• 한국인쇄학회지
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• 제18권2호
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• pp.69-82
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• 2000

Recently, as the prepress mainstream is changed to the digital workflow, various digital proofing systems such as high price dye sublimation printers and low price ink jet printers are widely used in printing industry. CRT monitors are also often used as a soft proofing device. However, it is very difficult to match the color image displayed on CRT monitors to the actual images printed on papers, because the color space of CRT monitors is RGB color system, and it is different with the CMY color system of the printing devices. Therefore, proper color compensations are needed to match the colors between hard-copy proofs on the printing device and soft copy proofs on CRT monitors. This paper shows the LUT and gamut mapping method considering the printing characteristics of output device is useful for the compensation.

• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 2000년도 하계학술대회 논문집
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• pp.193-197
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• 2000

BSCCO thin films are fabricated via a co-deposition process by an ion beam sputtering with an ultra-low growth rate, and sticking coefficients of the respective elements are evaluated. The sticking coefficient of Bi element exhibits a characteristic temperature dependence : almost a constant value of 0.49 below 73$0^{\circ}C$ and decreases linearly with temperature over 73$0^{\circ}C$. This temperature dependence can be elucidated from the evaporation and sublimation rates of bismuth oxide, Bi$_2$O$_3$, from the film surface. It is considered that the liquid phase of the bismuth oxide plays an important role in the Bi(2212) phase formation in the co-deposition process.

• 대한기계학회논문집
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• 제18권3호
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• pp.645-652
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• 1994

The leading edge of a turbine blade was simulated as a circular cylindrical surface. The effect of free-stream turbulence on the mass transfer upstream of the injectionhole has been investigated experimentally. The effects of injection location, blowing ratio on the Sherwood number distribution were examined as well. The mass transfer coefficients were measured by a naphthalene sublimation technique. The free-stream Reynolds number based on the cylinder diameter is 53,000. Other conditions investigated are: free-stream turbulence intensities of 3.9% and 8.0%, injection locations of $40^{\circ}$, $50^{\circ}$, and $60^{\circ}$ from the front stagnation point of the cylinder, and blowing ratios of 0.5 and 1.0. The role of the horseshoe vortex formed upstream edge of the injected jet is dicussed in detail. When the blowing ratio is unity, and the coolant jet is injected at $40^{\circ}$, the mass transfer upstream of the jet is not affected by the coolant jet at all. On the other hand, when the injection hole is located beyond $50^{\circ}$, the mass transfer upstream edge of the injection hole suddenly increases due to the formation of the horseshoe vortex, but it dereases as the free-stream turbulence intensity increases because the strength of the horseshoe vortex structure becomes weakened. The role of the horseshoe vortex is clearly evidenced by placing a rigid rod at the injection hole instead of issuing the jet. In the case of the rigid rod, the spanwise Sherwood number upstream of the injection hole is much larger due to the intense influence of the horseshoe vortex.

• 대한기계학회논문집
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• 제15권6호
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• pp.2132-2146
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• 1991

본 연구에서는 기존 유속계에 의한 측정이 어려운 점을 감안하여 나프탈렌 승 화법을 이용하여 열교환기 시스템의 한 모델인 원봉에 유한한 길이의 환상핀이 부착된 경우 환상핀과 원봉이 만나는 부분에서 와류들 특히 V2, V3등 구석와류가 물질전달을 증가시키는 구조에 대해 고찰한다. 이는 원봉 주위의 환상핀에 의한 대류 물질전달 에 영향을 줄수 있는 레이놀즈수, 환상핀의 크기에 따른 형상비, 그리고 경계층 두께, 배제 두께 등의 유동변수를 변화시켜 가며 물질전달률과의 관계를 규명하여 열교환기 설계의 기본자료를 제공한다. 또한 환상핀 사이의 원봉표면에 대한 전체물질전달률 을 측정하며, 환상핀에 인접한 곳에서 구석와류에 대한 환상핀의 끝 벽면 영향을 알아 보고 이를 근거로 하여 말굽와류의 3차원 박리 유동구조를 정성적으로 규명하고자 한 다.

