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

• 대한조선학회논문집
• /
• 제36권1호
• /
• pp.22-29
• /
• 1999

선박의 고속화에 따라서 선체를 부양시키거나 자세를 제어하기 위하여 높은 양력을 발생시키는 장치의 필요성이 증대하게 되었다. 뿐만 아니라 해양오염방지를 위하여 IMO 등의 국제기구에서는 대형 신조선에 대하여 충분한 조종성능을 확보할 것을 권장하고 있어서 높은 양력을 발생시키는 타의 필요성이 증대하게 되었다. 높은 양력을 얻는 문제는 항공분야에서 오래 전부터 핵심적인 문제로 다루어져 왔으며 그중 대표적인 것이 Coanda장치이다. 방형비척계수가 크고 길이-폭비가 작은 저속비대선에서는 통상적인 타를 부착한 경우에 높은 양력을 얻기 어려우므로 플랩이 부탁된 타를 선정하고 이에 Coanda장치를 도입하였을 때 성능이 향상되는 것을 선형시험수조에서 실험적으로 확인하고자 하였다.

• 대한조선학회논문집
• /
• 제42권1호
• /
• pp.1-9
• /
• 2005

Waterjet propulsion is widely used to thrust high speed marine vessels in excess of 30-35 knots by virtue of the high propulsive efficiency, good maneuverability, and less cavitation. From the aspect of power loss, approximately $7-9\%$ of the total power is lost in intake duct due to the flow separation, nonuniformity, etc. Thus, detail understanding of flow phenomena occurring within intake duct is essential to reduce the power loss, as well as noise and vibration. The present work solved 30 incompressible RANS equations to provide complicated viscous flow features of intake duct. The numerical results were compared with experiments and good agreements were obtained for three jet velocity ratios.

• 한국분무공학회지
• /
• 제11권4호
• /
• pp.220-227
• /
• 2006

Experimental studies has been conducted to investigate the effect of orifice diameter ratio on the mixing characteristics of the split element of doublet and triplet elements. The spray characteristics of non-reacting immiscible liquids have been investigated using a patternator. The local volume fraction is measured by use of mean value of each component. This volume measurement represents the mixing characteristics of the liquid, which affect the overall combustion efficiency. The ratio of the orifice diameter, ranging from 1 to 1.5, and that of the jet-momentum, ranging from 0.5 to 6.0, we used. The jet impinging behavior with use of various ratios exhibits substantially different mixing characteristics. Mixing efficiency is maximized when the jet-momentum ratio is increased; this behavior is particularly prominent when the orifice diameter ratio is greater than unity. The split of the triplet element yields better mixing characteristics and is more effective than that of the doublet element in regard to achieving high combustion efficiency. The optimum mixing factor for the triplet element is found to be 0.75, according to our measurement.

• 대한기계학회논문집
• /
• 제18권7호
• /
• pp.1851-1865
• /
• 1994

The objective of the present study is to predict the film cooling effectiveness by a row of holes at various injection ratios and injection angles. Numerical calculations have been performed to investigate the characteristics of flow and temperature distributions in a region near the down-stream of injection hole including the region of adverse pressure gradient. The elliptic turbulent 3-dimensional governing equations with variable thermal properties using the low-Reynolds number k-$\bar{varepsilon}$ model was solved by SIMPLE algorithm. The results showed that the presence of adverse pressure gradient and secondary vortex in the region near the downstream of injection hole induces large temperature gradent. The $45^{\circ}$ injection has higher averaged film cooling effectiveness than $60^{\circ}$ injection. But neverthless the $90^{\circ}$ injection has greater deviation from a flat plate than $45^{\circ}$ and $60^{\circ}$ injection, the $90^{\circ}$ injection has higher averaged film cooling effectiveness than $45^{\circ}$ and $60^{\circ}$ injection in the region near the downstream of injection hole.

• 한국전산유체공학회:학술대회논문집
• /
• 한국전산유체공학회 2008년도 춘계학술대회논문집
• /
• pp.61-64
• /
• 2008

The present study of these experiments are close examination of spray characteristics that are continuous liquid jet and modulated pressure pulse liquid jet. The experiments were conducted using water, over a range of cross-flow velocities from 42${\sim}$136 m/s, with injection frequencies of 35.7${\sim}$166.2 Hz. Between continuous cross-flow jet and pressure pulsed cross-flow jet for characteristics of penetration, breakup point, spray angle and macro spray shape are investigated experimentally. In cross-flow field, main parameter of liquid jet for breakup was cross-flow stream rather than pressure pulse frequency. As oscillation of the periodic pressure that could make liquid jet moved up and down, the mixing efficiency was increased. Also, a bulk of liquid jet puff was detected at upper field of liquid surface. So, this phenomenon has a good advantage of mixing spray from concentration of center area to outer area. Because of pressure pulsation frequency, an inclination of SMD for the structured layer was evanescent. Cross-sectional characteristics of SMD at downstream area were non-structured distributions. Then cross-sectional characteristics of SMD size were about same tendency over a range that is effect of spray mixing. The tendency of volume flux value for various frequency of pressure pulse was same distribution. And volume flux was decreased when the frequency of pressure pulse increase.

