• 설비공학논문집
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• 제18권3호
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• pp.193-201
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• 2006

Thermal performance model was developed for a cross-flow aluminum heat exchanger with relatively short passage. Appropriate heat transfer coefficient and friction factor equations for laminar channel flow were obtained considering developing regions. The heat exchanger was analyzed using the unmixed cross-flow ${\epsilon}$-NTU relationship considering leak-age between streams. Thermal contact between corrugations and plates was also considered. Tests were separately conducted for two samples - one made of non-treated aluminum sheets, and the other made of varnish-treated ones. The samples were made by stacking corrugations and plates one after another. The model adequately predicted the thermal performance and pressure drop of the non-treated heat exchanger. The thermal performance of the varnish-treated one was $7{\sim}12%$ overpredicted, and the pressure drop of the varnished-treated heat exchanger was $5{\sim}15%$ underpredicted. The air leakage ratio of the non-treated heat exchanger was $23{\sim}26%$. The ratio decreased to less than $10%$ with the varnish treatment.

• 한국해양환경ㆍ에너지학회지
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• 제4권4호
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• pp.21-31
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• 2001

바다에서 발생하는 유조선 등으로부터의 기름 유출사고는 해양환경을 크게 훼손하는 재앙에 속한다. 이러한 사고에 효과적으로 대응하기 위해서는 사고의 초기에 기름의 유출양을 정확히 판단하여 그에 적절한 대응방법을 수립하는 것이 필요하다. 기름 유출양의 추정을 위해서 사용되는 가장 간단한 방법은 토리첼리의 평형관계식을 사용하는 것이다. 하지만 이러한 평형관계식은 관성력과 점성력이 무시되었기 때문에 실제의 현상과는 다소 거리가 있다. 본 논문에서는 탱크로부터의 기름 유출양 산정을 위한 기초적인 실험과 수치계산을 수행하였다. 소형 유리 수조에 상자모양의 아크릴 기름탱크를 설치하고 종횡비가 다른 사각형의 유출구를 빠져나가는 기름의 양과 모양을 계측하였다. 그리고 유한체적법과 VOF법 등의 CFD 기술을 활용하여 기름과 물의 유동을 수치 시뮬레이션 하였다. CFD 계산견과는 실험에서 계측된 값과 좋은 일치를 보였으며, 복잡한 해난사고에서의 유출양 산정을 위한 CFD 기술의 활용가능성을 확인할 수 있었다. 본 논문의 실험조건에서 기름의 유출속도는 유출구의 형상에 따라 결정되는 유출구 내부의 마찰력에 의해 달라지며, 토리첼리 평형관계식으로부터 얻어지는 유출속도의 35~55%임을 알 수 있었고, 만약 유출구의 두께를 무시하면 종횡비에 상관없이 52%로 일정하게 추정되었다.

• 대한기계학회논문집B
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• 제31권1호
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• pp.68-75
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• 2007

A three-dimensional computation is conducted to simulate a three-dimensional rotating stall in a low speed axial compressor. It is generally known that a tip leakage flow has an important role on a stall inception. However, almost of researchers have taken no interest in a role of the hub-comer-stall on the rotating stall even though it is a common feature of the flow in an axial compressor operating near stall and it has a large effect on the flows and loss characteristics. Using a time-accurate unsteady simulation, it is found that the hub-comer-stall may be a trigger to collapse the axisymmetric flows under high loads. An asymmetric disturbance is initially originated in the hub-comer-stall because separations are naturally unstable flow phenomena. Then this disturbance is transferred to the tip leakage flows from the hub-comer-stall and grows to be stationary stall cells, which adheres to blade passage and rotate at the same speed as the rotor. When stationary stall cells reach a critical size, these cells then move along the blade row and become a short-length-scale rotating stall. The rotational speed of stall cells quickly comes down to 79 percent of rotor so they rotate in the opposite direction to the rotor blades in the rotating frame.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 춘계학술대회논문집B
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• pp.574-579
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• 2000

In this study. an off-design performance prediction program for centrifugal pumps is developed. To estimate the losses in an impeller flow passage, two-zone model and two-element in series(TEIS) model are used. At impeller exit. the mixing process occurs with an increase in entropy. In two-zone model. there are both primary zone and secondary zone for an isentropic core flow and an average of all non-isentropic streamtubes respectively. The level of the core flow diffusion in an impeller was calculated by using TEIS model. While internal losses in an impeller an automatically estimated by using the above models, some empirical correlations far estimating external losses. far example, disk friction loss, recirculation loss and leakage loss are used. In order to analyze the vaneless diffuser flow. the momentum equations for the radial and tangential directions are used and solved together with continuity and energy equations.

• 대한기계학회논문집B
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• 제40권10호
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• pp.645-651
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• 2016

본 연구에서는 압력면익단소익의 폭이 터빈 동익 압력면스퀼러팁 하류의 팁누설유동 및 압력손실에 미치는 영향에 대하여 연구하였다. 팁간극비 h/s = 1.36%에 대하여, 흡입면스퀼러의 높이는 $h_p/s=3.75%$로 일정하게 유지하고, 압력면익단소익의 폭은 w/p = 2.64%, 5.28%, 7.92%, 10.55% 등으로 변화시키면서 실험을 수행하였다. 일반적으로 압력면익단소익의 폭이 증가할수록, 통로와류 영역에서의 압력손실은 감소하였지만 팁누설유동 영역에서는 압력손실이 오히려 증가하였다. 그 결과 익단소익의 폭이 증가할수록, 질량평균 압력손실은 매우 소폭 감소하는 경향을 보였다. 본 연구 결과, 압력면스퀼러팁에 설치된 압력면익단소익은 압력손실 저감에 거의 기여를 하지 못함을 확인할 수 있었다.

