• Journal of the Korea Society of Computer and Information
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• v.28 no.1
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• pp.121-127
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• 2023

In this study, the design conditions and CFD analysis results are compared and reviewed in SCR that can optimally reduce nitrogen compounds. To this end, it was analyzed and compared using CFD to see if the design criteria were satisfied for the shell and tube areas of the boiler. In the SCR system, the analysis area is the gas/air heat exchanger on the shell side, and eight tubes of the gas/air heat exchanger on the tube side. Through CFD analysis, the gas velocity distribution on the primary catalyst side of the SCR system was designed to be 2.4%, and the NH3/NOx molar ratio distribution was 3.7%, which satisfied the design criteria. In addition, the uniformity of the temperature distribution was confirmed and the required condition of 260℃ or higher was satisfied. The angle of the gas entering the catalyst met the design conditions at 2.9 degrees, and the pressure loss that occurred also satisfied the design requirements. Through this CFD analysis, it was confirmed that it was designed and operated by satisfying the design conditions required for each area.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.5
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• pp.483-489
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• 2009

A CFD code was developed to investigate the inception of cavitation around impeller blades of centrifugal fuel pump using two dimensional cascade modeling. With the verification test for numerical validity of the developed code, the prediction of the onset of cavitation was made for the configuration of a newly designed KHP fuel pump. The calculation results show impeller design was free of cavitation if the pump operates within the operational temperature and rotational speed range. However, the cavitation would be relatively easy to occur at off design region of fuel pump where the rotational speed is higher than design limit. Specially, the onset of cavitation is sensitively dependent on the increase in fuel temperature while the decrease in temperature will reduce the possibility of cavitation inception in the pump.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.6
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• pp.9-16
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• 2010

The SFRJ(Solid Fuel Ram-Jet) propulsion is attractive for projectiles because of the combination of high propulsive performance and low system complexity more than conventional projectiles. The Objective of this research was to characterize the inlet aerodynamic characteristics (center-body & pitot type) in SFRJ. Diffuser static pressure & combustion chamber pressure was tested and the AoA was changed $0^{\circ}$ and $4^{\circ}$ at Mach number of 3.0 for performance estimate. The performance study of inlet was carried out with the Schlieren system and Supersonic cold-flow system. Under mach 3.0, the center-body showed twice higher total pressure recovering ratio than the pitot type. A Computational fluid dynamic solution is applied internal flow of inlet and the solutions are compared with experimental results.

• Journal of Korean Society of Environmental Engineers
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• v.22 no.10
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• pp.1817-1824
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• 2000

This study is carried out to investigate the discharge characteristics of PCDD/Fs from municipal solid waste(MSW) incinerator, According to the results measured at several air pollution control devices(APCDs), the largest amount of polychlorinated dibenzo-p-dioxins/dibenzofurans(PCDD/Fs) are found at selective catalytic reduction (SCR) inlet. Therefore, it concludes that the electrostatic precipitator(EP) provides the appropriate condition for the formation of PCDD/Fs. The concentration of PCDD/Fs shows a large difference with the season. The concentration of PCDD/Fs in winter is higher than that of autumn, which suggests that the formation of PCDD/Fs is affected by the MSW components and the operation condition of municipal solid waste incinerator(MSWI).

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.6
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• pp.30-37
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• 2008

Many theoretical and experimental studies have been conducted to investigate elements of swirl injector hydrodynamics, such as variations in liquid film thickness or air core diameter. From these studies, some theoretical relationships have been established through an approximate analytical solution of flow hydrodynamics in a swirl nozzle. However, experimental studies on elements such as the stability of internal flow have not produced conclusive results. In this study, the stability of the internal flow under tangential entry conditions was examined by visualizing the formation of the air core in the swirl chamber and measuring the liquid film thickness in the orifice.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1992.04a
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• pp.115-119
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• 1992

