• Transactions of the Korean Society of Mechanical Engineers B
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• v.34 no.2
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• pp.121-127
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• 2010

The in-furnace desulfurization technique is applied to the $O_2/CO_2$ combustion system for the carbon capture and storage (CCS) process because this combustion system does not need an additional chamber for the desulfurization. $CaCO_3$ sorbent particles, which have a wide range in size from a few nanometers to several tens of micrometers, are used for this process. In this study, an experimental system which can simulate the $O_2/CO_2$ combustion system was developed. $CaCO_3$ sorbent particles were exposed to the high temperature reactor at $1200^{\circ}C$ with various residence times (0.33-1.46 s) in air and $CO_2$ atmospheric conditions, respectively. The sorbent particles were then sampled at the inlet and outlet of the reactor and analyzed qualitatively/quantitatively using SMPS, XRD, TGA, and SEM. The results showed that the residence time and atmospheric condition in a high temperature reactor can affect the characteristics of the $CaCO_3$ sorbent particles used in the in-furnace desulfurization technique, such as the calcination rate and reaction mechanism.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.45-49
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• 2003

A Bake-Out test for STSAT-1 FM(Flight Model) was performed in a Bake-Out Chamber at SITC(Satellite Integration & Test Center) in KARI(Korea Aerospace Research Institute). The purpose of this test is to measure and analyze the outgassing rate to affect the optical equipment(FIMS) and to eliminate contaminants through the high temperature bake-out. This Bake-Out test is composed of three parts which are honeycomb panels & harnesses(Batch 1), an assembled satellite(Batch 2), and a disassembled satellite(Batch 3). For each test, quantitative and qualitative measurements and analysis were performed using TQCM(Thermoelectric Quartz Crystal Microbalance) and RGA(Residual Gas Analyzer.)

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.116-122
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• 2010

It is necessary to be careful about contamination control to minimize the accumulation of the contamination material on satellite surface during the I&T phase. In the space environment which characterized by high vacuum, high and very low temperature, contamination material causes satellite to lose its own performance. Especially, contamination material can accumulate on critical surfaces such as lenses, mirrors, and sensors. KARI(Korea Aerospace Research Institute) conducts the clean room to control and minimize the contamination effect. This paper introduces the principle of contamination and the method of measure and analysis for the contamination.

• Journal of computational fluids engineering
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• v.7 no.3
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• pp.9-16
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• 2002

Most of modem aerospace gas turbines must be operated at a gas temperature which is several hundreds of degrees higher than the melting temperatures of the materials used in their construction. Complicated cooling schemes need to be employed in the combustor walls and in the high pressure turbine stages. Internal passages are cast or machined into the hot sections of aero-gas turbine engines and air from the compressor is used for cooling. In many cases, the cooling system is engineered to utilize jets of high velocity air, which impinge on the internal surfaces of the components. They are categorized as 'Impinging Cooling Method' and 'Vortex Cooling Method'. Specially, research of new cooling system(Vortex Cooling Method) that overcomes inefficiency of film cooling and limitation of space. The focus of new cooling system that improves greatly cooling efficiency using less amount of cooling air on surface heat transfer elevation. Therefore, in this study, a numerical analysis has been peformed for characteristics of flow and heat transfer in the swirl chamber and compared with the flow measurements by LDV. Especially, for understanding high heat transfer efficiency in the vicinity of wall, we considered flow structure, vortex mechanism and heat transfer characteristics with variation of the Reynolds number.

• Proceedings of the Korean Vacuum Society Conference
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• 2012.02a
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• pp.524-524
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• 2012

