• Journal of Advanced Marine Engineering and Technology
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• v.35 no.1
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• pp.46-52
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• 2011

A study on the improvement for cycle efficiency of closed-type ocean thermal energy conversion (OTEC) was studied to obtain the basic data for the optimal design of cycle. For that, OTEC cycle with a generator, a reheater and a multi-turbine was simulated and analyzed. The basic thermodynamic model for OTEC is Rankine cycle and the surface seawater of $26^{\circ}C$ and deep seawater of $5^{\circ}C$ were used for the heat source of evaporator and condenser, respectively. Ammonia is used as the working fluid. The cycle efficiency increased when generator is added with 0.9 generator effectiveness. When the reheater and multi-turbine are applied in the basic cycle, the cycle efficiency showed 3.14% and the capacity of heat exchanger decreased for same total cycle power. For the OTEC cycle with the generator, the reheater and the multi-turbine showed the highest cycle efficiency and increased the efficiency by more than 6.5% comparing with the basic OTEC cycle.

• Journal of Advanced Marine Engineering and Technology
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• v.33 no.8
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• pp.1107-1115
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• 2009

The strengthened regulations for atmospheric emissions from ships like MARPOL Annex VI have caused a necessity of new, alternative power system in ships for the low pollutant emissions and the high energy efficiency. This paper attempts to investigate the configuration of SOFC/GT hybrid power system for marine applications like LNG tanker and to analyze the influence of design parameters on the system performance. The simulation results provide the basic data for the design and efficiency improvement of SOFC/GT hybrid system and indicate the guidelines for the safe system operation.

• Plant Journal
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• v.10 no.4
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• pp.24-28
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• 2014

During this study, number of fan by ambient air temperature that condenser pressure satisfies steam turbine exhaust pressure condition with intervals of $3^{\circ}C$ within the 150 MW thermal power plant site temperature range of $-17.1^{\circ}C$ to $36.7^{\circ}C$ was reviewed. An air cooled condenser changes its operating pressure influenced by cooling air circulation amount by atmospheric temperature and number of fan. For stable power plant operation, these were confirmed to maximize a quantity of air-cooled condenser fans at above or equal from design ambient temperature and to reduce an amount of circulating air to an air cooled condenser by depending on a quantity of fan considering exhaust pressure operation condition of a steam turbine at below design ambient temperature.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.6
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• pp.53-59
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• 2010

This research aims in finding a more optimal ejector size for evacuating engine exhaust gasses and 20% of the cell cooling air. The remaining 80% of cell cooling air pumped into the test chamber is separately exhausted from the test chamber via a discharge port fitted with flow control valves and vacuum pump. Unlike its predecessor this configuration utilizes a smaller capture area to improve pressure recovery. The modified ejector size has a diameter of 1100mm enough to evacuate 66kg/s jet engine exhaust in addition to about 20%, 24kg/s of the cell cooling air tapped from the sterling chamber. This configurations has an area ratio of the engine exit and ejector inlet of about 1.2. Simulation results of the proposed ejector configuration, indicates improved pressure recovery.

• Journal of Navigation and Port Research
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• v.36 no.5
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• pp.349-355
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• 2012

In this study, for the purpose of reduction of $CO_2$ gas emission and to increase recovery of waste heat from ships, the ORC(Organic Rankine Cycle) is investigated and offered for the conversion of temperature heat to electricity from waste heat energy from ships. Simulation is performed with waste heat from the exhaust gasse which is relatively high temperature and cooling sea water which is relatively low temperature from ships. The result shows that 1,000kW power generation is available from exhaust gas and 600kW power generation is available from sea water cooling system. Different fluid is used for simulation of the ORC system with variable temperature and flow condition and efficiency of system and output power is compared.

• Proceedings of the KSME Conference
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• 2001.06d
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• pp.782-789
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• 2001

Local heat/mass transfer and friction loss in a square duct roughened with various types of continuous and discrete rib turbulators are investigated. The combined effects of the gap flows of the discrete ribs and the secondary flows are examined for the purpose of the reduction of thermally weak regions and the promotion of the uniformity of heat/mass transfer distributions as well as the augmentation of average heat/mass transfer. The rib-to-rib pitch to the rib height ratio (p/e) of 8 and the rib angles of 90 and 60 deg are selected with $e/D_{h}=0.08$. The vortical structure of the secondary flows induced by the parallel angled arrays are quite distinct from that induced by the cross angled arrays. This distinction influences on heat/mass transfer and friction loss in all the tested cases. The gap flows of the discrete ribs reduce the strength of the secondary flows but promote local turbulence and flow mixing. As a result, the fairly uniform heat/mass transfer distributions are obtained with two row gaps.

