• 한국유체기계학회 논문집
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• 제17권1호
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• pp.35-40
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• 2014

A multi-objective optimization of a regenerative fan for enhancing the aerodynamic and aeroacoustic performance was carried out using an integrated fan design system, namely, Total FAN-Regen$^{(R)}$. The Total FAN-Regen$^{(R)}$ was developed for non-specialists to carry out a series of design process, viz., computational preliminary design, three-dimensional aerodynamic and aeroacoustic analyses, and design optimization, for a regenerative fan. An aerodynamic analysis of the regenerative fan was conducted by solving three-dimensional Reynolds-averaged Navier-Stokes equations using the shear stress transport turbulence model. And, an aeroacoustic analysis of the regenerative fan was implemented in a finite/infinite element method by solving the variational formulation of Lighthill's analogy based on the results of the unsteady flow analysis. An optimum shape obtained by Total FAN-Regen$^{(R)}$ shows the enhanced efficiency and decreased sound pressure level as much as 1.5 % and 20.0 dB, respectively, compared to those of the reference design. The performance test was carried out for an optimized regenerative fan to validate the performance of the numerically predicted optimal design.

• Asian Journal of Atmospheric Environment
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• 제10권4호
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• pp.179-189
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• 2016

Here we evaluated the effect of using water retentive pavement or WRP made from fly ash as material for main street in a real city block. We coupled computational fluid dynamics and pavement transport (CFD-PT) model to examine energy balance in the building canopies and ground surface. Two cases of 24 h unsteady analysis were simulated: case 1 where asphalt was used as the pavement material of all ground surfaces and case 2 where WRP was used as main street material. We aim to (1) predict diurnal variation in air temperature, wind speed, ground surface temperature and water content; and (2) compare ground surface energy fluxes. Using the coupled CFD-PT model it was proven that WRP as pavement material for main street can cause a decrease in ground surface temperature. The most significant decrease occurred at 1200 JST when solar radiation was most intense, surface temperature decreased by $13.8^{\circ}C$. This surface temperature decrease also led to cooling of air temperature at 1.5 m above street surface. During this time, air temperature in case 2 decreased by $0.28^{\circ}C$. As the radiation weakens from 1600 JST to 2000 JST, evaporative cooling had also been minimal. Shadow effect, higher albedo and lower thermal conductivity of WRP also contributed to surface temperature decrease. The cooling of ground surface eventually led to air temperature decrease. The degree of air temperature decrease was proportional to the surface temperature decrease. In terms of energy balance, WRP caused a maximum increase in latent heat flux by up to $255W/m^2$ and a decrease in sensible heat flux by up to $465W/m^2$.

• 플랜트 저널
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• 제15권4호
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• pp.36-42
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• 2019

최근 환경 규제 정책 강화에 따른 입지 제약발생으로 발전소 부지가 높아지고 냉각수 관로의 길이가 증가되어 냉각수 계통 내 수격현상이 심화된다. 이는 발전소 안정성에 심각한 영향을 주게 된다. 본 연구에서는 수두가 높은 1,000 MW급 대용량 석탄화력발전소 냉각수계통에 대한 안정성을 확보하고자 비정상상태 1차원 해석 상용 소프트웨어인 LIQT 7.2을 사용하여 과도현상을 분석하고, 수격현상을 저감하기 위해 수격방지장치를 개별 및 조합 적용하여 성능특성에 대한 효과를 예측하였다. 수격방지 장치를 설치하지 않고 펌프가 불시 정지되었을 경우 발생하는 냉각수 서지압력은 펌프 출구 측에서 가장 크게 나타났다. 이러한 냉각수계통의 서지압력을 저감시키는 가장 효과적이고 간단한 방법은 펌프 보호를 위해 필수적 장치인 유압구동역류방지밸브에 진공파괴밸브를 조합한 것이다.

• 한국가스학회지
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• 제5권3호
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• pp.1-8
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• 2001

본 연구는 한국가스공사에서 운영중인 천연가스 공급관리소의 가스히터를 대상으로 겨울철 히터 가동 중단시, 가스히터 내부의 열전달 매체액 (Bath Water)이 빙점에 도달하는 시간을 계산하여 보수주기에 대한 결정 및 동파 취약 부위에 대한 영향을 판단하기 위해 가스히터의 체적을 고려한 비선형 3차원 전산모사를 수행하였다. 이용된 시뮬레이터는 미국 FLUENT사의 FLUENT V 5.0으로서 열유체 유동해석 범용 Code이다. 본 문제는 열전도에 관한 문제로 에너지 방정식을 푸는 방식으로 진행되지만 가스히터의 체적을 고려한 3차원 계산을 수행하기 위해 현장의 가스히터 형상 및 축적을 거의 유사하게 모델링하였고 표면에서 공기에 의한 대류 (Convection)문제와 단열재 사이의 전달 (Conduction)문제, 히터내부 액체의 자연대류 (Natural Convection) 그리고 배관을 통한 열손실의 문제를 고려한 복합적인 열전달 현상을 분석하였다.

