• 수산해양기술연구
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• 제34권2호
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• pp.212-222
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• 1998

Heat transfer performance improvement by fin and groovs is studied for condensation of R-11 on integral-fin tubes. Eight tubes with trapczodially shaped integral-fins having fin density from 748 to 1654fpm(fin per meter) and 10, 30 grooves are tested. A plain tube having the same diameter as the finned tubes is also used for comparison. R-11 condensates at saturation state of 32 $^{\circ}C$ on the outside tube surface coded by inside water flow. All of test data are taken at steady state. The heat transfer loop is used for testing singe long tubes and cooling is pumped from a storage tank through filters and folwmeters to the horizontal test section where it is heated by steam condensing on the outside of the tubes. The pressure drop across the test section is measured by menas pressure gauge and manometer. The results obtained in this study is as follows : 1. Based on inside diameter and nominal inside area, overall heat transfer coefficients of finned tube are enhanced up to 1.6 ~ 3.7 times that of a plain tube at a constant Reynolds number. 2. Friction factors are up to 1.6 ~ 2.1 times those of plain tubes. 3. The constant pumping power ratio for the low integral-fin tubes increase directly with the effective area to the nominal area ratio, and with the effective area diameter ratio. 4. A tube having a fin density of 1299fpm and 30 grooves has the best heat transfer performance.

• 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.

• 설비공학논문집
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• 제16권9호
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• pp.845-854
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• 2004

The evaporation heat transfer coefficient for R-l34a, R-407C (a mixture of 23wt% R-32, 25 wt% R-125, and 52 wt% R-l34a) and R-410A (a mixture of 50 wt% R-32 and 50 wt% R-125) flowing in the oblong shell and plate heat exchanger were investigated experimentally in this study. Four vertical counterflow channels were formed in the exchanger by four plates of commercial geometry with a corrugated sinusoid shape of a chevron angle of 45 degree. The effects of the mean vapor quality, mass flux, heat flux, and saturation temperature of different refrigerants on the evaporation heat transfer were explored in detail. Similar to the case of a Plate heat exchanger, even at a very low Reynolds number, the flow in the oblong shell and plate heat exchanger remains turbulent. It is found that the evaporation heat transfer coefficient in the plates is much higher than that in circular pipes. The present data show that the evaporation heat transfer coefficients of all refrigerants increase with the vapor quality. At a higher mass flux h, is higher than for the entire range of the vapor quality. Raising the imposed wall heat flux was found to slightly improve h$_{r}$, while h$_{r}$ is found to be lower at a higher refrigerant saturation temperature. A comparison of the performance of the various refrigerants reveals that R-410A has the highest heat transfer performance followed by R-l34a, and R-407C had the lowest performance of the refrigerants tested. Based on the present data, empirical correlations of the evaporation heat transfer coefficient were proposed.sed.

• 대한기계학회논문집A
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• 제29권10호
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• pp.1289-1297
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• 2005

The flow in a microchannel is usually characterized as a low Reynolds number (Re) so that good mixing is quite difficult to be achieved. In this regard, we developed a novel chaotic micromixer, named Serpentine Laminating Micromixer (SLM) in the present study, Part 1. In the SLM, the higher level of chaotic mixing can be achieved by combining two general chaotic mixing mechanisms: splitting/recombination and chaotic advection. The splitting and recombination (in other term, lamination) mechanism is obtained by the successive arrangement of 'F'-shape mixing units in two layers. The chaotic advection is induced by the overall three-dimensional serpentine path of the microchannel. Chaotic mixing performance of the SLM was fully characterized numerically. To compare the mixing performance, a T-type micromixer which has the same width, height and length of the SLM was also designed. The three-dimensional numerical mixing simulations show the superiority of the SLM over the T-type micromixer. From the cross-sectional simulation results of mixing patterns, the chaotic advection effect from the serpentine channel path design acts favorably to realize the ideal lamination of fluid flow as Re increases. Chaotic mixing mechanism, proposed in this study, could be easily integrated in Micro-Total-Analysis-System, Lab-on-a-Chip and so on.

• 전자공학회논문지SC
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• 제42권1호
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• pp.33-37
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• 2005

마이크로믹서는 Bio-MEMS 혹은 μ-TAS 분야에서 중요한 역할을 수행한다. 혼합은 두 유체의 난류 상태와 상호확산에 의해 발생된다. 마이크로채널 내에서는 레이놀즈수가 작기 때문에 (Re << 2000) 난류가 발생되기 어려우므로 주로 상호확산에 의해서만 혼합된다. 따라서 두 유체가 적정하게 혼합되기 위해서는 긴 채널이 요구된다. 본 논문에서는 혼합에 소요되는 길이를 줄이기 위해서 PMN-PT에 의해 발생된 초음파에 의해 혼합되는 새로운 믹서를 제안하였다. 챔버 내에 발생된 초음파는 두 유체에 의해 생성된 경계면과 수직한 방향으로 방사된다. 사용된 두 유체는 상하방향으로 경계층을 이룬다. 혼합 상태는 NaOH와 페놀프탈렌의 반응에 따른 색상 변화론 관찰하여 측정하였다.

