• Proceedings of the Korean Society for Bio-Environment Control Conference
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• 1999.11a
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• pp.109-113
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• 1999

겨울철 난방에너지와 여름철 냉방에너지 절감을 위한 자갈축열 태양열 온실의 설계자료를 얻고자 모형 자갈축열층과 이론적 해석을 통하여 축열층의 공기유동성 및 자갈축열층의 축열성능을 분석한 결과를 요약하면 다음과 같다. 1. 압출식으로 공기를 유동시켰을 경우 축열층내 풍속은 0.09-l.50㎧(평균 0.60㎧)범위였으며, 흡인식으로 공기를 유동시켰을 경우 축열층내 풍속은 0.15-0.90㎧(평균 0.46㎧)범위로 평균풍속은 압출식이 높게 나타났으나 축열층 가운데에서는 흠인식이 약 0.06㎧정도 높게 나타났다. 이러한 결과로 볼 때 자갈축열층내 공기순환을 위한 별도의 파이프 매설은 불필요한 것으로 판단된다. 2. 자갈축열층의 공극율이 증가할수록 축열량은 감소하였으며 순환팬 용량과 공극율에 따라 평균 2,133㎉/h-3,243㎉/h 정도 축열량 차이가 있는 것으로 나타났다. 3. 공극율이 0.45인 경우 축열층의 높이가 높을수록 자갈축열층의 온도는 서서히 증가하였으며, 축열층 높이 60cm이하에서는 축열 7시간이후부터는 축열량 변화를 거의 없는 것으로 나타났다. 4. 이러한 결과를 모형축열층에 있어 실험적으로 구해지는 축열 자갈층의 온도 및 축열량과의 비교 검증단계를 거쳐 온실규모에 필요한 적정 축열시스템을 산정할 수 있는 시뮬레이션 프로그램의 기초자료로 활용하고자 한다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2012.05a
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• pp.405-406
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• 2012

• Journal of Energy Engineering
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• v.11 no.3
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• pp.237-246
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• 2002

If the safety depressurization system of APR-1400, the Korean next generation reactor, is in operation, water, air and steam are successively discharging into a in-containment refueling water storage tank through spargers. Among the phenomena occurring during the discharging processes, the air bubble clouds produce a low-frequency and high-amplitude oscillatory loading, which may result in the most significant damages to the submerged structures if the oscillation frequency is the same or close to the natural frequency of the structures. The involved phenomena are so complicated that most of the prediction of frequency and pressure loads has been resorted to experimental work and computational approach has been precluded. This study deals with a numerical simulation on the behavior of air bubble clouds discharging into a water pool through a sparger, by using a commercial thermal hydraulic analysis code, FLUENT, version 4.5. Among the multiphase flow models, the VOF (Volume Of Fluid) model was selected to simulate the water, air and steam flows. A satisfactory result was obtained comparing the analysis results with the ABB-Atom test results which had been performed for the development of sparser.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.9
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• pp.714-719
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• 2013

A turboprop aircraft for this study is required to operate at icing condition in order that it performs its given mission. So an air intake system of the turboprop aircraft should be designed and verified not only to provide the maximum possible total pressure at engine inlet at normal flight condition, but also to include an inertial separator which protects Foreign Object Debris (FOD) like ice or snow at icing condition from entering into the engine inlet screen which can cause or lead an catastrophic engine failure like engine flame-out or severe damage. So an air intake assembly incorporating a variable geometry inertial separator has been designed and then CFD/structural analysis for the assembly was performed to see its design results. Then 35% scaled model of the air intake assembly was manufactured and wind tunnel test was done. This paper describes the detailed design results for the aerodynamic design, analysis and wind tunnel testing during the development process of the air intake assembly.