• Current Research on Agriculture and Life Sciences
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• 제33권2호
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• pp.41-47
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• 2015

본 연구는 온실용 피복재 및 보온재의 조합에 대한 시뮬레이션 해석모델을 개발하여 관류열전달계수를 산정하고 측정된 결과와 비교하여 타당성을 평가하기 위해 수행되었으며 결과를 요약하면 다음과 같다. 유리이중피복의 경우 이중피복 사이의 공기층이 두꺼워짐에 따라 관류열전달계수가 서서히 작아져서 공기층 두께가 25 mm 이상이 되면 관류열전달계수의 변화가 거의 없는 것을 확인할 수 있었다. 또한 온도차가 증가함에 따라 관류열전달계수도 증가하는 것을 확인할 수 있었다. 두 플라스틱 피복재 사이에는 대류에 의한 열전달이 활발하게 일어나기 때문에 비정상 유동에 의한 열전달이 발생하고 이로 인해 온도분포도 비선형적으로 변하는 것으로 사료된다. 플라스틱 피복재 및 보온재들의 간격이 50~200 mm범위에서 변화할 때에 피복재의 간격은 관류열전달계수 큰 영향을 미치지 않는다는 사실을 확인할 수 있었다. 천공복사를 고려한 경우와 고려하지 않은 경우 모두 핫박스의 내외부 온도차가 $30^{\circ}C$인 조건에 대해서는 수치해석결과와 실험결과가 대체로 잘 일치하였다. 따라서 핫박스의 내외부 온도차가 $30^{\circ}C$ 이상인 조건에서 수치해석을 통해 관류열전달계수를 산정한다면 신뢰성 있는 값을 얻을 수 있을 것으로 판단된다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.91-93
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• 2003

A comprehensive numerical study is carried out to investigate for the understanding of the flow evolution and flame development in a supersonic combustor with normal injection of ncumally injecting hydrogen in airsupersonic flows. The formulation treats the complete conservation equations of mass, momentum, energy, and species concentration for a multi-component chemically reacting system. For the numerical simulation of supersonic combustion, multi-species Navier-Stokes equations and detailed chemistry of H2-Air is considered. It also accommodates a finite-rate chemical kinetics mechanism of hydrogen-air combustion GRI-Mech. 2.11[1], which consists of nine species and twenty-five reaction steps. Turbulence closure is achieved by means of a k-two-equation model (2). The governing equations are spatially discretized using a finite-volume approach, and temporally integrated by means of a second-order accurate implicit scheme (3-5).The supersonic combustor consists of a flat channel of 10 cm height and a fuel-injection slit of 0.1 cm width located at 10 cm downstream of the inlet. A cavity of 5 cm height and 20 cm width is installed at 15 cm downstream of the injection slit. A total of 936160 grids are used for the main-combustor flow passage, and 159161 grids for the cavity. The grids are clustered in the flow direction near the fuel injector and cavity, as well as in the vertical direction near the bottom wall. The no-slip and adiabatic conditions are assumed throughout the entire wall boundary. As a specific example, the inflow Mach number is assumed to be 3, and the temperature and pressure are 600 K and 0.1 MPa, respectively. Gaseous hydrogen at a temperature of 151.5 K is injected normal to the wall from a choked injector.A series of calculations were carried out by varying the fuel injection pressure from 0.5 to 1.5MPa. This amounts to changing the fuel mass flow rate or the overall equivalence ratio for different operating regimes. Figure 1 shows the instantaneous temperature fields in the supersonic combustor at four different conditions. The dark blue region represents the hot burned gases. At the fuel injection pressure of 0.5 MPa, the flame is stably anchored, but the flow field exhibits a high-amplitude oscillation. At the fuel injection pressure of 1.0 MPa, the Mach reflection occurs ahead of the injector. The interaction between the incoming air and the injection flow becomes much more complex, and the fuel/air mixing is strongly enhanced. The Mach reflection oscillates and results in a strong fluctuation in the combustor wall pressure. At the fuel injection pressure of 1.5MPa, the flow inside the combustor becomes nearly choked and the Mach reflection is displaced forward. The leading shock wave moves slowly toward the inlet, and eventually causes the combustor-upstart due to the thermal choking. The cavity appears to play a secondary role in driving the flow unsteadiness, in spite of its influence on the fuel/air mixing and flame evolution. Further investigation is necessary on this issue. The present study features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the previous works. In particular, the oscillatory flow characteristics are captured at a scale sufficient to identify the underlying physical mechanisms. Much of the flow unsteadiness is not related to the cavity, but rather to the intrinsic unsteadiness in the flowfield, as also shown experimentally by Ben-Yakar et al. [6], The interactions between the unsteady flow and flame evolution may cause a large excursion of flow oscillation. The work appears to be the first of its kind in the numerical study of combustion oscillations in a supersonic combustor, although a similar phenomenon was previously reported experimentally. A more comprehensive discussion will be given in the final paper presented at the colloquium.