• 한국유체기계학회 논문집
• /
• 제8권4호
• /
• pp.27-38
• /
• 2005

The present study investigated the effect of relative position of the blade on blade surface heat transfer. The experiments were conducted in a low speed wind tunnel with a stationary annular turbine cascade. The test section has a single turbine stage composed of sixteen guide vanes and blades. The chord length of the blade is 150 mm and the mean tip clearance of the blade is $2.5\%$ of the blade chord. The Reynolds number based on blade inlet velocity and chord length is $1.5{\times}105$ and mean turbulence intensity is about $3\%$. To investigate the effect of relative position of blade, the blade at six different positions in a pitch was examined. For the detailed mass transfer measurements, a naphthalene sublimation technique was used. In general, complex heat transfer characteristics are observed on the blade surface due to various flow characteristics, such as a laminar flow separation, relaminarization, flow acceleration, transition to turbulence and tip leakage vortices. The results show that the blade relative position affects those heat transfer characteristics because the distributions of incoming flow velocity and turbulence intensity are changed. Especially, the heat transfer pattern on the near-tip region is significantly affected by the relative position of the blade because the effect of tip leakage vortex is strongly dependent on the blade position. On the pressure side, the effect of blade position is not so significant as on the suction side surface although the position and the size of the separation bubble are changed.

• International Journal of Fluid Machinery and Systems
• /
• 제2권4호
• /
• pp.439-448
• /
• 2009

Three inducers were designed to avoid cavitation instabilities. This was accomplished by avoiding the interaction of tip cavity with the leading edge of the next blade. The first one was designed with extremely larger leading edge sweep, the second and third ones were designed with smaller incidence angle by reducing the inlet blade angle or increasing the design flow rate, respectively. The inducer with larger design flow rate has larger outlet blade angle to obtain sufficient pressure rise. The inducer with larger sweep could suppress the cavitation instabilities in higher flow rates more than 95% of design flow coefficient, owing to weaker tip leakage vortex cavity with stronger disturbance by backflow vortices. The inducer with larger outlet blade angle could avoid the cavitation instabilities at higher flow rates, owing to the extension of the tip cavity along the suction surface of the blade. The inducer with smaller inlet blade angle could avoid the cavitation instabilities at higher flow rates, owing to the occurrence of the cavity first in the blade passage and its extension upstream. The cavity shape and suction performance were reasonably simulated by three dimensional CFD computations under the steady cavitating condition, except for the backflow vortex cavity. The difference in the growth of cavity for each inducer is explained from the difference of the pressure distribution on the suction side of the blades.

• 한국유체기계학회 논문집
• /
• 제13권5호
• /
• pp.43-53
• /
• 2010

This study investigates a design optimization of a rotating two-pass rectangular cooling channel with staggered arrays of pin-fins. The radial basis neural network method is used as an optimization technique with Reynolds-averaged Navier-Stokes analysis of fluid flow and heat transfer with shear stress transport turbulent model. The ratio of the diameter to height of the pin-fins and the ratio of the streamwise spacing between the pin-fins to height of the pin-fin are selected as design variables. The optimization problem has been defined as a minimization of the objective function, which is defined as a linear combination of heat transfer related term and friction loss related term with a weighting factor. Results are presented for streamlines, velocity vector fields, and contours of Nusselt numbers, friction coefficients, and turbulent kinetic energy. These results show how fluid flow in a two-pass square cooling channel evolves a converted secondary flows due to Coriolis force, staggered arrays of pin-fins, and a $180^{\circ}$ turn region. These results describe how the fluid flow affects surface heat transfer. The Coriolis force induces heat transfer discrepancy between leading and trailing surfaces, having higher Nusselt number on the leading surface in the second pass while having lower Nusselt number on the trailing surface. Dean vortices generated in $180^{\circ}$ turn region augment heat transfer in the turning region and in the upstream region of the second pass. As the result of optimization, in comparison with the reference geometry, thermal performance of the optimum geometry shows the improvement by 30.5%. Through the optimization, the diameter of pin-fin increased by 14.9% and the streamwise distance between pin-fins increased by 32.1%. And, the value of objective function decreased by 18.1%.

