• 한국실내디자인학회논문집
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• 제17권2호
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• pp.75-82
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• 2008

Weeks who is an architect in England suggest that let us consider the hospital architecture as not determined architecture but an undetermined architecture. Because it has been changing unexpectedly. The changing process of hospital architecture is required that it has to involve the new function and be a role model because of variations of environmental factors. For silving the requirements above mentioned, hospital architecture takes the way of appropriateness inner origin form and finally it considers new formation. The 53% of hospital buildings in Korea were built in 1980s. For 30years, these buildings have been not only extended a buildings but also changed in parts of functions and sizes on buildings which are original. The purpose of this study is producing the basic references which suggest solution to face on the changing of hospital building during planning it in the future using by analysis of variation inside the hospital building and grasping of characters in each departments. Each department is analyzed as follows. There is no inner change but only expansion partly by enlargement of building. In the outpatient, there is not only expansion by enlargement of building and but also extension toward other parts and the rate of variation of inside is high. In the diagnostic treatment, there are differences in diagnostic treatment. Surgical suit and diagnostic imaging have been expanded by enlargement than the change of inside. But the others of the departments have been changed by change of inside and also there are sometimes changes of inner walls.

• 한국자기학회지
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• 제27권1호
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• pp.23-29
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• 2017

시료 크기별 자화 역전과 자기 상호작용이 보자력에 미치는 영향을 조사한 결과, 자구생성보다 자벽고착에 의한 자화 역전 현상이 지배적인 시료일수록 보자력과 각형비가 컸다. 이와 같은 현상은 자벽이 낟알 경계면이나 시료 내부에 존재하는 고착점에 강하게 포획되기 때문인 것으로 판단된다. 한편 자기 상호작용을 분석한 결과, 시료의 크기에 무관하게 모든 시료는 쌍극자 상호작용이 지배적인 상호작용 기구이며, 쌍극자 상호작용이 강한 시료일수록 보자력이 작았다. 따라서 보자력은 자화 역전 현상, 자기 상호작용 기구와 세기에도 깊이 관련됨을 알 수 있다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.671-686
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• 2004

The shock-induced combustion ramjet (shcramjet) is a hypersonic airbreathing propulsion concept which over-comes the drawbacks of the long, massive combustors present in the scramjet by using a standing oblique detonation wave (a coupled shock-combustion front) as a means of nearly instantaneous heat addition. A novel shcramjet combustor design that makes use of wedge-shaped flameholders to avoid detonation wave-wall interactions is proposed and analyzed with computational fluid dynamics (CFD) simulations in this study. The laminar, two-dimensional Navier-Stokes equations coupled with a non-equilibrium hydrogen-air combustion model based on chemical kinetics are used to represent the physical system. The equations are solved with the WARP (window-allocatable resolver for propulsion) CFD code (see: Parent, B. and Sislian, J. P., “The Use of Domain Decomposition in Accelerating the Convergence of Quasihyperbolic Systems”, J. of Comp. Physics, Vol. 179, No. 1,2002, pages 140-169). The solver was validated with experimental results found in the literature. A series of steady-state numerical simulations was conducted using WARP and it was deter-mined by means of thrust potential calculations that this combustor design is a viable one for shcramjet propulsion: assuming a shcramjet flight Mach number of twelve at an altitude of 36,000 m, the geometrical dimensions used for the combustor give rise to an operational range for combustor inlet Mach numbers between six and eight. Different shcramjet flight Mach numbers would require different combustor dimensions and hence a variable geometry system in or-der to be viable.

• Tribology and Lubricants
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• 제32권3호
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• pp.101-105
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• 2016

Trap effect of groove is evaluated in a lubricating system using computational fluid dynamics (CFD) analysis. The simulation is based on the standard k-ε turbulence model and the discrete phase model (DPM) using a commercial CFD code FLUENT. The simulation results are also capable of showing the particle trajectories in flow field. Computational domain is meshed using the GAMBIT pre-processor. The various grooves are applied in order to improve lubrication characteristics such as reduction of friction loss, increase in load carrying capacity, and trapping of the wear particles. Trap effect of groove is investigated with variations in cross-sectional shape and Reynolds number in this research. Various cross-sectional shapes of groove (rectangular, triangle, U shaped, trapezoid, elliptical shapes) are considered to evaluate the trap effect in simplified two-dimensional sliding bearing. The particles are assumed to steel, and defined a single particle injection condition in various positions. The “reflect” boundary condition for discrete phase is applied to the wall boundary, and the “escape” boundary condition to “pressure inlet” and “pressure outlet” conditions. The streamlines are compared with particles trajectories in the groove. From the results of numerical analysis in the study, it is found that the cross-sectional shapes favorable to the creation of vortex and small eddy current are effective in terms of particle trapping effect. Moreover, it is found that the Reynolds number has a strong influence on the pattern of vortex or small eddy current in the groove, and that the pattern of the vortex or small eddy current affects the trap effect of the groove.