• Journal of Energy Engineering
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• v.10 no.2
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• pp.166-175
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• 2001

핀-관 열교환기의 효율을 증대시키기 위하여는 열저항을 결정하는데 있어서 중요한 역할을 하는 공기측 열전달 특성의 향상이 필요하다. 본 연구에서는 슬릿핀과 같은 핀 형상의 개선으로 인한 높은 압력손실을 감소시키기 위하여 타원관형 열교환기를 고려하였으며 이를 자체 개발한 3차원 비압축성 Navier-Stokes 코드를 이용하여 공기측 성능을 해석하였다. 이 코드는 시간항에 스칼라 내재적 근사분해법(scalar implicit approximate factorization)절차, 공간항에 유한체적법과 2차의 풍상차분법을 사용한다. 핀 형상이 평판핀인 타원관에 대하여 세장비가 0.3, 0.5, 0.75인 경우와 핀 형상이 슬릿핀이고 세장비가 0.5인 타원관에 대하여 공기측 유동을 해석하였으며 이를 원관의 성능과 비교하였다. 평판핀의 경우, 압력강하량은 원관과 비교하여 세장비가 작아질수록 감소하는 것을 볼 수 있었으며, 열전달 계수는 고려한 유입속도 범위에서 원관을 기준으로 약 5%이하의 변화로 거의 동일하게 유지되는 것을 볼 수 있었다. 슬릿핀의 경우 역시 문제되는 높은 압력강하량은 타원관을 도입함으로써 효과적으로 낮출 수 있음을 볼 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.4
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• pp.1-10
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• 2006

Separation motion analysis of staging system is conducted using combined analysis programs, which include unsteady aerodynamic analysis codes and dynamic motion analysis tools. In this study, the analysis is for the long-rang missile staging system. The purpose of this study is to verify the safety and reliance of the proposed staging system, and to find out the influence of angle of attack perturbation on staging. A structured parallel overset mesh called Chimera grid is used for the simulation of unsteady supersonic Euler flow solver. In addition, unsteady dynamic simulations are also performed.

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.2
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• pp.18-24
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• 1999

Liquid ramjet combustor is closely connected with complex phenomena due to a series of processes such as intake air, spray, mixing, and combustion. The present numerical experiments were peformed to investigate these flow characteristics for two and three dimensional liquid ramjet combustor. Grid system was made with three domains: intake region where air is supplied and fuel is injected, combustor and nozzle region, and exit atmosphere region. The numerical results showed that two and three dimensional flow patterns in recirculation region of combustor were significantly different each other and spray model was necessary to predict correctly the chemical reaction flow characteristics. Numerically examined for two different location of fuel injector, one is located on the bottom position of curved intake and the other is located on the top position. We found that bottom position of fuel injector is better than top position because fuel influx to the recirculation region which is need to sustain chemical reaction is more than the latter.

• Journal of the Korea Convergence Society
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• v.12 no.11
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• pp.291-299
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• 2021

Recently, due to environmental problems caused by densification and high rise of urban areas, interests in air flow is increasing and appropriate shape and layout design of buildings is required. Therefore, in this study, we intend to propose an experimental method that can observe the air flow around a building using thermochromic pigment. Thermochromic pigments have limitations in observing precise temperature changes due to the characteristic that the color changes only with respect to a specific temperature, but they have the advantages of easy configuration of experimental equipment and short time required for experiments. In this study, the air flow tendencies around a building was examined by performing CFD analysis for a simple model and then compared with the thermochromic experiment results in order to review the usefulness of the proposed experimental method. As a result of the experiment, it was possible to observe the formation of separated flow and vortex region generated by buildings using the charateristics of thermochromic pigment and it was confirmed that the proposed method can be useful for buildings design and urban city planning.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.11
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• pp.889-902
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• 2020

In this study, a numerical analysis was performed to confirm the formation of supersonic flow and the stabilization time satisfying the design condition in a Direct-connect supersonic combustor. The process was examined in which the high-pressure gas of vitiation air heater propagates downstream to the supersonic combustor and forms a supersonic flow field. It was confirmed through the analysis of pressure and temperature that the supersonic flow field satisfies the design points of Mach number 2.0 and 1,000 K, and requires a minimum of 4.0 ms for stabilization. These results indicate that the time required for the supersonic flow field stabilization should be taken into account when testing for the supersonic combustion experiment.

• Journal of the Korea Convergence Society
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• v.5 no.4
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• pp.75-79
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• 2014

In this study, a flow analysis is carried out on the wing shape of cooling fan at automobile. By designing three kinds of Canival, Teracan and basic models with CATIA program, this analysis is done on the configuration of cooling fan with the same flow condition. It can be seen that the contour of flow velocity is changed due to the model of wing and the pressure distribution of fluid is changed due to the configuration or the area of wing. In case of cooling model of Teracan among three models, there is the most air flow and it can be thought to be most effective to cool the radiator. And it is possible to be grafted onto the convergence technique at design and show the esthetic sense.