• Applied Chemistry for Engineering
• /
• v.29 no.5
• /
• pp.594-603
• /
• 2018

The effects of operating conditions such as benzene concentration, nitrogen flow rate, steam flow rate, and bed temperature on TSA process were experimentally investigated as a potential VOC removal technology using two kinds of beds packed with activated carbon and zeolite 13X. The TSA cycle studied was composed of the adsorption step, steam desorption step, and drying and cooling step. At 2% benzene concentration, the total adsorption amounts of zeolite 13X and activated carbon were 4.44 g and 3.65 g, respectively. Since the zeolite 13X has a larger packing density than that of the activated carbon, the larger benzene amount could be adsorbed in a single cycle. Increasing the water vapor flow rate to 75 g/hr at 2% benzene concentration reduced the desorption time from 1 hr to a maximum of 33 min. If the desorption time is shortened, the drying and cooling step period can be relatively increased. Accordingly, the steam removal and bed cooling could be sufficiently performed. The desorption amounts increased with the increase of the bed temperature. However, the energy consumption increased while the desorption amount was almost constant above $150^{\circ}C$. In the continuous cycle process, when the amount of remained benzene at the completion of the regeneration step increased, it might cause a decrease in the working capacity of the adsorbent. The continuous cycle process experiment for zeolite 13X showed that the amount of remained benzene at the end of regeneration step maintained a constant value after the fourth cycle.

• Journal of Aerospace System Engineering
• /
• v.14 no.5
• /
• pp.73-82
• /
• 2020

Recently, there has been an increase in additive manufacturing for the fabrication of liquid rocket engines. This technology can innovate conventional fabrication methods to reduce the lead time and manufacturing cost and can enhance the performances such as weight reduction. In this study, a literature survey is presented that includes types, advantages, disadvantages, and foreign government-based projects of the technology related to liquid rocket engine manufacturing. The present survey focuses on the technology that has been applied to various components such as turbopumps and valves while much larger efforts are made for combustion chambers with regenerative cooling channels and diverging nozzles, as the advantages of the technology are maximized for the applications.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
• /
• 2008.11a
• /
• pp.334-345
• /
• 2008

컴퓨터의 발달과 더불어 현대사회는 기록하고 보존해야할 정보의 양이 점점 방대해 지고 있다. 그로 인해 자기기록매체처럼 정보를 사용자의 편의에 따라 반복적으로 기록하고 재생할 수 있는 광기록매체에 대한 관심이 증가되고 있다. $Ge_2Sb_2Te_5$(GST)는 기존의 CD-RW나 Floppy Disk(FD)를 대체할 차세대 기록매체로 주목받고 있다. 따라서 본 연구에서는 비정질상과 결정상으로 변하는 성질을 가지고 있는 GST롤 상변화 기록매체로서 이용하기 위해 굴절률을 평가하였다. 시료는 5N의 순도를 갖는 Ge, Sb, Te 물질을 준비하고 조성비에 맞추어서 석영관에 진공 봉입한 후 용융-냉각법으로 벌크를 제작하였고 열증착 방법으로 Si 및 유리 기판위에 1000nm 두께로 박막을 제작하였다. UV-Vis-IR spectrophotometer를 사용하여 반사도와 투과도를 측정하였고 측정한 스펙트럼을 이용하여 Swanepoel method로 굴절률을 계산하였다. 본 연구진이 자체 개발한 계산툴에 실험값을 대입하였고 실험에 의해 얻은 투과도와 계산툴에 의해 얻은 투과도 스펙트럼을 비교하였다.

• Journal of the Korean Solar Energy Society
• /
• v.30 no.5
• /
• pp.17-24
• /
• 2010

태양열 제습냉방은 액체흡수제를 이용한 냉각효과로 기존의 전기에너지를 가능케 하는 해결책중 하나이다. 따라서 태양열을 거의 활용하지 않는 여름에 가열온수를 열원으로 활용하여 쾌적조건을 구현하는 본 연구의 대상인 태양열냉방시스템은 제습기와 재생기로 크게 이루어져 있다. 본 논문은 제습기의 유량 변화에 따른 열전달 및 물질전달의 변화를 실험과 이론적 해석으로 규명하고 있는데, 흐름의 양상은 병렬형과 대향류형을 대상으로 하고 있다. 실험결과와 이론해석이 비교적 잘 일치하였으며, 대향류형이 병렬형보다도 물질전달 면에서 유리하게 나타났으며, 입 출구의 엔탈피 차이에서도 크서 열전달에서도 우수한 것으로 나타났다. 또한 그 차이를 본 논문에서는 나타내었으며, 일정한 높이나 길이 이상에서는 항상 일정함을 알 수 있었다. 따라서 본 논문의 결과들은 제습기의 유동흐름을 통한 태양열냉방시스템 중 제습기의 설계 및 성능 향상에 도움을 줄 것이다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.8 no.4
• /
• pp.102-108
• /
• 2004

