• 한국항공우주학회지
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• 제34권3호
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• pp.51-59
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• 2006

교반기 내에서의 교반속도 변화에 따라 제조된 자가치료용 마이크로캡슐의 물리적 특성을 입도분석기와 광학현미경을 통해 실험적으로 관찰하였다. 또한 자가치료용 마이크로캡슐의 제조공정을 이해하기 위해 3차원 수치해석의 수행을 통해 교반기 내에서의 유동 특성을 조사하였다. 연구결과에 따르면, 교반기 내에서의 교반속도는 마이크로캡슐의 크기를 결정하는 주요 인자임을 확인하였다. 액체가 혼합된 교반기 내에서는 회전하는 임펠러에 의해 제트와 끝단 와류 성분이 발생하였으며 임펠러의 블레이드 주위에 형성되는 와도는 교반속도가 높아질 때 증가함을 알 수 있었다. 또한 자가치료용 마이크로캡슐의 크기는 끝단 와류와 같은 작은 크기의 혼합 패턴 유동에 큰 영향을 받았다.

• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2006년도 추계학술대회 논문집(제1권)
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• pp.45-49
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• 2006

물분사장치가 부착된 NACA-0021 익 주변의 흐름을 입자영상유속계를 이용하여 고찰하였다. $R_w=6.0261{\times}10^4$에서 영각(a)을 $0^{\circ}{\sim}35^{\circ}$로 변화시켜가며, 물분사 속도를 0[m/s], 9.2[m/s]의 2가지로 조절한 결과 익 후류영역에서는 박리 후 비정상적인(unsteady) 재순환 ${\cdot}$ 재부착 영역이 형성되었으며, 박리영역의 폭이 콴다 효과(Coanda effect)를 갖는 물분사로 인하여 최대 1/3만큼 감소하는 경향을 확인하였다. ?Nㄴ사가 없는 조건에서의 박리는 영각(a) $17^{\circ}{\sim}18^{\circ}$ 부근에서 시작되는 것이 관측되었으나, 물분사를 시켰을 경우 $20^{\circ}{\sim}21^{\circ}$에서 박리가 시작되는 것을 유동관측을 통해 알 수 있었다. 유동계측을 통해 익의 후연부(trailing edge)에서 생성되었던 와(vortex, eddy)가 물제트분사로 인해 소멸되는 것을 알 수 있었고, 영각이 작고 물분사 유속이 빠를수록 박리영역의 감소가 더욱 가속화됨을 알 수 있었다.

• 대한의용생체공학회:의공학회지
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• 제24권1호
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• pp.37-44
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• 2003

본 실험연구에서는 정상유동상태에서 새롭게 설계된 자가팽창성 그래프트 스텐트의 수력학적 성능을 평가하고자 하였다. 코팅 재질이 다른 두 개의 그래프트 스텐트와 한 개의 타이티놀 금속스텐트가 실험에 사용되었으며, 유량이 가자 5, 10, 15 1/min에서 스텐트 전후에서의 압력변화 및 속도분포를 측정하였다. 스텐트 삽입에 의한 압력손실은 유량이 증가함에 지수적으로 증가하였다. 특히 15 1/min의 유량에서 다공성 PTFE 그래프트 스텐트와 TiNi 금속스텐트의 압력손실은 거의 동일하나 PU 그래프트 스텐트는 약 6배 이상의 현저한 증가를 보이고 있다. 스텐트 후류에서의 속도분포는 다공성 PTFE 그래프트 스텐트와 TiNi 금속스텐트는 유량에 관계없이 유사한 형태를 보여주고 있다. 그러나, PU 그래프트 스텐트에서는 특히 유량이 10 1/min 이상에서 속도분포가 비대칭적이고 관 중심에서의 상대적인 낮은 유속을 보여주고 있으며, 결과적으로 벽면전단응력 및 수직응력의 증가론 초래하고 있다. 이와같이 PU 그래프트 스텐트의 상대적으로 낮은 수력학적 성능은 스텐트가 보다 작은 관에 삽입되었을때 코팅재질의 낮은 유연성으로 인하여 스텐트의 표면에 주름이 발생하여 유동단면이 비대칭적으로 되고 벽면의 조도가 증가하며, 관벽과 스텐트와 틈새가 존재하여 제트류가 형성되기 때문으로 해석된다.

• 한국유체기계학회 논문집
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• 제11권6호
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• pp.24-30
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• 2008

In order to enhance the heat/mass transfer, a turbulator has been installed at the exit of injection hole for the impingement/effusion cooling system. The local heat/mass transfer coefficients have been obtained by a naphthalene sublimation method. Experiments have been carried out at the fixed jet Reynolds number of 10,000. Two turbulators with different diameter have been used in the current study. The result presents that the turbulator leads to the increase in flow mixing and jet velocity, consequently enhancing the heat/mass transfer at a stagnation region. Further, the stagnation region is divided into four small areas with peak value. In the existence of initial crossflow, the stagnation regions move downstream and low heat/mass transfer regions are formed regardless of the installation of turbulator. However, the increased jet velocity by turbulator reduces the crossflow effect against the jet, resulting in decrease of low heat/mass transfer regions. Compared to the case without turbulator, the installation of turbulator yields $5{\sim}10%$ augmentation in averaged Sh value.

