학회논문지
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• 제17권3호
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• pp.270-275
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• 2016

본 연구에서는 디젤 연료 온도에 따른 실제 분사되는 연료량, 분사율 그리고 거시적 분무 발달 과정에 대한 특성을 파악하고자 하였다. 시험 결과 동일한 분사 시작 신호 및 분사 기간 신호를 입력하였음에도 불구하고, 연료 온도가 낮아짐에 따라 실제 연료 분사량이 감소하는 경향을 보였다. 분사율 측정 결과를 통해 연료 온도가 낮은 조건에서 실제 분사 시작 시점이 지연되며, 실제 분사가 유지되는 기간이 짧아지는 것을 확인하였으며, 이를 통해 실제 분사되는 연료량 저감에 대한 근거를 찾을 수 있었다. 거시적 분무 이미지 촬영 결과를 연료 온도 별 분무 도달 거리로 표현하여 비교 하였으며, 낮은 연료 온도 조건에서 분무 미립화 성능 악화로 인해 분무 도달 거리가 길어지는 것을 확인하였다. 저온 조건에서의 연소 개선을 위해 향후 시도할 선행 평가로서 피스톤 타켓팅 평가를 수행하였으며, 이른 시기에 분사되는 파일럿 연료가 크레비스 영역으로 유입되는 것을 확인하였으며, 이를 통해 파일럿 분사 방식 적용 시 연료량 분배 및 분사 시기 선정이 매우 중요한 인자가 됨을 파악하였다.