• 한국추진공학회지
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• 제6권1호
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• pp.21-29
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• 2002

하이브리드 연소 시스템은 안정된 작동조건이나 안전성 면에서 많은 장점을 가지고 있는 반면 기존의 하이브리드 모터는 고체 추진 로켓모터보다 낮은 연료 regression율과 연소효율은 갖는 단점이 있다. 따라서 최근의 연구들은 하이브리드 로켓모터의 연소실 체적의 제한과 연료의 regression율을 향상시키는데 그 초점을 맞추고 있다. 본 연구는 하이브리드 로켓 엔진의 연소과정을 수치적으로 해석하였다. 난류연소는 eddy breakup 모델을 이용하였으며 soot의 생성 및 산화를 다루기 위하여 Hiroyasu와 Nagle and Strickland-Constable 모델을 적용하였다. 복사열전달은 유한체적법을 이용하여 계산하였으며 고체 연료 벽면에서의 분출 효과로 야기되는 대류열전달의 불확실성을 줄이기 위하여 낮은 레이놀즈 수 $\kappa-\varepsilon$ 난류모델을 적용하였다. 계산된 수치결과를 토대로 선회 유동을 가지는 하이브리드 로켓 엔진의 난류연소과정에 대하여 상세히 기술하였다.

• International Journal of Naval Architecture and Ocean Engineering
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• 제8권4호
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• pp.330-343
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• 2016

This paper presents results of an experimental investigation of vortex-induced vibration (VIV) of a flexibly mounted and rigid cylinder with two-degrees-of-freedom with respect to varying ratio of in-line natural frequency to cross-flow natural frequency, $f^*$, at a fixed low mass ratio. Combined in-line and cross-flow motion was observed in a sub-critical Reynolds number range. Three-dimensional displacement meter and tension meter were used to measure dynamic responses of the model. To validate the results and the experiment system, x and y response amplitudes and ratio of oscillation frequency to cross-flow natural frequency were compared with other experimental results. It has been found that the higher harmonics, such as third and more vibration components, can occur on a certain part of steel catenary riser under a condition of dual resonance mode. In the present work, however, due to the limitation of a size of circulating water channel, the whole test of a whole configuration of the riser at an adequate scale for VIV phenomenon was not able to be conducted. Instead, we have modeled a rigid cylinder and assumed that the cylinder is a part of steel catenary riser where the higher harmonic motions could occur. Through the experiment, we have found that even though the cylinder was assumed to be rigid, the occurrence of the higher harmonic motions was observed in a small reduced velocity ($V_r$) range, where the influence of the in-line response is relatively large. The transition of the vortex shedding mode from one to another was examined by using time history of x and y directional displacement over all experimental cases. We also observed the influence of in-line restoring force power spectral density with $f^*$.

• 한국정밀공학회지
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• 제29권2호
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• pp.214-221
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• 2012

Recently, the biochip which is a prime representation of NT, IT, BT, as an example of convergence technology, has been frequently mentioned. With the recent rapid advance in biotechnology, these compact devices, such as lab-on-a-chip or u-TAS, have been developed, and more research is needed. These compact devices typically use the micro-channel in order to shed or detach and mix a variety of materials. Specially, in micro-fluidic systems, a mixer is necessary to produce a mixture because only laminar flow occurs at a low-Reynolds number. To solve this problem, HVM a micromixer that induces a horizontal and vertical multi-mixing flow motion, is proposed. The mixing performance was analyzed and verified by optimizing the shape through the CFD analysis and evaluating the structural analysis and the soundness with material properties that are obtained through the basic experiment.

• 한국항공우주학회지
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• 제44권9호
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• pp.759-768
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• 2016

고고도 장기체공 태양광 무인기 EAV-3의 프로펠러를 설계하고 전산해석을 수행하였다. 실험설계법(Design of Experiment, DOE)을 사용하여 설계변수들의 실험점들을 획득하고 목적함수와 구속함수들에 대한 크리깅 근사모델을 생성하였다. 요구조건 및 제약조건들과 함께 반응면을 평가하여 프로펠러 형상을 설계하였으며, 근사모델 기반의 최적설계를 수행하여 설계의 타당성을 검증하였다. 상용 CFD 코드를 이용하여 해석을 수행하고 그 결과를 설계코드 및 시험결과와 비교하였다. 설계점 고도에서 해석 결과가 설계코드의 예측과 잘 일치하였다. 또한 시험장치와 지지대 기둥에 의한 폐쇄효과가 풍동시험 결과에 포함되어 있으며, 이를 포함한 해석 결과가 시험 결과와 잘 일치함을 확인하였다.

• 한국항공우주학회지
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• 제37권10호
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• pp.975-983
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• 2009

본 논문은 동축반전 로터 블레이드의 성능 특성 파악을 위한 선행연구로서, 단일 로터 블레이드에 대한 공력 데이터 획득 및 성능 특성을 확인하기 위한 연구에 중점을 두었다. 이를 위해 제자리 비행 상태에서 추력과 토크의 측정이 가능한 소형 로터 블레이드용 회전 시험장치를 구성하고 제작하였다. 로터 회전 시험장치는 회전장치부, 센서부, 그리고 데이터 획득 시스템으로 구성되었으며, 고정된 회전속도에서 콜렉티브 피치각을 변화시키면서 추력과 토크를 측정할 수 있도록 하였다. 이를 통하여 저 레이놀즈 수 ($Re{\approx}3{\times}10^5$) 영역에서 운용되는 단일 로터의 제자리 비행 성능 시험을 수행하였고 소형 로터 블레이드의 제자리 비행 성능을 획득하여 로터 회전 시험장치의 성능을 검증하였다.