• 대한기계학회논문집B
• /
• 제22권7호
• /
• pp.927-936
• /
• 1998

In the fully developed pipe flow, when jet is injected in cross to the flow there are complex transition flows caused by interaction of the cross flow and jet. These interactions are studied by means of the flow visualization methods and frequency analysis using a hot-wire anemometer. The velocity range of cross flow of the pipe is 0.3 m/s ~ 1.2 m/s and the corresponding Reynolds number, R$\sub$p/, based on the pipe diameter is 2.25 * 10$\^$3/ ~ 9.02 * 10$\^$3/. The velocity ratio (R), jet velocity/cross flow velocity, is chosen from 2 to 10. A circular cylinder is placed in the pipe instead of jet to observe the vortex shedding from the solid body. To compare the jet and circular cylinder flow, the vortical structure is analyzed in both cases and the structure of vortices and the origin of its formation are investigated, especially. The vortex shedding of the dominant coherent structure is compared between the jet flow and the circular cylinder flow. In the case of the jet flow, the Strouhal numbers are different depending on the existence of the upright vortex as well as the velocity ratio (R).

• 대한기계학회논문집B
• /
• 제20권4호
• /
• pp.1363-1375
• /
• 1996

Oil-film flow visualizations and three-dimensional flow measurements using a five-hole probe have been conducted to investigate three-dimensional flow characteristics and total pressure losses of a row of film-cooling jets injected in spanwise direction. For several span-to-diameter ratios, experiments are performed in the case of three velocity ratios of 0.5, 1.0 and 1.5. The flow measurements show that downstream flow due to the injection is characterized by a single streamwise vortex instead of a pair of counter-rotating vortices, which appear in the case of streamwise injection, and the vortex strength strongly depends on the velocity ratio. Regardless of the velocity*y ratio, presence of the spanwise film-cooling jets always produces total pressure loss, which is pronounced when the velocity ratio is large. It has also been found that the production of the total pressure loss is closely related to the secondary vortical flow. In addition, effects of the span-to-diameter ratio on the flow and total pressure loss are discussed in detail.

• 한국진공학회:학술대회논문집
• /
• 한국진공학회 2014년도 제46회 동계 정기학술대회 초록집
• /
• pp.423.2-423.2
• /
• 2014

비정질 실리콘 박막 태양전지는 1970년대 중반 개발된 이후 현재까지 지속적으로 연구 개발이 이루어져 왔으며, 대면적의 용이성 및 재료 사용의 효율성 등 산업적 측면에서 많은 장점을 보이고 있다. 하지만, 재료 특유의 무질서(disorder)로 인한 Voc의 한계 및 광 열화 현상 등의 문제점이 극복해야 할 과제로 남아있다. 이를 개선하기 위한 시도 중 하나로 나노입자를 포함한 실리콘 박막 제작을 통해 재료의 무질서도를 낮추고 전기광학적 물성을 개선하는 방법이 제안되고 있다. 본 연구에서는 유도결합 플라즈마(ICP, Inductively coupled plasma)를 사용하여 제작한 실리콘 나노입자 박막으로 비정질 실리콘 박막의 한계를 극복하고자 한다. 실리콘 나노입자를 사용하여 조밀한 박막을 제작하는데 중요한 변수로는 유도결합 플라즈마 반응기 상, 하부의 압력차 및 이로 인한 제트분사의 속력, 그리고 나노 입자의 크기 등이 중요하게 작용한다. 합성된 입자의 크기와 물성의 변화는 유입되는 반응 가스의 양, 공정압력과 파워에 의존한다. 실리콘 나노입자 박막을 다양한 플라즈마 조건에 따라 제작한 후 XRD, Raman, SEM, TEM을 이용하여 물성 변화를 관찰하였으며, 이를 통해 박막태양전지로의 응용 가능성을 제시하고자 한다.

• 한국분무공학회지
• /
• 제7권3호
• /
• pp.12-17
• /
• 2002

In this paper, spray and combustion characteristics of a liquid-fueled ramjet engine were experimentally investigated. The spray penetrations were measured to clarify the spray characteristics of a liguid jet injected transversely into the subsonic vitiated airstream, which is maintained a high velocity and temperature. The spray penetrations are increased with decreasing airstream velocity, increasing airstream temperature, and increasing air-fuel momentum ratio. To compensate our results of penetrations, the new experimental equation were modified from Inamura's equation. In the case of insufficient penetration, the combustion phenomenon in ram-combustor were unstable. Therefore, the temperature distribution was slanted to the low wall of the ram-combustor. These trends gradually disappeared as the length and air temperature of the combustor became longer. Combustion efficiency increased when the length of the combustor was long and the air temperature was high. Especially, stable flame region is enlarged when the length of the combustor was long and the air temperature was high. Type Abstract here. Type Abstract here.