• 한국결정학회지
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• 제3권1호
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• pp.23-30
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• 1992

단결정 a-SiC성장시 결정성장로의 감압속도가 결정 성장 속도, 결정성, 성장방향에 미치는 영향 을 고찰해 보기 위해서 승화법으로 (001)면 a-SiC 단결정 종자정위에 단결정 a-SiC를 성장시켰다. 결정성장 초기에는 성장로의 빠른 감압 속도에 따라 결정성장속도가 빨라지고 3C-SiC 다결정이 종자정위에 성장하였고, 감압속도를 느리게 한 경우에는 결정성장 속도가 느려지고 6H-SiC 단결정이 성장하였다. 초기에 단결정층이 성장하는 조건 하에서 2시간 성장후의 단면 성장 양상을 보면, 종자정 하단에서 발생하는 낙은 종자정의 연속적 인 승화 때문에 종자정과 초기의 단결정층이 소멸 되고, 종자정이 놓여있던 혹연 도가니의 바닥으로부터 연속적으로 다결정 층이 성장된 것이 관찰되었다. 그러나, 이러한 종자정의 승화 소멸은 초기 성장 후 냉각과정을 거치고 다시 승온시키는 두 단계 공정을 사용함으로써 효과적으로 억제시킬 수 있었다. 이와같은 방법으로 장시간 성장시킨 결정은 6H-HiC 단결정이었으며, (001) 방향으로 성장하였다.

• 대한기계학회논문집B
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• 제24권6호
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• pp.870-879
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• 2000

An experimental investigation is conducted to improve a slot film cooling system which can be used for the cooling of gas turbine combustor liner. The tangential slots are constructed of discrete holes with different injection types which are the parallel, vertical, and combined to the slot lip. The investigation is focused on the coolant supply systems of normal-, parallel-, and counter-flow paths to the mainstream direction. A naphthalene sublimation technique has been employed to measure the local heat/mass transfer coefficients in a slot with various injection types and coolant feeding directions. The velocity distributions at the exit of slot lip for the parallel and vertical injection types are fairly uniform with mild periodical patterns with respect to the hole positions. However, the combined injection type increases the nonuniformity of flow distribution with the period equaling twice that of hole-to-hole pitch due to splitting and merging of the ejected flows. The secondary flow at the lip exit has uniform velocity distributions for the parallel and vertical injection types, which are similar to the results of a two-dimensional slot injection. In the results of local heat/mass transfer coefficient, the best cooling performance inside the slot is obtained with the vertical injection type among the three different injection types due to the effect of jet impingement. The lateral distributions of Sh with the parallel- and counter-flow paths are more uniform than the normal flow path. The averaged Sh with the injection holes are $2{\sim}5$ times higher than that of a smooth two-dimensional slot path.

• 대한기계학회논문집B
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• 제23권5호
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• pp.577-586
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• 1999

Two problems with jet injection through the cylindrical film cooling hole are 1) penetration of jet into mainstream rather than covering the surface at high blowing rates and 2) nonuniformity of the film cooling effectiveness in the lateral direction. Compound angle injection is employed to reduce those two problems. Compound angle injection increases the film cooling effectiveness and spreads more widely. However, there is still lift off at high blowing rates. Shaped film cooling hole is a possible means to reduce those two problems. Film cooling with the shaped hole is investigated in this study experimentally. Film cooling hole used in present study is a shaped hole with conically enlarged exit and Inlet-to-exit area ratio is 2.55. Naphthalene sublimation method has been employed to study the local heat/mass transfer coefficient and film cooling effectiveness for compound injection angles and various blowing rates around the shaped film cooling hole. Enlarged hole exit area reduces the momentum of the jet at the hole exit and prevents the penetration of injected jet into the mainstream effectively. Hence, higher and more uniform film cooling effectiveness values are obtained even at relatively high blowing rates and the film cooling jet spreads more widely with the shaped film cooling hole. And the injected jet protects the surface effectively at low blowing rates and spreads more widely with the compound angle injections than the axial injection.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2004년도 유체기계 연구개발 발표회 논문집
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• pp.140-150
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• 2004