• 한국해안해양공학회지
• /
• 제19권5호
• /
• pp.484-491
• /
• 2007

규칙파와 수면아래 잠긴 수평판 사이의 비선형 상호작용을 규명하기 위하여 수치파동수조를 이용하여 수치 실험을 수행하였다. 수치모델로 비선형 포텐셜 이론을 근거로 한 고차 경계요소법과 Navier Stokes 방정식과 엄밀한 자유표면 경계조건식을 푸는 CADMAS-SURF을 사용하였다. 두 모델 모두 수평판 위의 천수역에서 발생하는 고차 조화항들을 예측할 수 있으며 점성효과를 포함하는 CADMAS-SURF는 수평판 양단에서 발생하는 와류와 박리에 의한 고차 조화항의 발생을 재현할 수 있다. 수평판의 잠긴 깊이와 길이 변화에 따른 반사율과 투과율을 Patarapanich and Cheong(1989)의 모형실험결과와 비교하였고 서로 잘 일치함을 확인하였다. 수평판의 길이가 길어지고 잠긴 깊이가 얕아질수록 입사파의 에너지가 고차 조화항으로 더 많이 전이됨을 확인하였다.

• 한국해양환경ㆍ에너지학회지
• /
• 제16권2호
• /
• pp.61-70
• /
• 2013

조류발전용 수직축터빈(VAT)의 3차원적인 유체동력학적 성능을 효과적으로 예측할 수 있는 연구를 진행하였다. 수치해석은 2차원과 3차원으로 수행하였으며 이를 통해 물리적 유동현상의 차이를 파악하였다. 3차원 효과는 주로 날개 끝단에서 발생하는 날개끝 보오텍스가 주된 원인으로서, 이로 인해 터빈 날개가 내어주는 양력이 손실되고 회전하는 터빈은 토크가 감소하였다. 이러한 현상은 본 연구에서 채택한 통상적인 수직축 터빈의 스팬-직경비 범위에서 상당한 수준으로 나타남을 확인하였다. 본 연구에서는 대상 터빈을 선정하고 2차원으로 성능해석 후 3차원 효과를 보정하는 비교적 간단하고 효과적인 방법을 제안하였다.

• 대한의용생체공학회:의공학회지
• /
• 제23권6호
• /
• pp.437-449
• /
• 2002

관상동맥은 체순환 동맥과 비교하여 매우 다른 유동조건을 갖는다. 본 연구에서는 이러한 관상동맥의 유동조건이 다른 혈관과 비교하여 동맥경화의 생성과 발전에 어떤 영향을 미치는지를 협착된 혈관 모델의 혈류역학적 전산유체해석을 통해 분석하였다. 연구 결과, 협착된 관상동맥 모델의 유동장과 벽면전단응력의 분포는 복부 대동맥 및 고동맥과 비교하여 큰 차이점을 보였다. 관상동맥은 혈관 지름이 혈류량에 비해 상대적으로 작으므로 큰 벽면전단응력값을 보이는 반면에, 혈관 협착부 목 후방부에 하나의 보텍스만 보이는 단순한 유동장 분포를 보였다. 한편, 복부대동맥과 고동맥 모델은 협착부 목 전반부와 후방부에 여러 개의 보텍스를 나타내는 복잡한 유동장을 형성하였다. 관상동맥 모델에서는 임피던스 페이즈앵글이 음의 큰 값을 가질 때에 벽면전단응력의 크기가 증가하고 재순환영역이 증가함이 관찰되었다. 그러므로 심장의 수축운동과 -110。에 이르는 관상동맥의 큰 음의 임피던스 페이즈앵글 값은 동맥경화를 촉진시키는 유동환경을 조성함을 알 수 있었다.

