• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.12 no.9
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• pp.870-878
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• 2000

An experimental study and a modeling are peformed to investigate the pressure drop of combining junctions in two-phase flows. Experiments on tripod geometry used in a condenser or an evaporator, are conducted with inlet mass fluxes from 200 to$ 400 kg/m^2$s, and pipe diameters of 7 m and 9.52 m. The working fluid is R22. The result shows that the pressure drop increases as the quality does, but the effect of the increase of the pressure decreases when the diameter of a pipe increases. When the mass flux increases, the pressure drop linearly does. Furthermore, when the pipe diameter decreases, the pressure drop has a quadratic increase.

• Journal of Energy Engineering
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• v.9 no.3
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• pp.250-260
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• 2000

유동층 연소기술은 다양한 연료의 사용과 SOx와 같은 공해물질의 배출제어가 용이하여 환경규제에 대한 대처능력이 우수한 발전방식으로 널리 적용되고 있는 추세이다. 국내에서도 동해화력 1,2호기(200MWe급)가 유동층 연소방식을 도입하여 운전중에 있으며, 국내 무연탄을 연료로 사용하는 최대 규모의 순환 유동층 보일러라 할 수 있다. 본 논문에서는 IEA-CFBC 모델을 이용하여 개발된 동해화력 순환유동층 성능모사 시뮬레이션 틀을 이용하여 여러 가지 운전변수 변화에 따른 성능예측을 수행하였으며, 특히, 연소로의 성능향상을 위한 방안의 일환으로 사이클론 개조를 수행하고 그에 따른 성능모사를 고찰하였다. 본 성능평가 결과 연소로내 전체 차압을 증가시키는 운전을 지향하는 것이 연소로내 희박상의 온도분포를 낮추고, 탈황효율을 증가시켜 운전 안정화에 기여하는 것으로 나타났다. 또한, 본 시뮬레이션 틀을 이용한 운전변수 변화에 대한 성능예측 결과 동해화력 운전 실측치와 잘 일치하는 것으로 고찰되었다.

• Proceedings of the Korea Water Resources Association Conference
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• 2019.05a
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• pp.280-280
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• 2019

복잡한 구조의 인공어초는 그 형상에 따라 다양한 유동의 특성을 나타낸다. 이러한 유동장 분석은 여러 방면에서 다양한 실험적 연구가 수행되었으나, 현실적으로 좁은 측정영역 내에서 접촉식 계측장비의 설치가 불가하고 갇혀진 수로 내에서 발생하는 반사파랑의 영향으로 인하여 사실상 정량적인 결과도출이 어려운게 현실이다. 본 연구에서는 2차원 단면실험수로 내에 별도의 소파장치를 고안하여 단위 시간당 발생하는 반사율을 측정하고 그에 따른 인공어초 인근의 유동장의 양상을 검토하였다. 수리모형실험은 1/50의 실험축척을 적용하였으며, 서해의 조석 1주기를 재현함과 동시에 반사파랑을 최소화하기 위하여 동일한 스펙트럼(브렛슈나이더-Mytuyatu spectrum) 조건에서의 입사파랑을 15번 반복적으로 조파하였다. 실험 시 측정된 반사율은 0.05에 해당하며, PIV(Particle Image Velocimerty)시스템을 활용하여 인공어초 내부의 미세유동장을 측정하였다.

• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.23 no.1
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• pp.87-94
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• 2011

Characteristics of two-phase pressure drop in microchannels were investigated experimentally. The microchannels consisted of 9 parallel trapezoidal channels with each channel having $205\;{\mu}m$ of bottom width, $800\;{\mu}m$ of depth, $3.6^{\circ}$ of sidewall angle, and 7 cm of length. Pressure drops in convective boiling of Refrigerant 113 were measured in the range of inlet pressure 105~195 kPa, mass velocity $150{\sim}920\;kg/m^2s$, and heat flux $10{\sim}100\;kW/m^2$. The total pressure drop generally increased with increasing mass velocity and/or heat flux. Two-phase frictional pressure drop across the microchannels increased rapidly with exit quality and showed bigger gradient at higher mass velocity. A critical review of correlations in the literature suggested that existing correlations were not able to match the experimental results obtained for two-phase pressure drop associated with convective boiling in microchannels. A new correlation suitable for predicting two-phase friction multiplier was developed based on the separated flow model and showed good agreement with the experimental data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.6
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• pp.23-29
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• 2003

Transonic two-phase flow of Saturated humid air, in which relative humidity is 100%, with various condensation processes around thin airfoils is investigated. The study uses an extended transonic small-disturbance(TSD) model of Rusak and Lee [11, 12] which includes effects of heat addition to the flow due to condensation. Two possible limit types of condensation processes are considered. In the nonequilibrium and homogeneous process, the condensate mass fraction is calculated according to classical nucleation and droplet growth rate models. In the equilibrium process, the condensate mass fraction is calculated by assuming an isentropic process. The flow and condensation equations are solved numerical1y by iterative computations. Results under same upstream conditions describe the flow structure, field of condensate, and pressure distribution on airfoil's surfaces. It is found that flow characteristics, such as position and strength of shock waves and airfoil’s pressure distribution, are different for the two condensation processes. Yet, in each case, heat addition as a result of condensation causes significant changes in flow behavior and affects the aerodynamic performance of airfoils.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.35 no.6
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• pp.609-615
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• 2011