• 대한기계학회논문집B
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• 제38권12호
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• pp.1035-1042
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• 2014

엔진 마찰 저감은 엔진 개발의 중요한 항목이 되어왔다. 엔진의 기계적 마찰 손실 중 피스톤계의 마찰이 40~55%에 해당하고, 피스톤 부분의 마찰을 제거할 수 있다면 투입되는 전체 에너지의 5% 정도 향상시킬 수 있다. 엔진의 마찰 손실을 감소시키기 위해서 각 요소에서의 마찰 수준, 이에 영향을 미치는 인자에 대한 분석 및 다른 엔진들과의 비교분석이 필요하다. 하지만 기존 연구에서 마찰이 발생하는 윤활막의 연구들이 유체역학 바탕의 모델링에서 수행해 왔으나, 피스톤계의 윤활막이 크게는 마이크로에서 작게는 나노단위의 영역에 해당하므로 분자들간의 상호관계를 고려할 필요가 있다. 따라서, 본 연구에서는 엔진 실린더 라이너를 따라 형성하는 유막의 운동을 미시적으로 접근하여 분자들간의 상호작용에 따른 마찰변화를 제시하고자 한다.

• Advances in aircraft and spacecraft science
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• 제3권3호
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• pp.243-257
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• 2016

The increase of air traffic volume has brought an increasing amount of issues related to carbon and NOx emissions and noise pollution. Aircraft manufacturers are concentrating their efforts to develop technologies to increase aircraft efficiency and consequently to reduce pollutant discharge and noise emission. Ultra High By-Pass Ratio engine concepts provide reduction of fuel consumption and noise emission thanks to a decrease of the jet velocity exhausting from the engine nozzles. In order to keep same thrust, mass flow and therefore section of fan/nacelle diameter should be increased to compensate velocity reduction. Such feature will lead to close-coupled architectures for engine installation under the wing. A strong jet-wing interaction resulting in a change of turbulent mixing in the aeroacoustic field as well as noise enhancement due to reflection phenomena are therefore expected. On the other hand, pressure fluctuations on the wing as well as on the fuselage represent the forcing loads, which stress panels causing vibrations. Some of these vibrations are re-emitted in the aeroacoustic field as vibration noise, some of them are transmitted in the cockpit as interior noise. In the present work, the interaction between a jet and wing or fuselage is reproduced by a flat surface tangential to an incompressible jet at different radial distances from the nozzle axis. The change in the aerodynamic field due to the presence of the rigid plate was studied by hot wire anemometric measurements, which provided a characterization of mean and fluctuating velocity fields in the jet plume. Pressure fluctuations acting on the flat plate were studied by cavity-mounted microphones which provided point-wise measurements in stream-wise and spanwise directions. Statistical description of velocity and wall pressure fields are determined in terms of Fourier-domain quantities. Scaling laws for pressure auto-spectra and coherence functions are also presented.

• Advances in aircraft and spacecraft science
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• 제4권2호
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• pp.145-167
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• 2017

The presented paper gives an overview of several projects addressing the experimental characterization and control of the buffet phenomenon on 3D turbulent wings in transonic flow conditions. This aerodynamic instability induces strong wall pressure fluctuations and therefore limits flight domain. Consequently, to enlarge the latter but also to provide more flexibility during the design phase, it is interesting to try to delay the buffet onset. This paper summarizes the main investigations leading to the achievement of open and closed-loop buffet control and its experimental demonstration. Several wind tunnel tests campaigns, performed on a 3D half wing/fuselage body, enabled to characterize the buffet aerodynamic instability and to study the efficiency of innovative fluidic control devices designed and manufactured by ONERA. The analysis of the open-loop databases demonstrated the effects on the usual buffet characteristics, especially on the shock location and the separation areas on the wing suction side. Using these results, a closed-loop control methodology based on a quasi-steady approach was defined and several architectures were tested for various parameters such as the input signal, the objective function, the tuning of the feedback gain. All closed-loop methods were implemented on a dSPACE device able to estimate in real time the fluidic actuators command calculated mainly from the unsteady pressure sensors data. The efficiency of delaying the buffet onset or limiting its effects was demonstrated using the quasi-steady closed-loop approach and tested in both research and industrial wind tunnel environments.