• International Journal of Aeronautical and Space Sciences
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• 제16권2호
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• pp.157-164
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• 2015

The present work performs three-dimensional flow calculations based on Reynolds Averaged Navier-Stokes (RANS) and Delayed Detached Eddy Simulation (DDES) to investigate the flow field of a transonic rotor (NASA Rotor 37) at near-stall condition. It is found that the DES approach is likely to predict well the complex flow characteristics such as secondary vortex or turbulent flow phenomenon than RANS approach, which is useful to describe the flow mechanism of a transonic compressor. Especially, the DES results show improvement of predicting the flow field in the wake region and the model captures reasonably well separated regions compared to the RANS model. Besides, it is discovered that the three-dimensional vortical flows after the vortex breakdown from the rotor tip region are widely distributed and its vortex structures are clearly present. Near the rotor leading edge, a part of the tip leakage flows in DES solution spill over into next passage of the blade owing to the separation vortex flow and the backflow is clearly seen around the trailing edge of rotor tip. Furthermore, the DES solution shows strong turbulent eddies especially in the rotor hub, rotor tip section and the downstream of rotor trailing edge compared to the RANS solution.

• 항공우주기술
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• 제3권2호
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• pp.183-190
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• 2004

액체로켓용 연료펌프의 설계를 검증하기 위해 상용 3차원 유동해석 소프트웨어를 이용하여 설계점 성능을 예측하였다. 연료펌프의 성능과 축추력에 영향을 미치는 누설유량에 대한 예측의 정확도를 높이기 위해 인듀서, 임펠러, 볼류트 및 2차 유로를 계산영역으로 설정하였으며 인듀서/임펠러/누설유로/볼류트 사이의 경계면에 혼합면 기법을 적용하여 계산에 소요되는 시간을 줄이고자 하였다. 유동해석을 통해 예측된 수력성능은 설계요구조건을 만족시키는 것으로 나타났으나 축추력이 허용치에 비해 크게 예측되어 이를 감소시키기 위한 설계변경이 이루어졌다. 변경된 설계안에 대한 유동해석을 수행한 결과 연료펌프의 수력성능은 유지되면서 축추력은 처음의 설계안에 비해 30% 수준으로 크게 감소하였음을 확인할 수 있었다.

• 한국유체기계학회 논문집
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• 제14권1호
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• pp.48-54
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• 2011

The effect of channel cutback on three-dimensional flow fields and aerodynamic losses downstream of a cavity squealer tip has been investigated in a turbine rotor cascade for the squealer rim height-to-chord ratio and tip gap height-to-chord ratio of $h_{st}/c$ = 5.51% and h/c = 2.0% respectively. The cutback length-to-camber ratio is changed to be $CB/c_c$ = 0.0, 0.1, 0.2 and 0.3. The results show that longer cutback delivers not only stronger secondary flow but also higher aerodynamic loss in the tip leakage vortex region, meanwhile it leads to lower aerodynamic loss in the passage vortex region. The discharge of cavity fluid through the cutback opening provides a beneficial effect in the reduction of aerodynamic loss, whereas there also exists a side effect of aerodynamic loss increase due to local wider tip gap near the trailing edge. With increasing $CB/c_c$ from 0.0 to 0.3, the aerodynamic loss coefficient mass-averaged all over the measurement plane tends to increase slightly.

• 한국유체기계학회 논문집
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• 제15권6호
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• pp.5-10
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• 2012

The effect of pressure-side opening length on three-dimensional flow fields and aerodynamic losses downstream of a cavity squealer tip has been investigated in a turbine rotor cascade for the squealer rim height-to-chord ratio and tip gap height-tochord ratio of $h_{st}/c$ = 5.05% and h/c = 2.0% respectively. The opening length-to-camber ratio is changed to be $OL/c_c$ = 0.0, 0.1, 0.2, 0.3, 0.4, 0.5, and 0.7 The results show that longer OL leads not only to weaker secondary flow but also to lower aerodynamic loss in the tip leakage vortex region, while it significantly widens the area with high aerodynamic loss in the passage vortex region. The aerodynamic loss coefficient mass-averaged all over the measurement plane is kept almost constant for $0.0{\leq}OL/c_c{\leq}0.3$, whereas it increases rapidly for $OL/c_c$ > 0.3 in proportion to $OL/c_c$. There is little deterioration in flow turning with increasing $OL/c_c$.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2001년도 유체기계 연구개발 발표회 논문집
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• pp.264-270
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• 2001

The hydraulic performance analysis of an entire pump system composed of an inducer, impeller, volute and seal for the application on turbopumps is performed using three-dimensional Wavier-Stokes equations. A quasi-steady mixing-plane method is used on the impeller/volute interface to simulate the unsteady interaction phenomena. From this wort the effects of each component on the pump performance are investigated at design and off-design conditions through the analysis of flow structures and loss mechanisms. The computational results are in a good agreement with experimental ones in terms of the headrise and efficiency even though very complex flow structures are present. It is found that the asymmetric pressure distribution along the volute wall constitutes the main reason of the difference between experimental and computational results due to the limitation of the applying the quasi-steady method. Since the volute was found to be over-designed according to the pressure distribution of the volute wall, redesign of the volute has been performed resulting in an improved performance characteristic.