산업의 발전과 더불어 새로운 재료의 개발에 대한 요구가 날로 증가하고 있으며 이와 같은 요구에 부응하기위하여 각종의 신소재가 개발되고있다. 이들 신소재 중에서 섬유강화 복합재료는 높은 비탄성과 비강도특성 때문에 구조물의 경량화가 요구되는 우주선, 항공기 등에 주로 이용 되어 왔으며 최근에는 복합재료의 가격이 저렴해 지면서 이 재료의 높은 비탄성과 감쇠특성을 이용하고자 스포츠용품 및 기계 부품에도 섬유강화 복합재료의 이용이 증가 되고 있다. 항공기나 고속회전체의 부품을 복합재료로 제작하였을 경우 복합재료를 다른 금속이나 다른 복합재료부품에 접합(joining)시켜야 하는데 이 때문에구조물의 효율은 Joint에서 주로 죄우된다. Joint를 제작하기 위해서는 복합재료의 표면을 가공한 수 Adhesive를 이용하거나 Bolt로 체결하기 위해 구멍 뚫기 작업이 필요하여 드릴링을 하였을때 이 재료가 매우 연마성이 강하여 심한 공구마멸을 일으키며, 드릴의 입구와 출구쪽에서 각 ply들의 박리 현상이 발생하고, 드릴가공된 벽면으로부터 섬유 또는 레진의 탈락현상등이 발생하는 결점을 가지고 있다. 따라서 본 연구에서는 이러한 결점을 최소화하여 고정밀도의 높은 생산성을 얻기위한 가공기술에 대한 자료를 만들고 최적 절삭조건 및 복합재료가공용 드릴의 설계를 위한 지침을 제시하고자 고속도강 표준드릴을 사용하여 유리섬유 에폭시 복합재료및 탄소섬유 에폭시 복합재료의 드릴링 실험에서 절삭조건이 가공면 생성, 공구마멸, 절삭력에 미치는 영향에 대하여 조사하였다.

• Journal of the Korean Applied Science and Technology
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• v.37 no.5
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• pp.1402-1408
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• 2020

In order to save energy, a lot of research has been conducted to develop a high-efficiency heat pump. Research to reduce or eliminate the occurrence of frost in the outdoor unit coil is also being conducted at the same time. A constant temperature chamber was constructed that allows experimentation under the same conditions as in the natural state so that frost does not occur in the outdoor unit of the heat pump regardless of the season. In order to verify the validity of the experimental apparatus, a simulation was conducted by dividing the straight length of the duct in front of the outdoor unit in the constant temperature chamber, which is the experimental apparatus, into three conditions. As a result, it was found that a straight space must be secured 10 times the diameter of the duct.

• Proceedings of the Korean Vacuum Society Conference
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• 2010.08a
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• pp.12-12
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• 2010

첨단 공정이 필요한 반도체와 LCD, PDP, LED 등의 디스플레이 및 IT 부품을 제조하는데 필요한 장비의 고성능화와 작업환경의 고청정화에 따른 초고진공펌프의 수요 확대와 앞으로 전개될 한-미 FTA에 따른 시장 확대로 인해 크라이오펌프의 국산화가 시급한 실정이다. 고성능 크라이오펌프를 만들기 위해서는 냉각판을 극저온으로 냉각하기 위한 극저온 냉동기 개발도 중요하지만 냉각판(cryoarray)에 최대한 많은 분자를 포획시키는 것 또한 최우선적으로 고려되어야 할 사항 중 하나이다. 이에 본 논문은 크라이오펌프용 냉각판의 분자포획능력에 대하여 연구하였다. 해석에 이용한 냉각판은 현재 상용화된 모델들 중 원형 중앙판에 $45^{\circ}$ 하향 skirt가 달린 형태이며 8장의 냉각판이 일정한 간격을 두고 아래쪽으로 적층되어 있다. 냉각판의 분자포획능력의 해석은 형상계 수법(view factor method)을 이용해 수행하였다. 형상계수법은 크라이오펌프를 n개의 미소면적으로 구성된 밀폐된 공간으로 가정하고 각 미소면적요소의 온도와 흡착계수, 표면조건 그리고 분자유속이 일정하다는 조건을 이용해 분자유속에 관해 n개의 대수연립방정식을 얻고 이 대수연립방정식을 풀어 냉각판의 분자포획능력을 구한다. 해석에 이용한 냉각판의 기체분자포획능력이 구속된 형상에서 얼마나 우수한 가를 알아보기 위해 중앙판의 직경, 입구와 냉각판 사이의 거리, 그리고 각 냉각판 사이의 거리를 변화시켜가며 해석을 수행하고 그 결과를 비교, 분석하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.1
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• pp.61-66
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• 2005

A theoretical analysis is developed for an annular-injection-type supersonic ejector having a second-throat downstream the ejector under the assumption that the Fabri choking is placed in mixing chamber. Non mixing theory is applied to formulate secondary flow pressure in the region between inlet of the mixing chamber and Fabri choking. To describe the shock standing at the inlet of the mixing chamber, two dimensional oblique shock relations are used and it is assumed that the shock affects only primary flow at Fabri choking plane. Physical constraint, which is that primary flow pressure and secondary flow pressure are same at Fabri choking plane, is added. In conclusion, it agrees well with experiments in case of small contracting angle of mixing chamber, under 4degrees.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.37-46
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• 2006

The outside environment is very severe while aircraft is cruising. Especially small particle of icing in cold air condition can have negative influence on aircraft performance. If ice particle is attached to leading edge of wing, it can change wing configuration and decrease flight quality. If icing particle is attached to inlet of engine, it can damage compressor blade and have negative influence to aircraft safety. We make icing simulation device with liquid air system for analyzing about variation of engine performance due to incoming of icing to engine.