• Transactions of the Korean Society of Mechanical Engineers
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• v.12 no.1
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• pp.81-94
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• 1988

A series of experiments was performed in this study to investigate the boiling heat flux between an impinging water jet and a hot surface. Test variables were surface roughness, jet velocity, saturation temperature excess of surface, nozzle diameter and the gap distance between nozzle plate and the hot surface. In order to make the impinged cooling water a forced flow streaming a long the hot surface immediately after the initial impingement, the flat nozzle tip was extended to a circular flat plate having the same diameter as the hot surface. Utilizing the dimensionless parameter study on continuity, momentum and energy equations, 5 groups of variables involved in the nucleate boiling heat transfer were derived so that it is possible to estimate the increased heat flux by impinging water jet in a similar experimental work. For the case of saturated water being impinging onto a high temperature surface, an applicable correlation among dimensionless parameters describing the heat flux was found to be as follow.

• The Transactions of the Korean Institute of Electrical Engineers P
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• v.63 no.4
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• pp.283-289
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• 2014

A Fresnel lens is an optical component which can be used as a cost-effective, lightweight alternative to conventional continuous surface optics. Fresnel lens solar concentrators continue to fulfill a market requirement as a system component in high volume cost effective Concentrating Photovoltaic (CPV) electricity generation. The basic principles of the fresnel lens are reviewed and some practical examples are described. To investigate the performance space of the Fresnel lens, a fast simulation method which is a hybrid between raytracing and analytical computation is employed to generate a cache of simulation data. Injection molders are warming up to the idea of cycling their tool surface temperature during the molding cycle rather than keeping it constant. Heat and cool process are now also finding that raising the mold wall temperature above the resin's glass-transition or crystalline melting temperature during the filling stage and product performance in applications from automotive to packaging to optics. This paper deals with the suitability of Fresnel lenses of imaging and non-imaging designs for solar energy concentration. The concentration fresnel lens confirmed machinability and optical transmittance and roughness measure through manufactured the prototype.

• Corrosion Science and Technology
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• v.10 no.5
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• pp.167-174
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• 2011

Due to commercialization of nuclear power, most countries have taken interest in decontamination process of nuclear power plant and tried to develop a optimum process. Because open literature of the decontamination process are rare, it is hard to obtain skills on decontamination of foreign country and it is necessarily to develop proper chemical decontamination process system in Korea. In this study, applicable possibility in chemical decontamination for reactor coolant pump (RCP) was investigated for the various stainless steels. The stainless steel (STS) 304 showed the best electrochemical properties for corrosion resistance and the lowest weight loss ratio in chemical decontamination process with immersion type than other materials. However, the pitting corrosion was generated in both STS 415 and STS 431 with the increasing numbers of cycle. The intergranular corrosion in STS 431 was sporadically observed. The sizes of their pitting corrosion also increased with increasing cycle numbers.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.26-26
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• 1998

우주항공 산업에 대한 관심 증가에 따라 지상에서 많은 연소시험을 시행하고 있으나, 소음 발생문제에 부딪혀 어려움을 겪고 있는 실정이다. 따라서 초보적 단계이기는 하나, 액체로켓 엔진의 추력 손실을 최소화시키고 최대한 제트 소음을 크게 줄일 수 있는 소음기를 연구, 개발하고 있다. 본 연구에서는 제트소음에 대한 기초연구를 수행하여 물분사형 소음기를 설계 및 제작하였고, 물분사량과 소음기의 기하학적형상이 소음 특성에 미치는 영향을 연구하였다. 본 실험범위에서 연구의 결과는 다음과 같다. 1. 동일한 물 분사량 조건에서, 소음기 길이가 노즐출구 직경의 10배 모델 보다 30배 모델이 9dbl 정도 감음효과를 보였다. 2. 불 분사량이 증가함에 따라 소음레벨은 감소하였고, 30배 모델의 경우 불분사량이 배기가스의 10-12배 조건에서는 소음레벨을 91dbl까지 줄일 수 있었다. 3. 상기조건(소음레벨 91dbl)에 확장관을 부착함으로써, 소음레벨을 약 86dbl까지 줄일 수 있었다. 4. 본 형태의 물분사방식을 채택할 경우 고온배기가스로 인한 소음기의 파손을 방지하기 위해서 반드시 막냉각장치의 설치가 요구된다.

• Journal of the Korean Vacuum Society
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• v.18 no.1
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• pp.44-48
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• 2009

The effect of temperature gradient between the substrate and ambient gas on the structural characteristics of GaN nanorods grown on r-plane sapphire substrates by hydride vapor phase epitaxy was investigated. The density, diameter, and length strongly depended on the tempearture gradient. In addition, the cross-sectional shape of the nanorrods at the end of growth was found to be more dependedent on the temperature of a substrate itself than the temperature gradient.