Thermal Barrier Coating (TBC)은 미사일, 로켓발사체와 같이 고온에 노출되는 장비를 열로부터 보호하기 위한 코팅이다. 일반적인 Thermal Barrier Coating (TBC)은 모재와 코팅층간의 낮은 접합력과 높은 열충격으로 인한 박리가 많이 나타난다. 그래서 접합력을 높이고, 열충격을 줄이기 위해 모재와 코팅층 사이에 본드코팅층을 만든 Duplex - Thermal Barrier Coating (Duplex-TBC)이 개발되었다. 그러나 Duplex - Thermal Barrier Coating (Duplex-TBC)은 금속재료인 본드코팅층과 세라믹재료인 탑코팅층 사이에서 박리가 많이 발생한다. 이러한 문제점을 해결하기 위해 두 가지 분말을 동시에 코팅하여 본드코팅과 탑코팅의 경계가 없는 Functional Gradient Material - Thermal Barrier Coating (FGM-TBC)의 연구가 필요하다. 본 연구에서는 Functional Gradient Material - Thermal Barrier Coating (FGM-TBC)의 열충격 특성에 미치는 진공 플라즈마 용사 조건의 영향을 조사하였다. Functional Gradient Material - Thermal Barrier Coating (FGM-TBC)는 진공 플라즈마 용사장치를 사용하여 Cu-Cr 합금위에 코팅하였다. 거리, Carrier gas flow, 그리고 챔버 내부의 압력을 달리하여 제조하였다. 사용한 분말은 본드코팅용으로 Amdry 962와 내열 세라믹코팅을 위해 204NS를 사용하였고, 각각 분말 공급조건을 조절하여 두 분말의 비율을 달리하였다. 제조한 Functional Gradient Material - Thermal Barrier Coating (FGM-TBC) 코팅은 전기로에서 50분간 가열한 후, 수조에서 10분간 냉각하는 열충격 실험을 통해 열차폐 성능을 평가 하였다. 이러한 과정에서 진공 플라즈마 용사 조건 및 FGM 조성과 비율이 내열충격 특성에 미치는 영향을 미세조직학적 관점에서 고찰하였다.

• Proceedings of the Korea Crystallographic Association Conference
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• 2003.05a
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• pp.12-12
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• 2003

초전도 선재로의 응용을 위하여 Pulsed laser deposition(PLD)법으로 고온 초전도 체 YBa₂Cu₃O/sub 7-δ/(YBCO) coated conductor를 제조하였다. coated conductor는 금속기판/완충층/초전도층의 구조를 이루고 있는데 완충층은 금속 기판의 집합조직을 초전도층까지 전달하는 역할과 금속기판의 금속이 초전도층으로 확산되어 초전도층의 전기적 특성을 열화시키는 것을 막아주는 확산장벽으로의 역할 등을 수행한다. 완충층의 박막 성장이 제대로 이루어지지 않으면 우수한 초전도 특성을 가지는 초전도층을 얻을 수 없다. 완충층은 금속기판과의 lattice match, thermal match등이 요구되고, 화학적으로 금속기판 및 초전도층과 반응하지 않아야 하며, 긍속기판의 산화없이 epitaxial하게 박막증착이 이루어질 수 있는 재료이어야 한다. 이러한 조건을 만족하는 YBCO, CeO₂, YSZ 등이 주로 사용되고 있다. 전기연구원에서 YBCO coated conductor 선재를 제조하기 위하여 사용하고 있는 다층 박막의 구조는 YBCO/CeO₂/YSZ/CeO₂/Ni(002)과 YBCO/CeO₂/YSZ/Y₂O₃/Ni(002)이며, 최적의 증착조건을 찾기 위하여 성장시 챔버의 산소분압, 완충층의 두께, 기판 온도 등을 변화시켰다. 증착된 완충층 및 초전도층의 집합 조직은 D8-Discover with GADDS(General Area Detector Diffraction System)로 XRD분석을 했고, 미세구조는 SEM으로 관찰하였으며 4단자법을 이용하여 초전도 특성을 측정하였다.

• 한국전산유체공학회:학술대회논문집
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• 2002.05a
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• pp.71-78
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• 2002

All modem, aerospace gas turbines must operate with hot stage gas temperature several hundreds of degrees hotter than the melting temperatures of the materials used in their construction. Complicated cooling schemes need to be employed in the combustor walls and In the high pressure turbine stages. Internal passages are cast or machined into the hot sections of aero-gas turbine engines and air from the compressor is used for cooling. In many cases, the cooling system is engineered to utilize jets of high velocity air, which impinge on the internal surfaces of the components. They are divided by Impinging cooling method and Vortex cooling method. Specially, Research of new cooling system(Vortex cooling method) that overcome inefficiency of film cooling and limitation of space. The focus of new cooling system that improve greatly cooling efficiency using quantity's cooling air which is less is set in surface heat transfer elevation. Therefore, In this study, the numerical analysis have been performed for characteristic of flow and thermal in the swirl chamber and compared with the flow field measurement by LDV. especially, for understanding of high heat transfer efficiency in vicinity of wall. we considered flow structure and mechanism of vortex and heat transfer characteristic in variation of Reynolds number.