• 대한기계학회논문집B
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• 제21권3호
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• pp.436-444
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• 1997

Three-dimensional conjugate heat transfer and particle deposition on a circular cylinder in the OVD process are numerically investigated. Flow and temperature fields are obtained by an iterative method, and thermophoretic particle deposition is simulated. Effects of the heat conduction in the cylinder, the rotation speed of the cylinder, and the traversing speed of torch on the deposition are studied. Effects of variable properties are also included. As the conductivity of the cylinder decreases, particle deposition rate and deposition efficiency greatly decrease due to the reduced temperature gradient. The rotation of the cylinder has no significant effect on the deposition due to the small diameter of the cylinder and low speed of rotation. Since the increase of the torch speed keeps the surface low temperature, the particle deposition increases with the traversing speed.

• 한국전산유체공학회지
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• 제7권3호
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• pp.9-16
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• 2002

Most of modem aerospace gas turbines must be operated at a gas temperature which is several hundreds of degrees higher than the melting temperatures of the materials used in their construction. Complicated cooling schemes need to be employed in the combustor walls and in the high pressure turbine stages. Internal passages are cast or machined into the hot sections of aero-gas turbine engines and air from the compressor is used for cooling. In many cases, the cooling system is engineered to utilize jets of high velocity air, which impinge on the internal surfaces of the components. They are categorized as 'Impinging Cooling Method' and 'Vortex Cooling Method'. Specially, research of new cooling system(Vortex Cooling Method) that overcomes inefficiency of film cooling and limitation of space. The focus of new cooling system that improves greatly cooling efficiency using less amount of cooling air on surface heat transfer elevation. Therefore, in this study, a numerical analysis has been peformed for characteristics of flow and heat transfer in the swirl chamber and compared with the flow measurements by LDV. Especially, for understanding high heat transfer efficiency in the vicinity of wall, we considered flow structure, vortex mechanism and heat transfer characteristics with variation of the Reynolds number.

• 한국연소학회지
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• 제4권1호
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• pp.49-57
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• 1999

An experimental study on double-concentric diffusion flame has been carried out in order to investigate the shape, the flame length, and the other characteristics of the flame. Flow visualization of the flame by the $TiO_2$ particles and also the emission measurements are conducted. The commercial grade LP gases are used as fuel. The inverse diffusion flames are formed at the center when the central air flow rate is about 0.1 L/min. With a larger flow rate of the central air jet than 0.2 L/min the flame turns to be an annular-shaped flame, which is very bright. When the central air flow rate increases over 2.4 L/min, the flame turns to blue and the flame tips are opened because of the lifting of the inner part of the flame. Because of this lifting and the incomplete combustion, the CO emission increases abruptly from 25 ppm to more than 150 ppm. On the contrary, the NOx emission is decreased.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 춘계 학술대회논문집
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• pp.126-131
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• 2004

The interaction between the hypersonic free stream and the side jet flow at high altitudes is investigated by direct simulation Monte Carlo(DSMC) method. Since there is a great difference in density between the free stream and the side jet flow, the weighting factor technique which could control the number of simulation particles, is applied to calculate these two flows simultaneously. Chemical reactions are not considered in the calculation. For validation, the corner flow passing between a pair of plates that are perpendicularly attached is solved. The side jet flow is then injected into this comer flow and solution is found for the merged flow. Results are compared with the experiments. For a more realistic rocket model, the flow past a blunted cone cylinder shape is solved. The leeward or windward jet injection is merged with this flow. The effect on the rocket surface is observed at various flow angles. The lambda effect and the wake structure are found like low attitudes. High interaction between the free stream and the side jet flow is observed when the side jet is injected in the windward direction.

• 한국군사과학기술학회지
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• 제6권4호
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• pp.124-131
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• 2003

When a secondary gaseous flow is injected vertically into a supersonic flow through circular nozzle, a complicated structure of flow field is produced around the injection area. The interaction between the two streams produces a strong bow shock wane on the upstream side of the side-jet. The results show that bow shock wave and turbulent boundary layer interaction induces the boundary layer separation in front of the side-jet. This study is to analyze the structure of flow fields and distribution of surface pressure on the flat plate according to total pressure ratio using a supersonic cold-flow system and also to study the control force of affected side-jet. The nozzle of main flow was designed to have Mach 2.88 at the exit. The injector has a sonic nozzle with 4mm diameter at the exit of the side-jet. In experiments, The oil flow visualization using a silicone oil and ink was conducted in order to analyze the structure of flow fields around the side-jet. The flow fields are visualized using the schlieren method. In this study, a computational fluid dynamic solution is also compared with experimental results.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 추계 학술대회논문집
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• pp.219-222
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• 2005

Recently, the interest of the engine capacity and environment of the atmosphere is increasing, so the researches for the engine capacity have been conducted for a long time. But the internal environment of an automotive engine is very severe. A piston is exposed to combustion gas of over $2000^{\circ}C$ and strong friction is occurred by high speed motion in the cylinder. The fraction between piston and wall of the cylinder causes the increase of temperature in the engine. The temperature of the engine has an effect on the engine capacity. If the temperature is high, the capacity of the engine is low. So we have to maintain the optimum temperature. To maintain the optimum temperature, the enough flow rate of the engine oil is needed. The oil jet is used to control the flow rate of the engine oil and supply the engine oil to the piston and cylinder. The purpose of this study is to check the mass flow rate of the engine oil and the characteristics of internal flow of the oil jet. Flow pattern of the engine oil is very important because it concludes the loss in the oil jet. This study is the previous research about the oil jet and we will consider the movement of the ball check valve to get more accuracy result.