• Advances in aircraft and spacecraft science
• /
• 제4권4호
• /
• pp.353-369
• /
• 2017

Flutter is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces. This includes aircraft, buildings and bridges. Flutter occurs as a result of interactions between aerodynamic, stiffness, and inertia forces on a structure. In an aircraft, as the speed of the flow increases, there may be a point at which the structural damping is insufficient to damp out the motion which is increasing due to aerodynamic energy being added to the structure. This vibration can cause structural failure, and therefore considering flutter characteristics is an essential part of designing an aircraft. Scientists and engineers studied flutter and developed theories and mathematical tools to analyze the phenomenon. Strip theory aerodynamics, beam structural models, unsteady lifting surface methods (e.g., Doublet-Lattice) and finite element models expanded analysis capabilities. Periodic Structures have been in the focus of research for their useful characteristics and ability to attenuate vibration in frequency bands called "stop-bands". A periodic structure consists of cells which differ in material or geometry. As vibration waves travel along the structure and face the cell boundaries, some waves pass and some are reflected back, which may cause destructive interference with the succeeding waves. This may reduce the vibration level of the structure, and hence improve its dynamic performance. In this paper, for the first time, we analyze the flutter characteristics of a wing with a periodic change in its sandwich construction. The new technique preserves the external geometry of the wing structure and depends on changing the material of the sandwich core. The periodic analysis and the vibration response characteristics of the model are investigated using a finite element model for the wing. Previous studies investigating the dynamic bending response of a periodic sandwich beam in the absence of flow have shown promising results.

• 상하수도학회지
• /
• 제23권6호
• /
• pp.789-797
• /
• 2009

The flow in the beginning lateral sewer can be characterized as intermittent and unsteady, and a moment maximum flow energy is required to transport fecal solids in the sewer. It is thus difficult to design to satisfy a minimum velocity criteria (0.6m/s), because of the substantially lower discharge in the beginning lateral sewer. This study is the result of a field survey, and aims to determine a design criteria for the minimum slope to prevent sediment in a lateral sewer. The survey performed on the two flat small catchments in Goyang-si consisting of D400mm hume-pipe, aimed to understand the manner in which the scope of a sewer slope has an effect on sediment in the beginning lateral sewer. The survey showed that the sewer slope below 3‰ had sedimentation of 88.7%, while the sewer slope of 3~6‰ had sedimentation of 47.8%. In addition, the minimum design slope was estimated to refer to the result of hydraulic experiments from Public Works Research Institute in Japan. Analysis showed that the D400mm hume pipe should be installed with a slope of 6.5‰ to prevent sediment in the beginning lateral sewer. For future installations, the study results showed that a D300mm plastic pipe requires a minimum slope of 3.5‰, and a D250mm plastic pipe requires a minimum slope of 3.3‰ in the beginning lateral sewer.

• 대한전기학회:학술대회논문집
• /
• 대한전기학회 2009년도 제40회 하계학술대회
• /
• pp.1070_1071
• /
• 2009

Recently, small hydropower attracts attention because of its clean, renewable and abundant energy resources to develop. Therefore, a cross-flow hydraulic turbine is proposed for small hydropower development in this study. The turbine‘s simple structure and high possibility of applying to the sites of relatively low effective head and large flow rate can be advantages for the introduction of the small hydropower development. The purpose of this study is not only to investigate the effects of air layer in the turbine chamber on the performance and internal flow of the cross-flow turbine, but also to suggest a newly developed air supply method. CFD analysis for the performance and internal flow of the turbine is conducted by an unsteady state calculation using a two-phase flow model in order to embody the air layer effect on the turbine performance effectively. The result shows that air layer effect on the performance of the turbine is considerable. The air layer located in the turbine runner passage plays the role of preventing a shock loss in the runner axis and suppressing a recirculation flow in the runner. The location of air suction hole on the chamber wall is very important factor for the performance improvement. Moreover, the ratio between air from suction pipe and water from turbine inlet is also significant factor of the turbine performance.

• International Journal of Naval Architecture and Ocean Engineering
• /
• 제9권6호
• /
• pp.641-654
• /
• 2017

The KVLCC2 and its modified hull form were investigated in regular head waves using Unsteady Reynolds Averaged Navier-Stokes (URANS) methods. The modified KVLCC2 (named KWP-bow KVLCC2) is designed for reducing wave reflection from the bow. Firstly, the original KVLCC2 is studied for verification of the present code and methodology and the computed time history of total resistance and 2DOF motions (heave and pitch) for the selected two wave length conditions are directly compared with the results obtained from KRISO towing tank experiment under the identical condition. The predicted added resistance, heave and pitch motion RAOs show relatively good agreement with the experimental results. Secondly, the comparison of performance in waves between KVLCC2 and KWP-bow KVLCC2 is carried out. We confirmed that newly designed hull form shows better performances in all the range of wave length conditions through both the computation and the experiment. The present URANS method can capture the difference of performance in waves of the two hull forms without any special treatment for short wave length conditions. It can be identified that KWP-bow KVLCC2 gives about 8% of energy saving in sea state 5 condition.

• 한국가스학회지
• /
• 제5권3호
• /
• pp.1-8
• /
• 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.

• 한국수자원학회논문집
• /
• 제52권5호
• /
• pp.373-380
• /
• 2019

본 연구에서는 상수도관망의 피해율 저감을 위한 최적의 펌프운영기법을 제안하였다. 펌프운영시스템은 효과적인 펌프운영을 위하여 개발되었다. 이를 위해 펌프와 소통할 수 있는 압력센서가 상수도관망의 관말단부에 설치되었다. 펌프운영시스템은 관말단의 센서로 부터 수신된 데이터를 통하여 펌프를 제어하게 된다. 따라서 펌프운영시스템은 관말단부에 충분한 유량을 전달할 수 있는 압력을 유지할 수 있고 불필요한 압력을 줄일 수 있다. 펌프운영시스템의 효과를 입증하기 위해 신뢰성해석모형이 사용되었고 기존의 펌프운영시스템과 새로운 펌프운영시스템의 운영결과를 통하여 상수도관의 파괴확률을 정량적으로 비교하였다. 이를 위해서 부정류해석을 수행하였고 그 결과는 파괴확률을 산정하는데 사용되었다. 그 결과, 새로 제시된 펌프운영시스템은 상수도관의 파괴확률을 현저히 낮출 수 있음을 확인할 수 있었다.

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