• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1995.11a
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• pp.105-109
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• 1995

본 연구에서는 수치모사로 부터 단위 전지 양극가스내 질소 조성과 각 가스의 순환에 따른 단위전지내의 온도분포 및 성능변화를 구하였다. 양극가스내 질소의 영향은 냉각효과로 나타났고 순환비가 증가할수록 전지내의 온도와 전지의 성능은 감소하였다. 작동압력이 증가할수록 전지의 성능은 증가하였고, 기전력변화 대 압력의 상용대수변화의 직선의 기울기는 문헌상의 실험치와 유사하게 나타났다.

• The Journal of Natural Sciences
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• v.13 no.1
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• pp.15-23
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• 2003

본 연구에서는 코일의 온도를 액체질소 온도 정도의 저온으로 냉각시켜 핵자기공명 신호 및 영상의 신호대잡음비를 향상시키는데 그 목적을 두었다. 핵자기공명 신호의 신호대잡음비에 대한 이론적인 분석을 토대로 다양한 형태의 고주파코일을 제작했고, 저온의 표면고주파코일로 획득된 신호를 상온의 일반 구리코일로 획득된 신호와 비교하였다. 본 연구에서 제작된 저온코일의 경우, 상온코일에 비해서 신호대잡음비의 향상을 얻을 수 있었다. 이러한 신호대잡음비의 향상을 통하여 핵자기공명영상 시간을 단축할 수 있으며, 이를 통한 진단의 신뢰도 향상에 기여할 수 있을 것으로 사료된다.

• Journal of Advanced Marine Engineering and Technology
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• v.36 no.8
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• pp.1050-1060
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• 2012

As an approach to high-efficiency of SOFC system, SOFC/GT Hybrid system is effective. However, if the output size of the system belongs to the marine class of dozens MWs, the introduction of the cooling system of GT system, which is used as sub-system, makes its related devices complicated and also makes its control difficult. Accordingly, for the marine use, SOFC/GT (non-cooling)Hybrid system looks more suitable than SOFC/GT(cooling)Hybrid system. This study established the SOFC/GT (non-cooling)Hybrid system, and examined the operating temperature & current density of the stack for the system, pressure ratio of the gas turbine, the influence of TIT(Turbine Inlet Temperature) on system performance, etc. through the simulation process. Through this research process, this study was able to confirm that electrical efficiency rises in spite of the increase in the required power for the air compressor, and there exists a limited range of temperatures for operation in TIT.

• Current Industrial and Technological Trends in Aerospace
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• v.9 no.1
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• pp.139-149
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• 2011

The combustion chamber and nozzle of a liquid rocket engine need thermal protection against the high temperature combustion gas. The nozzle extension of a high-altitude engine also has to be compatible with high temperature environment and several kinds of cooling methods including gas film cooling, ablative cooling and radiative cooling are used. Especially for an upper-stage nozzle extension having a large expansion ratio, the weight impact on the launcher performance is crucial and it necessitated the development of light-weight refractory material. The present survey on the nozzle extension materials employed in the liquid rocket engines of USA, Russia and European Union has revealed a trend that the heavier metals like stainless steels and titanium alloys are being substituted with light weight carbon fiber or ceramic matrix composite materials.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.149-152
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• 2008

Effects of chamber configuration on combustion characteristic velocity of full-scale combustion chamber for 30-tonf-class liquid rocket engine were studied. The configurations of combustion chamber are ablative and channel cooling chamber (${\varepsilon}$=3.2) which have detachable mixing head, and single body regenerative cooling chamber which has nozzle expansion ratio of 3.5 and 12, respectively. The combustion chambers have chamber pressure of 53${\sim}$60 bar and propellant mass flow rate of 89 kg/s, and the injectors of all combustion chamber have recess number 1.0 and double-swirl characteristics. The hot firing test results at design point show that the combustion characteristic velocity of the regenerative cooling chamber which has nozzle expansion ratio of 12 is higher than that of other combustion chambers. The reasons for the above result are the increases of combustion pressure and enthalpy of kerosene which is heated due to cooling of the chamber wall before injection into the combustion field.

• Journal of Advanced Marine Engineering and Technology
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• v.38 no.9
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• pp.1027-1031
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• 2014

Free cooling system is used to reduce energy consumption of cooling system. Free cooling system is consisted of cooling group and dry-cooler in which heat exchange of chilled water and out air is conducted. Although this system has an excellent energy saving effect in place having cooling load regularly, data or material of design for free cooling system is lacked. In this study, characteristics analysis of free cooling system is conducted through software HYSYS with changing some facts. The main result is following as : Dry-cooler capacity is influenced by out air temperature, required chilled water temperature and LMTD(Logarithmic Mean Temperature Difference) of heat exchanger. As out air temperature is more low, dry-cooler capacity become increased. in addition, as required chilled water temperature is more high and LMTD is more low, the out air temperature range is widened for using dry-cooler. If out air temperature is below $0^{\circ}C$, antifreeze need to be used because freeze and burst can be occurred. In case of South Korea, antifreeze of 34% of ethylene glycol concentration is proper. When compressor load of R22, R134a and R407C is compared, considering environmental regulation and energy consumption, R134a is best working fluid.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.1459-1460
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• 2011