A layout of regenerative liquid rocket engine using turbo pump has been designed for development of high performance liquid rocket engine. each components of engine system was placed by considering assembly and characteristic. first stage engine system is controled by one plane of axis gimballing and composed of four engine assembly to cluster with launch vehicle. second stage engine system is controled by two plane of axis gimballing and composed of one engine assembly. assembly and disassembly Processes and required program have been developed. various shape of instruments were also developed for carrying out assembly and disassembly process efficiently.

• The Journal of the Korea institute of electronic communication sciences
• /
• v.10 no.2
• /
• pp.261-266
• /
• 2015

Power system for renewable energy is composed of module, transform DC power into AC power inverter, control power flow and device for a charge of the grid-connected. Power system for renewable energy produce the most DC power, when this system is much insolation in summer and daytime. But if the certain temperature rises above, the essential grid-connected power inverter is take a nose dive. There, in this paper, we propose an improved reduction of heating system. In addition, selection of the most serious heat region and through analysis of temperature characteristics according to location and distance derive the optimal model.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.37 no.11
• /
• pp.1140-1147
• /
• 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 Korean Society of Propulsion Engineers Conference
• /
• 2004.10a
• /
• pp.162-165
• /
• 2004

A layout of regenerative liquid rocket engine using turbo pump has been designed for development of high performance liquid rocket engine. each components of engine system was placed by considering assembly and characteristic. first stage engine system is controled by one plane of axis gimballing and composed of four engine assembly to cluster with launch vehicle. second stage engine system is controled by two plane of axis gimballing and composed of one engine assembly. assembly and disassembly processes and required program have been developed. various shape of instruments were also developed for carrying out assembly and disassembly process efficiently

• Journal of ILASS-Korea
• /
• v.27 no.2
• /
• pp.66-76
• /
• 2022

This study presents a prediction methodology of transport properties using the methane-based TRAPP (m-TRAPP) method in a wide range of temperature and pressure conditions including both subcritical and supercritical regions, in order to obtain thermo-physical properties for hydrocarbon aviation fuels and their products resulting from endothermic reactions. The viscosity and thermal conductivity are predicted in the temperature range from 300 to 1000 K and the pressure from 0.1 to 5.0 MPa, which includes all of the liquid, gas, and the supercitical regions of representative hydrocarbon fuels. The predicted values are compared with those data obtained from the NIST database. It was demonstrated that the m-TRAPP method can give reasonable predictions of both viscosity and thermal conductivity in the wide range of temperature and pressure conditions studied in this paper. However, there still exists large discrepancy between the current data and established values by NIST, especially for the liquid phase. Compared to the thermal conductivity predictions, the calculated viscosities are in better agreement with the NIST database. In order to consider a wide range of conditions, it is suggested to select an appropriate method through further comparison with another improved prediction methodologies of transport properties.

• Journal of ILASS-Korea
• /
• v.28 no.2
• /
• pp.89-96
• /
• 2023

This study presents a numerical simulation investigating hydrodynamic characteristics of high-temperature hydrocarbon aviation fuel injected through a plain orifice injector. The analysis encompassed the temperature range up to the critical point, and the obtained results were compared with prior experimental observations. The analysis unveiled that the injector's exit pressure remains equivalent to the ambient pressure when the fuel injection temperature is below the boiling point. However, when the fuel temperature surpasses the boiling point, the exit pressure of the injector transitions to the saturated vapor pressure corresponding to the fuel injection temperature. Consequently, the exit pressure of the injector increases in tandem with the rapid increase of the saturation vapor pressure due to escalating fuel temperatures. This rise in the exit pressure necessitates a proportional increase in fuel injection pressure to ensure a fixed fuel mass flow rate. Furthermore, the investigation revealed that the discharge coefficient obtained by applying the exit pressure instead of the ambient pressure did exhibit no decrease, but rather was maintained at a nearly constant value, comparable to its level below the boiling point.