• Proceedings of the Korean Society for Agricultural Machinery Conference
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• 2002.02a
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• pp.223-229
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• 2002

패드엔팬을 이용하여 물 공급량, 팬 회전속도의 변화에 따른 온실 냉방효과 시험한 결과를 요약하면 다음과 같다. 가. 패드에 흐르는 물 공급량별로 일중 11:00-16:00경에 물 공급량이 분당 60$\ell$이상 공급하면 8.0~9.5$^{\circ}C$의 온도차를 낼 수 있으며, 팬을 1170rpm으로 회전시킬 경우 6.0~9.$0^{\circ}C$의 온도차를 낼 수 있었다. 나. 온실과 팬출구 공기의 온도차는 일중 14:30~16:00 경에 60$\ell$이상의 물을 패드에 공급하는 경우 6.0~7.8$^{\circ}C$ 온도 강하 효과가 있고 팬을 1170rpm으로 회전시킬 경우에는 외기온 28$^{\circ}C$일 때 3$0^{\circ}C$이하로 온도를 강하시킬 수 있었다. 다. 패드에 흘리는 물의량을 60 $\ell$/min 이상을 공급하여 주면 30분당 20~28$\ell$의 물을 증발시킬 수 있다. 배출팬 회전속도가 1170rpm일 경우에 30분당 20~30$\ell$의 물을 증발시키는 것으로 나타났다. 라. 본시험에 사용된 패드엔팬의 흡.배기의 엔탈피변화는 8:30이전에는 흡기가 배기보다 온도가 낮아 엔탈피가 양(+)의 값을 나타났고, 8:30 이후에는 흡기가 배기 보다 온도가 높아 -2.0~-4.OkJ/kg의 엔탈피 차만큼 냉각효과가 있었으며, 냉방효율을 65~80% 수준으로 나타났다. 마. 본시험결과로 패드엔팬의 냉기 공급방식만 개선된다면 이동식인 박스형 패드엔팬도 냉방장치로 사용 가능할 것으로 판단된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.11
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• pp.1140-1147
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• 2009

Flow analyses have been performed to investigate the uniformity of propellant flow through the fuel and oxidizer manifolds of a full-scaled gas generator for a pump-fed liquid rocket engines. Injectors were simulated as porous medium layers having equivalent pressure drops. The uniformity of propellants has been analyzed for 3 fuel rings and 3 injector head configurations. The mixture ratio distribution at the exit of injectors has been estimated from the mass flow rates of fuel and oxidizer. The best configuration of fuel ring and injection head was selected through these flow analyses.

• Proceedings of the KIEE Conference
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• 2005.07b
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• pp.1252-1254
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• 2005

High Tc superconducting(HTS) model coil was prepared. Current-voltage(I-V) characteristic curves of model coil, sub-coils and joints were investigated at 77K and other some temperatures. Cooling system for characteristics measurement was made by using G-M cryocooler. At 77K, quench current(Iq) of model coil was 43.9A and the lowest Iq of sub-coils was 38.8A. At 55K, sub coil SP #06 was 106A. So, 100A was chosen as the operating current at 55K with margin. Joule heat of model coil was 0.65W at 100A, operating current and 58K. Joint resistances between sub-coils were about $70n{\Omega}$ at 77K and about $30n{\Omega}$ at 55K.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.12 no.11
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• pp.5188-5193
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• 2011

This research is for temperature control of insulating oil inside the transformer. After I designed and manufactured various systems using Peltier element, which was thermal element, and Heat pipe, which was a cooling system, without electric power. The optimum system could be made by applying them to the temperature control for the insulating oil. I could verify that the combination type of Heat pipe 100 W+ Peltier 100W has a more outstanding capacity than pure Heat pipe 300 W within 60 degrees Celsius through experiments. Through this, I verify that the method of a proper design is prominent, and make an attempt at contribution to power saving effect and more effective control of Distributing board by using this combination type.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.454-456
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• 2012

Conceptual design results of a thrust chamber for a 7 tonf-class liquid rocket engine of KSLV-II 3rd stage were described. The engine system for KSLV-II 3rd stage is pump-fed system, the thrust chamber has vacuum thrust of 6.9 tonf, vacuum specific impulse of 336.9 sec, chamber pressure of 70 bar, nozzle expansion ratio of 94.5, total propellant mass flow rate of 20.5 kg/s, mixture ratio(O/F) of 2.45. The thrust chamber consists of mixing head with 90 coaxial swirl injectors and regeneratively combustion chamber cooled by kerosene.