자성유체에 60Hz의 교류자기장을 인가할 때 발생되는 냉각효과를 해석하기 위해 유한요소법을 결합하였다. 열원으로는 전류가 코일에 흐를 때 생성되는 줄열과 닐운동과 브라운운동으로 야기되는 전력손실에 의한 발열이 있다. 교류자기장은 주파수가 낮기 때문에 줄열이 주요한 열원이 된다. 그러므로 코일에서 자성유체로 일어나는 열전달과 자연대류현상은 코일의 표면에서 일어난다. 자연대류현상을 해석하기 위해서는 자성유체의 부력밀도를 고려해야 한다. 부가적으로 자계의 세기와 온도에 관한 함수인 자화와 자기체적력밀도로 인해 자기대류현상과 같은 강제대류가 일어난다. 이러한 두 가지 대류현상으로 인해 교류자기장을 인가한 자성유체에서 냉각효과가 일어난다. 자기체적력밀도는 유한요소법으로 보간된 가상공극개념을 이용하여 켈빈전자기력밀도를 이끌어 낸 후 이를 수치적으로 이용하여 구하였다. 랑제방함수는 켈빈전자기력밀도와 전력손실을 계산하는데 필요한 비선형 자화율을 고려하기 위해 사용하였다.

• Proceedings of the Korean Nuclear Society Conference
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• 1998.05b
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• pp.324-329
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• 1998

본 연구는 주증기배관으로 사용되고 있는 SA106. Gr.C의 모재와 용접계에 대해서 파괴인성에 미치는 온도와 하중속도의 영향을 살펴보기 위해서 다양한 온도와 하중속도에서 J-R 시험 및 인장시험을 수행하였다. 두 재료 모두 동적변형시효의 영향을 받고 있는 온도영역에서 약 40% 정도의 파괴인성 감소가 관찰되었으며, 하중속도에 따른 파괴인성 감소영역은 serration과 인장강도 증가 영역의 하중속도 의존성과 일치하였다. 원자력발전소 운전온도에서 모재와 용접재 모두 하중선변위속도가 4.0mm/min 일 때 파괴인성치의 최저를 보였으며, 하중속도가 증가함에 따라 증가하여 동적하중속도(800, 40mm/min)일 때 최대를 보였다. 모재와 용접재를 비교하면 용접재에서 serration이 뚜렸했고, 보다 넓은 온도영역에서 관찰되었다. 또한 인장강도의 증가가 보다 고온에서 형성되었다. 이러한 특성은 용접재가 모재에 비해 냉각률이 크고 미세한 결정입으로 이루어져있으며, 망간의 함량이 높기 때문으로 판단된다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.25 no.8
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• pp.1131-1139
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• 2001

Experimental results are presented, which describe the effect of blowing ratio on film cooling from two rows of holes with opposite orientation angles. The inclination angle is fixed at 35°, and the orientation angles are set to be 45°for the downstream row, and -45°for the upstream row. The studied blowing ratios are 0.5, 1.0 and 2.0. The boundary layer temperature distributions are measured using thermocouple at two downstream locations. Detailed adiabatic film cooling effectiveness and heat transfer coefficient distributions are measured with TLC(Thermochromic Liquid Crystal). The adiabatic film cooling effectiveness and heat transfer coefficient distributions are discussed in connection with the injectant behaviors inferred from the boundary layer temperature distributions. Film cooling performance, represented by heat flux is evaluated from the adiabatic film cooling effectiveness and heat transfer coefficient data. The results show that the investigated geometry provides improved film cooling performance at the high blowing ratios of 1.0 and 2.0.

• Proceedings of the KSME Conference
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• 2000.04b
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• pp.113-118
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• 2000

Experimental results describing the effects of blowing ratio on film cooling from two rows of holes with opposite orientation angles are presented. The inclination angle was fixed at $35^{\circ}$ and the orientation angles were set to be $45^{\circ}$ for downstream row. and $-45^{\circ}$ for upsream row. The studied blowing ratios were 0.5, 1.0 and 2.0. The boundary layer temperature distributions were measured using thermocouple at two downstream loundary layer temperature distributions were measured using thermocouple at two downstream locations. Detailed adiabatic film cooling effectiveness and heat transfer coefficient distributions were measured with TLC(Thermochromic Liquid Crystal). The adiabatic film cooling effectiveness and heat transfer coefficient distributions are discussed in connection with the injectant behaviors inferred from the boundary layer temperature distributions. Film cooling performance, represented by heat flux was calculated with the adiabatic film cooling effectiveness and heat transfer coefficient data.