• Geomechanics and Engineering
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• 제18권2호
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• pp.189-203
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• 2019

Brine leakage is a common phenomenon during construction facilitated by artificial freezing technique, threatening the stability of frozen wall due to the continual thawing of already frozen domain. This paper takes the frequently encountered soft clay in Wujiang District as the study object, and remolded specimens were prepared by mixing calcium chloride solutions at five levels of concentration. Both the deformation and pore water pressure of frozen specimens during thawing were investigated by two-stage loading tests. Three sections were noted from the changes in the strain rate of specimens during thawing at the first-stage load, i.e., instantaneous, attenuated, and quasi-stable sections. During the second-stage loading, the deformation of post-thawed soils is closely correlated with the dissipation of pore water pressure. Two characteristic indexes were obtained including thaw-settlement coefficient and critical water content. The critical water content increases positively with salt content. The higher water content of soil leads to a larger thaw-settlement coefficient, especially at higher salt contents, based on which an empirical equation was proposed and verified. The normalized pore water pressure during thawing was found to dissipate slower at higher salt contents, with a longer duration to stabilize. Three physical indexes were experimentally determined such as freezing point, heat conductivity and water permeability. The freezing point decreases at higher salt contents, especially as more water is involved, like the changes in heat conductivity. The water permeability maintains within the same order at the considered range of salt contents, like the development of the coefficient of consolidation. The variation of the pore volume distribution also accounts for this.

• Nuclear Engineering and Technology
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• 제53권4호
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• pp.1119-1126
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• 2021

Spacer grid with mixing vane had been widely used in nuclear reactor core. One of the main feather of spacer grid with mixing vane was that strong swirl flow was formed after the spacer grid. The swirl flow not only changed the bubble generation in the near wall field, but also affected the bubble behaviors in the center region of the subchannel. The interaction between bubble and the swirl flow was one of the basic phenomena for the two phase flow modeling in fuel assembly. To obatin better understanding on the bubble behaviors in swirl flow, full three dimension numerical simulations were conducted in the present paper. The swirl flow was assumed in the cylindral calculation domain. The bubble interface was captured by Volume Of Fluid (VOF) method. The properties of saturated water and steam at different pressure were applied in the simulation. The bubble trajectory, motion, shape and force were obtained based on the bubble parameters captured by VOF. The simulation cases in the present study included single bubble with different size, at different angular velocity conditions and at different pressure conditions. The results indicated that bubble migrated to the center in swirl flow with spiral motion type. The lateral migration was mainly related to shear stress magnitude and bubble size. The bubble moved toward the center with high velocity when the swirl magnitude was high. The largest bubble had the highest lateral migration velocity in the present study range. The effect of pressure was small when bubble size was the same. The prelimenery simulation result would be beneficial for better understanding complex two phase flow phenomena in fuel assembly with spacer grid.

• 한국자기학회지
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• 제9권4호
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• pp.190-195
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• 1999

최대 출력 3.5kW인 고주파에 의한 알곤 플라즈마 분위기에서 제작한 Fe1-xCox(x=0.2와 0.4)계와 25$\mu\textrm{m}$의 철 박막의 자기적인 성질을 상온에서의 X선 회절과 진동시료자력계를 이용한 자기이력곡선 측정 방법을 사용하여 연구하였다. arc로에서 제작된 시룐느 삼단계 처리 가공하였다. 첫째는 수압기로 9,000N/$\textrm{cm}^2$의 압력을 가하여 알약 형태로 만들었다. 이 단계는 압연기로 눌러 얇은 sheet로 만들었다. 삼단계는 시료는 질소 가스 분위기에서 90$0^{\circ}C$로 열처리하였다. 일단계 시료의 X선 회절결과는 시료가 균질이며 각 시료는 철과 동일한 bcc 결정구조를 갖는 단일결저상(single crystal phase)임을 보였다. 철 박막은 43 Oe의 항자력과 인가자기장에 대한 자화, 즉 초기 기울기는 0.328 emu/gOe를 나타냈다. 이단계 시료에서는 Co량이 증가함에 따라 항자력과 포화자화값은 증가하였다. 반면 초기 기울기는 감소하였다. 이는 항자력의 증가로 인해서 계면이동이 억제되었음을 의미한다. 삼단계 시료에서 두 시료 모두 포화자화값은 증가하였다. 반면 이들 시료의 항자력은 감소하였다. 3단계 시료의 포화자화의 열처리로 인한 시료의 X선 회절강도 변화와 연관이 있어 보인다. 또한 몇 개의 자기 매개변수를 단순모형을 써서 계산하여 다른값과 비교하였다.