• Proceedings of the Korean Vacuum Society Conference
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• 2010.02a
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• pp.78-78
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• 2010

그래핀(Graphene)은 탄소원자가 육각형 벌집(honeycomb)구조로 빼곡히 채워진 2차원의 단원자 층으로 역학적 강도와 우수한 화학적/열적 안정성 및 흥미로운 전기 전도 특성을 가지고 있다. 이러한 그래핀의 우수한 특성으로 인하여 현재 기초연구뿐만 아니라 응용연구 등 많은 연구들이 진행되고 있다. 일반적으로 그래핀의 우수한 물리적 특성들은 그래핀의 층수, 모서리(edge)구조, 결함(defect), 불순물 등에 의해 크게 좌우되는 것으로 알려져 있다. 따라서 그래핀의 구조 및 결함정도를 자유로이 제어하고 그에 따르는 특성 변화를 관찰하는 것은 기초연구의 측면에서 뿐만 아니라 향후 그래핀 응용에 있어서도 매우 중요하다고 할 수 있다. 본 연구에서는 그래핀의 내산화 특성을 연구하기 위하여, 그래핀을 열 및 플라즈마 산화 분위기에 노출시킨 후, Raman 분광법을 이용하여 광학적, 구조적 변화를 분석함으로써 그래핀의 내산화 특성에 대하여 조사하였다. 그래핀은 실리콘 웨이퍼에 전자빔증착법으로 니켈박막을 증착한 후 열화학증기증착법으로 합성하였으며, 메탄가스를 원료가스로 $900^{\circ}C$ 전후에서 합성하였다. 합성한 그래핀은 산화반응 시 기판의 영향을 제거하기 위하여 트렌치 구조의 기판 위에 전사(transfer)함으로써 공중에 떠있는 구조를 구현하였다. 열 산화의 경우, 합성한 그래핀을 대기분위기의 고온($500^{\circ}C$) 챔버에 넣고 처리시간에 따른 특성변화를 살펴보았다. 플라즈마 산화의 경우는 공기를 이용하여 직류플라즈마를 발생시킨 후 0.4 W의 낮은 플라즈마 파워를 이용하여 플라즈마 산화처리와 특성평가를 매회 반복하였다. 그래핀의 특성분석은 Raman분광기와 광학현미경, 원자힘현미경(AFM) 등을 이용하여 분석하였으며, 상기 결과들은 향후 산화환경에서의 그래핀 응용소자 개발에 유용할 것으로 예상된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.397-400
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• 2008

Traditional propellants which have a hypergolic characteristic have a high performance but also have disadvantages of toxicity and complex handling requirement. In order to replace these propellants, one of the alternatives is hydrogen peroxide which generates high temperature oxygen and water vapor after catalytic reaction. In this paper, autoignition characteristics of kerosene by decomposed hydrogen peroxide were investigated to perform fundamental research for designing a thruster using hydrogen peroxide and kerosene propellants. Contraction ratio, whether flame holder exists or not, and feeding pressure of propellants were selected as variables. From the experiments for different mixture ratio, we confirmed the ignition stability is strongly affected by a feeding pressure of propellants.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.39 no.6
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• pp.567-573
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• 2015

This paper aims to evaluate the variation in the mechanical properties of carbon/epoxy composites under in situ low- and high-temperature environments. In situ low- and high-temperature environments were simulated with temperature ranging from $-40^{\circ}C$ to $220^{\circ}C$ using an environmental chamber and furnace. The variation in the mechanical properties of the composites was measured for longitudinal and transverse tensile properties, in-plane shear properties and interlaminar shear strength. Under the low temperature of $-40^{\circ}C$, all mechanical properties increased moderately compared to the baseline properties measured at room temperature. The changes in the longitudinal tensile properties decreased moderately with increasing temperature. However, transverse tensile properties, in-plane shear properties and interlaminar shear strength each showed a significant drop due to the glass transition behavior of the matrix after $140^{\circ}C$. Notably, the tensile property value near $100^{\circ}C$ increased compared to baseline property value, which was an unusual occurrence. This behavior was a direct result of post-curing of the epoxy resin due to its exposure to high temperature.