• Journal of Advanced Marine Engineering and Technology
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• v.30 no.1
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• pp.22-29
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• 2006

Gas turbine engine among Principal internal combustion engines has been mainly applied as an aero and industrial Power plant. In order to increase its thermal efficiency. it has been raised their pressure ratio of compressor and the turbine inlet temperature. To operate above the limit temperature of turbine material, turbine nozzle vanes should be cooled. For this the cooling air is bled from the compressor section of 9as turbine. Meanwhile, to keep high thermal efficiency of 9as turbine, turbine vanes are to be cooled by using small cooling air Therefore, the complex cooling passages are requested to be designed and evaluated the effectiveness of vane cooling by measuring turbine vane temperature. But it is very difficult or impossible for us to measure local turbine temperatures at actual temperature When local heat transfer coefficients are known these can be calculated, therefore this study has been investigated on obtaining these coefficients of turbine vane at room temperature using TLC.

• Journal of Advanced Marine Engineering and Technology
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• v.36 no.5
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• pp.595-602
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• 2012

In this study, for the purpose of reduction of $CO_2$ gas emission and to increase recovery of waste heat from ships, the ORC (Organic Rankine Cycle) is investigated and offered for the conversion of temperature heat to electricity from waste heat energy from ships. Simulation was performed with waste heat from the exhaust gasse which is relatively high temperature and cooling sea water which is relatively low temperature from ships. Various fluid is used for simulation of the ORC system with variable temperature and flow condition and efficiency of system and output power is compared. Finally, 2,400kW output power is obtained by system optimization of the preheater and reheater utilizing waste heat form sea water cooling system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.7
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• pp.547-551
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• 2013

Mass averaged and core enthalpy in the arc jet flow are obtained experimentally. The experiment is made for the 150kW Huels type arc-jet applying the test condition for the research of gasturbine engine injection cooling technique. The mass averaged enthalpy value determined by the sonic throat method is 5.5MJ/kg. The core enthalpy value determined by the heat transfer rate method is 14.3MJ/kg. Based on result of experiment, the ratio of the core to mass averaged enthalpies is 2.6.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.88-88
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• 2003

로켓 엔진 시스템에는 가압가스로 추진제를 엔진으로 공급하는 가압 시스템과 터보펌프를 이용해 엔진으로 고압의 추진제를 공급하는 터보펌프 시스템으로 나눌 수 있으며 터보펌프 시스템은 다시 Gas Generator를 이용하는 개방형 엔진과 Prebumer를 이용한 폐쇄형 엔진인 다단 엔진으로 구분할 수 있다. 로켓의 엔진 시스템은 Turbine, Turbopump, Gas Generator, Thrust Chamber, Tube, Valve, Propellant Tank 등 각 구성품 간에 서로 상호간섭이 매우 심한 공정이다 로켓 엔진 시스템은 이와 같은 상호간섭에 의해 추력 제어 및 혼합비 제어, 추진제 소진 제어 적용 시 정확하고 강인한 제어를 수행하여야 한다. 이를 위해 정확한 동특성 모델을 구축하는 것이 중요하며 모델을 통해 적절한 제어 시스템을 선택하여야 한다. 그러나 현재 국내에는 이에 대한 연구가 미미하며 해외의 경우 로켓은 특수 분야에 속함으로 공개되어 있지 않다. 로켓에 대한 개발 연구에 있어서는 위와 같은 작업이 선행되어야 하며 이에 대한 선행 연구로 한국항공우주연구원에서 Gas Generator를 이용한 개방형 터보펌프 엔진 시스템에 대한 연구를 진행하고 있다. 본 논문에서는 Gas Generator를 이용한 개방형 터보펌프 엔진시스템에 대한 동특성 모델을 구성하였다. 배관부, 터빈, 펌프, 밸브, Gas Generator, 재생냉각, 추력연소실 등 엔진 시스템을 구성하는 구성품에 대한 동특성 모델을 구성하였으며 이를 matlab의 simulink를 통해 각 구성품을 연결하여 최종 엔진시스템의 동특성 모델을 구성하였다. 구성된 동특성 모델을 통해 각종 변화(추진제 밀도 변화, 추력 변화, 혼합비 변화 등)에 대한 엔진 시스템 변화를 예측하여 정확한 엔진 시스템에 대한 이해를 넓혔으며 추력 제어 및 혼합비, 추진제 소진 제어를 최적으로 할 수 있는 제어 시스템 구축을 위한 기초 자료로 이용할 수 있을 것이다.