• 한국윤활학회:학술대회논문집
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• 한국윤활학회 1997년도 제25회 춘계학술대회
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• pp.204-209
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• 1997

This paper reports on the theoretical study of the vane motions in a positive displacement vane pump. Vane detachment cause the pressure fluctuation, noise, wear in cam ring, and decrease the volumetric efficiency. Dynamic equation of vane motion and flow continuity equation have been modeled and solved simultaneously using 4th order Runge-Kutta method. As results of analysis, vane detachment occurs due to pressure overshoot by excess compression in the pumping chamber. Amount of vane detachment has been reduced by decreasing the pressure overshoot.

• Bulletin of the Korean Chemical Society
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• 제20권9호
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• pp.1031-1034
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• 1999

Tin oxide films have been grown employing the chemical vapor deposition technique under reduced pressure conditions using tetramethyltin as the precursor and oxygen as the oxidant. An activation energy derived for the deposition reaction under representative deposition conditions has a value of 89±3 kJ mol-1, suggesting a typical kinetic control. Deposition rates of tin oxide films exhibit a near first order dependence on tetramethyltin partial pressure and a zeroth order dependence on oxygen partial pressure. This study provides the first quantitative information about the growth kinetics of tin oxide films from tetramethyltin by the cold-wall low-pressure chemical vapor deposition.

• Korean Chemical Engineering Research
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• 제53권5호
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• pp.614-619
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• 2015

미세입자의 플라즈마 표면 개질을 감압상태하의 순환유동층 반응기에서 수행하였다. 플라즈마에 의해 처리된 폴리스타이렌 입자는 폴리에틸렌글리콜로 표면에 그래프팅하였다. 표면 개질 전 입자와 플라즈마 처리된 입자 그리고 그래프팅된 입자의 특성은 각각 DPPH 방법, FTIR, SEM 그리고 접촉각 측정으로 분석하였다. 플라즈마 처리된 폴리스타이렌 입자의 표면에 과산화물이 잘 형성되었다. 또한, 폴리에틸렌글리콜의 그래프팅 중합에 의해 플라즈마 처리된 입자 표면에 그래프팅이 잘 분산되었다. 따라서 감압상태의 순환 유동층 반응기에서 플라즈마 처리에 의한 PEG-g-PS 입자를 성공적으로 형성할 수 있었다.

• 대한전자공학회논문지
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• 제22권1호
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• pp.34-40
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• 1985

시스뎀 압력이 1.0 기압[대기압 공정]일 경우와 0.1 기압(감압 공정)일 경우에 대해, SiH2Cl2를 사용했을 때의 에퍼택셜층 및 폴리실리콘의 성장 현상과 HCI을 사용했을 때의 이것들의 에칭 현상을 조사하였다. 실험적으로 구한 성장 속도 및 에칭 속도에 대한 식들로부터 Sih2Cl2와 HCI을 혼합하여 사용할 경우에 대한 선화적 에퍼택시가 가능한 공정 조건이 예측되었다. 그 결과, 선택적 에퍼택셜 성장 영역이 감압 공정에서는 실험 범위내에서 존재하였지만 대기압 공정에서는 존재하지 않는 것으로 나타났다. 이 것은 대기압과 감압에서의 성장 속도 및 에칭 속도가 차이가 나기 때문에 기인하는 것이다.

• 한국전기전자재료학회논문지
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• 제17권12호
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• pp.1301-1307
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• 2004

Reduced pressure chemical vapor deposition(RPCYD) technology has been investigated for the growth of SiGe epitaxial films with two dimensional in-situ doped boron impurities. The two dimensional $\delta$-doped impurities can supply high mobility carriers into the channel of SiGe heterostructure MOSFETs(HMOS). Process parameters including substrate temperature, flow rate of dopant gas, and structure of epitaxial layers presented significant influence on the shape of two dimensional dopant distribution. Weak bonds of germanium hydrides could promote high incorporation efficiency of boron atoms on film surface. Meanwhile the negligible diffusion coefficient in SiGe prohibits the dispersion of boron atoms: that is, very sharp, well defined two-dimensional doping could be obtained within a few atomic layers. Peak concentration and full-width-at-half-maximum of boron profiles in SiGe could be achieved in the range of 10$^{18}$ -10$^{20}$ cm$^{-3}$ and below 5 nm, respectively. These experimental results suggest that the present method is particularly suitable for HMOS devices requiring a high-precision channel for superior performance in terms of operation speed and noise levels to the present conventional CMOS technology.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2003년도 추계학술대회논문집
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• pp.92-97
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• 2003

By using a centerbody injection, an effort to reduce shock assoicated noise is made in an underexpanded sonic nozzle with an exit diameter of 10mm. The centerbody or micro nozzle, aligned with the axis of the main jet has an o.d. of 2mm and i.d. of 1.5mm. When measured at 90$^{\circ}$ relative to the main jet the farfield noise spectra showed that the screech tones and broadband shock associated noise can be significantly reduced simply by varying the length of the centerbody and/or mass fraction of the microjet. The maximum reduction in overall sound pressure level (OASPL) was as much as 9 and 4 ㏈ at fully expanded jet Mach numbers Mi of 1.3 and 1.5, respectively, when the length of the centerbody was varied from 0 to 4 main nozzle diameters without blowing. With the aid of the blowing, the maximum reduction in OASPL increased to 12 and 7 ㏈ at M$\sub$j/=1.3 and 1.5, respectively. The impact pressure field in the main jet plume strongly suggested that the reduced periodic pressure distribution in the shear layers and/or centerline is responsible for the reduced screech and broadband shock associated noise. Therefore, the steady blowing by a micro centerbody is a promising technique for shock noise reduction in a supersonic jet.