In this study, the effect of relative position of the blade for the fixed vane has been investigated on blade surface heat transfer. The experiments were conducted in a low speed stationary annular cascade, and heat transfer of blade was examined for six positions within a pitch. Turbine test section has one stage composed of sixteen guide vanes and blades. The chord length of the tested blade is 150 mm and the mean tip clearance of the blade having flat tip is about $2.5\%$ of the blade chord. For the detailed mass transfer measurements on the blade surfaces, a naphthalene sublimation technique was used. The inlet flow Reynolds number is fixed to $1.5{\times}10^5$. Complex heat transfer characteristics are observed on the blade surface due to various flow characteristics, such as separation bubble, relaminarization, transition to turbulence and leakage vortices. The distributions of velocity and turbulence intensity change significantly with the relative position due to the blockage effect of the blade. This causes the variation of heat transfer patterns on the blade surface. The results show that the flow near the leading edge get highly disturbed and deflected toward the either side of the blade when the blade leading edge is positioned close to the trailing edge of the vane. Therefore, separation bubble disappears on the pressure side and overall heat transfer on the relaminarization region is increased. But, due to reduced tip gap flow at the upstream region, the effect of leakage flow on the upstream region of the blade surface is weakened. Thus, the heat transfer characteristics significantly change with the blade positions.

• 한국결정성장학회지
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• 제5권1호
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• pp.50-59
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• 1995

자체 제작된 승화법에 의한 결정성장 장치를 이용하여, 6H-SiC 단결정을 성장하였다. Acheson 법으로 얻어진 6H 결정을 seed substrate로 사용하였으며, SiC source 로부터 분해된 승화 증기가 seed상에서 육성되도록 흑연 도가니내의 온도구배 및 성장온도와 압력을 유기적으로 조절하였다. 성장 전 graphite 도가니 구성부와 SiC 원료에 대한 purification을 행함으로써 성장결정 내부로의 불순물 혼입이 억제되도록 하엿다. 결정 성장시의 육성조건으로 도가니 바닥의 온도는 $2300~2400^{\circ}C$였으며, 성장로 내부의 분위기 압력은 200~400 torr에서 양질의 단결정을 얻을 수 있었다. 성장된 결정을 두께 1.5 mm의 wafer로 제작하여 XRD와 optical microscope로 관찰하였고, FT-IR spectrum으로 분석하였다.

• 대한기계학회논문집B
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• 제29권4호
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• pp.495-503
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• 2005

Experiments were conducted in a low speed stationary annular cascade to investigate local heat transfer characteristics on the tip and shroud and the effect of inlet Reynolds number on the tip and shroud heat transfer. Detailed mass transfer coefficients on the blade tip and the shroud were obtained using a naphthalene sublimation technique. The turbine test section has a single stage composed of sixteen guide vanes and blades. The chord length and the height of the tested blade are 150 mm and about 125 mm, respectively. The blade has flat tip geometry and the mean tip clearance is about $2.5{\%}$of the blade chord. The inlet flow Reynolds number based on chord length and incoming flow velocity is changed from $1.0{\times}10^{5}\;to\;2.3{\times}10^{5}.$ to investigate the effect of Reynolds number. Flow reattachment after the recirculation near the pressure side edge dominates the heat transfer on the tip surface. Shroud surface has very intricate heat/mass transfer distributions due to complex flow patterns such as acceleration, relaminarization, transition to turbulent flow and tip leakage vortex. Heat/mass transfer coefficient on the blade tip is about 1.7 times as high as that on the shroud or blade surface. Overall averaged heat/mass transfer coefficients on the tip and shroud are proportional to $Re_{c}^{0.65}\;and\;Re_{c}^{0.71},$ respectively.