• 한국항공우주학회지
• /
• 제30권5호
• /
• pp.109-117
• /
• 2002

옆미끄럼이 있는 조건에서 LEX를 갖는 삼각날개의 와류 특성을 유동의 가시화에 의한 실험적 방법으로 연구하였다. 모델은 $65^{\circ}$ 후퇴각의 갖는 평판 날개이다. 자유 유동속도는 6.2 m/s이며, 이 속도와 날개뿌리 시위를 기준으로 한 레이놀즈 수는 $4.4\times10^5$ 이다. 받음각 범위와 옆미끄림각 범위는 각각 $16^{\circ}\sim28^{\circ}$와 $0^{\circ}\sim-15^{\circ}$ 이다. 미세수적과 레이저 평면광에 의한 가시화는 오공 프로브에 의한 측정으로부터 얻을 수 없었던 보다 자세한 와유동 구조를 관찰 할 수 있도록 하였다. 옆미끄럼각이 있는 경우, 바람쪽은 LEX 와류와 날개 와류의 상호작용과 붕괴가 촉진되는 반면, 바람반대쪽은 두 와류의 상호작용과 붕괴가 억제되었다.

• 대한기계학회논문집B
• /
• 제26권3호
• /
• pp.394-401
• /
• 2002

The instantaneous flow characteristics of a round jet issuing normally into a crossflow has been studied using a flow visualization technique and particle image velocimetry. The effects of parameters such as jet inflow profile and turbulence intensity of the jet are evaluated for various Reynolds numbers in range between 735 and 3150, which are based on the crossflow velocity and jet-pipe diameter. The jet-to-crossflow velocity ratio is fixed at the value of 3.3. Instantaneous later tomographic images of the symmetry plane of the crossflow jet show that there exist very different natures in the flow structures of the near-field of the jet even though the velocity ratio is same. It is found that when the turbulence intensity of jet is elevated, the shear layer becomes much thicker due to the strong entrainment of the ambient fluid by turbulent interaction between the jet and crossflow. The detailed characteristics of instantaneous velocity and vorticity fields are presented to illustrate the effects of the above parameters on the vertical structures of the crossflow jet.

• 대한기계학회논문집B
• /
• 제25권12호
• /
• pp.1821-1830
• /
• 2001

The flow around free end of a finite circular cylinder (FC) embedded in an atmospheric boundary layer has been investigated experimentally. The experiments were carried out in a closed-return type subsonic wind tunnel with varying aspect ratio of the finite cylinder mounted vertically on a flat plate. The wakes behind a 2-D cylinder and a finite cylinder located in a uniform flow were measured for comparison. Reynolds number based on the cylinder diameter was about Re=20,000. A hot-wire anemometer was employed to measure the wake velocity and the mean pressure distributions on the cylinder surface were also measured. The flow past the FC free end shows a complicated three-dimensional wake structure and flow phenomenon is quite different from that of 2-D cylinder. The three-dimensional flow structure was attributed to the downwashing counter rotating vortices separated from the FC free end. As the FC aspect ratio decreases, the vortex shedding frequency decreases and the vortex formation length increases compared to that of 2-D cylinder. Due to the descending counter-rotating twin-vortex, near the FC free end, regular vortex shedding from the cylinder is suppressed and the vortex formation region is hardly distinguished. Around the center of the wake, the mean velocity for the FC located in atmospheric boundary layer has large velocity deficit compared to that of uniform flow.

• 한국가시화정보학회지
• /
• 제16권1호
• /
• pp.30-36
• /
• 2018

In the present study, we investigate the flow characteristics of a quadrotor UAV in a hovering mode by measuring multiple two-dimensional velocity fields in the wake. The experiment is conducted at Re = 24,000 in a chamber large enough to neglect the ground effect, where Re is the Reynolds number based on the rotor chord length and the rotor tip speed. The rotational speed of the rotor is determined by an optical tachometer so that the lift force can be balanced with the weight of the UAV. The velocity field measured on the center plane of the rotor shows that the vortices are shedding from the tip of the rotor, inducing large fluctuations in the streamwise velocity along the wake shear layer. The strength of the rotor-tip vortex shedding is asymmetric with respect to the rotor axis due to the interaction between the rotor and the wake centerline of each rotor is inclined to the center of the UAV due to the pressure difference caused by the induced velocity. The wake from each rotor moves closer to each other while traveling in the streamwise direction, and then is merged together inducing large fluctuations in the transverse velocity. Due to the wake merging, on the center plane of the UAV, the velocity increases in the streamwise direction showing two-peak structure in the streamwise velocity contours.