• 대한기계학회논문집B
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• 제22권4호
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• pp.468-480
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• 1998

The temporal and spatial distributions of soot volume fractions were measured for single toluene droplet flames as a function of pressure under the normal-gravity condition. In order to characterize the transient nature of the flame and sooting regions, a full-field light extinction and subsequent tomographic inversion technique was used. The reduction in sooting as a function of pressure was assessed by comparison of the maximum soot volume fractions at several vertical positions along the axis above the droplet. The maximum soot volume fraction was reduced by 70% when the pressure was reduced by 60% from 1 atm to 0.4 atm. The reduction in sooting is attributed to variation of the geometric configuration of flame which reduces the system Grashof number as well as only the change in the adiabatic flame temperature as the pressure decreases. The gravimetrically-measured total soot yield was also compared to the optically-measured soot volume fraction to obtain a correlation between the two measurements. As a result, the total soot yield was linearly proportional to the optically-measured maximum soot volume fraction and linearly reduced as the pressure decreased. Accordingly, the non-intrusive full-field light extinction-measurements were able to be calibrated not only to measure soot volume fraction, but to simultaneously evaluate the total soot yield emitted from the toluene droplet flame (which is useful in the practical application).

• 한국터널지하공간학회 논문집
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• 제2권2호
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• pp.3-10
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• 2000

고속열차가 터널에 진입할 때 압축파가 터널 내부로 전파된다. 이 압축파와 연관된 터널출구 미기압파는 고속철도 열차-터널 인터페이스에서 발생되는 독특한 물리현상이다. 미기압파를 저감시키는 방법중에 터널 입 출구부에 공기역학적인 구조물을 사용하여 압축파의 시간에 대한 구배를 지연시키는 방법이 있다. 본 연구의 목적은 터널주행 열차모형 시험기로 최적의 경사갱구를 개발하는 것이다. 경사갱구의 경사각도에 따른 시험을 통한 시험결과에서 터널 입구부에 $45^{\circ}$ 경사갱구를 적용했을 때 미기압파 최대 피크값이 19.2 %가 저감되었다. 터널 입 출입구 양쪽에 $45^{\circ}$ 경사갱구를 적용할 경우는 41.2% 저감되었다. 또한 터널 입 출입구 양쪽에 $30^{\circ}$ 경사갱구를 적용할 경우는 미기압파 최대 피크값이 34.6% 저감되었다.

• 한국수소및신에너지학회논문집
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• 제20권6호
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• pp.499-504
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• 2009

The effect of gas diffusion layer (GDL) compression caused by different stack clamping pressures on fuel cell performance was experimentally studied in a miniature 5-cell proton exchange membrane fuel cell (PEMFC) stack. Three stacks with different GDL compressions, 15%, 35% and 50%, were prepared using SGL 10BC carbon fiber felt GDL and Gore 57 series MEA. The PEMFC stack performance and the stack stability were enhanced with increasing stack clamping pressure resulting in the best performance and stability for the stack with higher GDL compressions up to 50%. The excellent performance of the stack with high GDL compression was mainly due to the reduced contact resistance between GDL and bipolar plate in the stack, while reduced gas permeability of the excessively compressed GDL in the stack hardly affected the stack performance. The high stack clamping pressure also resulted in excessive GDL compression under the rib areas of bipolar plate and large GDL intrusion into the channels of the plate, which reduced the by-pass flow in the channels and increase gas pressure drop in the stack. It seems that these phenomena in the highly compressed stack enhance the water management in the stack and lead to the high stack stability.

• Journal of Mechanical Science and Technology
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• 제19권8호
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• pp.1632-1648
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• 2005

The effects of Reynolds number on the non-nulling calibration of a typical cone-type five-hole probe have been investigated for the representative Reynolds numbers in turbomachinery. The pitch and yaw angles are changed from - 35 degrees to 35 degrees with an angle interval of 5 degrees at six probe Reynolds numbers in range between $6.60{\times}10^3\;and\;3.17{\times}10^4$. The result shows that not only each calibration coefficient itself but also its Reynolds number dependency is affected significantly by the pitch and yaw angles. The Reynolds-number effects on the pitch- and yaw-angle coefficients are noticeable when the absolute values of the pitch and yaw angles are smaller than 20 degrees. The static-pressure coefficient is sensitive to the Reynolds number nearly all over the pitch- and yaw-angle range. The Reynolds-number effect on the total-pressure coefficient is found remarkable when the absolute values of the pitch and yaw angles are larger than 20 degrees. Through a typical non-nulling reduction procedure, actual reduced values of the pitch and yaw angles, static and total pressures, and velocity magnitude at each Reynolds number are obtained by employing the calibration coefficients at the highest Reynolds number ($Re=3.17{\times}10^4$) as input reference calibration data. As a result, it is found that each reduced value has its own unique trend depending on the pitch and yaw angles. Its general tendency is related closely to the variation of the corresponding calibration coefficient with the Reynolds number. Among the reduced values, the reduced total pressure suffers the most considerable deviation from the measured one and its dependency upon the pitch and yaw angles is most noticeable. In this study, the root-mean-square data as well as the upper and lower bounds of the reduced values are reported as a function of the Reynolds number. These data would be very useful in the estimation of the Reynolds-number effects on the non-nulling calibration.