A two-dimensional Stokes flow past a vertical plate in a channel is analyzed. The vertical plate is located at the center of the channel, and plane Poiseuille flow exists far upstream and downstream of the vertical plate. The Stokes approximation is used, and the flow is investigated analytically using the method of eigenfunction expansion and the point collocation method. From the analysis, the stream function and pressure distribution are obtained, and the pressure and shear stress distributions on the plate and channel wall are calculated. The additional pressure drop induced by the vertical plate and the force exerted on it are calculated as functions of the length of the vertical plate. For a typical length of the vertical plate, the streamline pattern and pressure distribution are shown. In addition, numerical analysis of laminar flow with a small Reynolds number is carried out to analyze the effect of a small Reynolds number on the flow pattern.

• Proceedings of the Korean Vacuum Society Conference
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• 2016.02a
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• pp.227.2-227.2
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• 2016

환형 전자 빔이 진행됨에 따라 표면파의 전단 유동에 의해 발생 및 진행되는 diocotron instability(다이오코트론 불안정성)를 안정시키기 위해, 나선형 자기장이 인가된 상황을 2차원 PIC 시뮬레이션을 통해 구현하고 그 효과에 대한 조사가 수행되었다. 나선형 자기장은 2차원 단면 상에서 회전하는 자기장으로 표현되었고, 이에 대해서 자기장이 회전하는 각도와 회전 주기, 회전 방향을 변수로 하여 그 효과를 나타내었다. 결과적으로, 자기장이 회전 하는 방향과 전자 빔이 회전하는 방향이 반대가 되었을 때, diocotron instability가 진정되는 효과를 얻었으며 이는 불안정성의 근원인 전단 유동을 완화시킴으로써 얻어진 결과임이 확인되었다. 이 때, 동반되는 밀도 분산 현상에 대해서도 고려가 되었고, 결론적으로 인가되는 나선형 자기장에 대하여 가장 적절한 조건에 대한 조사가 수행되었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.4
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• pp.44-52
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• 2002

Aerodynamic characteristics of a flapping airfoil in low Reynolds number flows are numerically studied using the unsteady, incompressible Navier-Stokes flow solver with a two-equation turbulence model. For more efficient computation of unsteady flows over flapping airfoil, the flow solver is parallel-implemented by MPI programming method Unsteady computations are performed for low Reynolds number flows over a NACA four-digit series airfoils. Effects of pitching, plunging, and flapping motion with different reduced frequency, amplitude, thickness and camber on aerodynamic characteristics are investigated. Present computational results yield a better agreement in thrust at various reduced frequency with experimental data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.2
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• pp.89-97
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• 2020

In this study, a numerical analysis was performed on 26 inch single and coaxial propeller using the ANSYS Fluent 19.0 Solver to analyse the effect of the distance between coaxial propellers as one of the design parameter. The Moving Reference Frame (MRF) method was used for single propeller, while the sliding mesh method was used for a coaxial propeller to analyse the flow field varying with azimuth angle. The thrust and power are decreased as the upper and lower propeller approaching each other. As H/D is increased, interference between the propellers is decreased. According to the flow field variable contour of the coaxial propeller, it appears that the change in aerodynamic performance is due to the loading effect and the tip vortex wake effect.

• Korean Chemical Engineering Research
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• v.44 no.4
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• pp.375-381
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• 2006

In this sturdy, spherical activated carbon(SPAC) contained $TiO_2$ was made by ion-exchanged treatment and heat treatment for applying fluidizing bed system. The ion-exchange resin was treated by $TiCl_3$ aqueous solution. The treated resin and raw resin were heat-treated under nitrogen condition to convert into Ti-SPAC. During the heat-treatment, burn-off weight amounts and the element were measured by means of TGA and TGA/MS, individually. The physicochemical properties of Ti-SPAC was characterized by means of XRD, SEM, EDS, BET, EPMA, ESR, intensity and titanium content. The Ti-SPAC had spherical shape with diameter size about $350{\mu}m{\sim}400{\mu}m$ and $617m^2/g$ specific surface area. Structure of $TiO_2$ in Ti-SPAC was anatase and rutile form. Also, $TiO_2$ on SPAC were found that the $TiO_2$ were uniformly distributed through EPMA analysis. Moreover, the Ti-SPAC showed indirect photocatalyst activity estimation through ESR analysis, characteristics of photocatalyst potentially. Over all results, Ti-SPAC was used in fluidizing bed UV/photocatalyst system to remove HA(Humic Acid). That results were HA removal efficiency was about 70％ and Ti-SPAC intensity was preserved during reaction. Ti-SPAC showed practical possibility as photocatalyst in fluidizing bed system.