• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.17-17
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• 2000

이젝터-디퓨저 시스템은 고압의 기체를 노즐로 팽창시켜서 얻은 대량의 운동에너지를 이용하여 낮은 에너지를 가지는 주변의 기체를 외부로 배출시키는데 이용되는 유체 역학적 펌프이다. 이젝터-디퓨저 시스템은 작동부가 없고 구조가 단순하여 설치/보수 및 시스템 전체의 경량화에 많은 이점이 있으므로 그 활용도가 증대하고 있는 추세이다. 그러나 이젝터-디퓨저를 지나는 초음속 유동은 복잡한 충격파 및 난류현상들로 인하여 그 물리적 특성들이 명확히 알려지지 않았다. 특히 이러한 제현상들의 간섭과 전단층의 불안정성 때문에 발생하는 비정상성은 1차 유동과 2차 유동의 혼합작용에 영향을 미쳐, 결국 시스템 전체의 배기성능을 저하시킬 뿐만 아니라, 소음과 진동을 발생시켜 시스템의 안정적인 운전을 방해한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.8
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• pp.1-9
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• 2002

Axisymmetric separated flows in a converging-diverging conical nozzle are investigated through numerical simulations for various pressure ratios. We employ AUSM scheme for spatial derivatives and Pulliam's 2nd order subiteration time stepping scheme for implicit time integration. Numerical results indicate that the separated flow structures are very complex when compared to the simple quasi-one dimensional flow. Depending on the pressure ratio, the flow within the nozzle is either separated or non-separated. Various separated flow patterns with distinctive features are illustrated and discussed in detail.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.20 no.8
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• pp.2650-2669
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• 1996

A new low Reynolds number nonlinear second moment turbulence closure was introduced to analyze a square sectioned 180.deg. bend flow. Inclusion of nonlinear return to isotropy term and cubic mean pressure strain term has brought out a marked improvement in the level of agreement with measured velocity profiles. Optimization of present closure was performed by comparison of computed velocity profiles with the experimental ones with variation of nonlinear return to isotropy term and quadratic and cubic pressure-strain model. Progressive vortex breakdown due to the interaction of primary and secondary flows was well captured by using the optimized second moment turbulence closure.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.1
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• pp.34-46
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• 2020

Computational assessment of gas-dynamic characteristics is explored for a three-dimensional counter-flow thrust vector control system in a rectangular supersonic nozzle. This convergent-divergent nozzle is designed by Method of Characteristics and its design Mach number is specially set as 2.5. Performance variations of the counter-flow vector system are illustrated by varying the gap height of the secondary flow duct. Key parameters are quantitatively analyzed, such as static pressure distribution along the centerline of the upper suction collar, deflection angle, secondary mass flow ratio, and resultant thrust coefficient. Additionally, the streamline on the symmetry plane, three-dimensional iso-Mach number surface contour, and three-dimensional turbulent kinetic energy contour are presented to reveal overall flow-field characteristics in detail.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.99-102
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• 2009

LES(Large eddy simulation) of breakup and atomization of a liquid jet into cross turbulent flow was performed. Two phase flow between a gas phase and a liquid phase was modeled by a mixed numerical scheme of both Eulerian and Lagrangian methods for gas and liquid phases respectively. The first and second breakup of liquid column was observed. The penetration depth in cross flow was comparable with experimental data for several variant of a liquid-gas momentum flux ratio by varying liquid injection velocities. SMD(Sauter Mean Diameter) distribution downstream of jet was analyzed.

• Journal of Ocean Engineering and Technology
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• v.10 no.3
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• pp.44-49
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• 1996

후방계단(backward facting step) 주위의 난류 유동 특성을 수치 해석을 통해 파악하고자 하였다. 지배방정식은 2차 정도의 유한 차분 기법으로 이산화하였으며 비교차격자계를 사용하여 양해법으로 계산하였다. 난류 모형으로는 이층 모형(two-layer)을 사용하였고 압력 Poisson 방정식을 이용하여 압력과 속도를 연성 시켰다. Re=44,000인 경우에 대해 계산 결과로 부터 후방 계단 뒤의 속도 벡터, 유선, 압력 및 속도 분포, 재부착 길이(reattachment length)등의 실험치와 비교하였다. 본 계산에 사용한 수치 해석 기법은 박리등이 포함된 복잡한 난류 유동 현상을 잘 재현할 수 있음을 확인할 수 있었다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.19 no.9
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• pp.2271-2282
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• 1995

Numerical simulations for the effects of secondary flow and turbulence diffusion on the particle concentration distributions have been carried out for the single stage electrostatic precipitator. The electrohydrodynamic secondary flow, particle concentration distribution and collection efficiency have been evaluated as a function of dimensionless parameters such as Re, $N_{end}$, $P_{e}$ x. The results of simulations show that for increasing secondary flow intensity the concentration distribution is drastically deformed and collection efficiency is decreased which is more than due to turbulent diffusion.n.n.

• Transactions of the Korean Society of Mechanical Engineers
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• v.16 no.10
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• pp.1915-1927
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• 1992

A three-dimensional Navier-Stokes code has been developed for analysis of viscous flows through turbomachinery blade rows or other internal passages. The Navier-Stokes equations are written in a cartesian coordinate system, then mapped to a general body-fitted coordinate system. Streamwise viscous terms are neglected and turbulent effects are modeled using the baldwin-Lomax model. Equations are discretized using finite difference method on the stacked C-type grids and solved using LU-ADI decomposition scheme. calculations are made for a two-dimensional cascade in a transonic wind-tunnel to see the infuence of the endwalls. The flow pattern of the three-dimensional flow near the endwall is found to be different from that of the two-dimensional flow due to the existence of the endwalls.

• Proceedings of the KSME Conference
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• 2002.08a
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• pp.119-122
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• 2002

In general, Liquid Injection Thrust Vector Control(LITVC) is accomplished by injecting a liquid into the supersonic exhaust flow through holes in the wall of the propulsion nozzle. This injection flow field is highly complicated and detailed flow physics associated with the secondary flow injection should be known far the practical design and use of the LITVC system. The present study aims at understanding the LTTVC flow field and obtaining fundamental design parameters for LITVC. The experimentations were performed in a supersonic blow-down wind tunnel. Compressed, dry air was used for both the main exhaust and injection flows but the pressures of these two flows were controlled independently. The location of the injection holes was changed and the pressures of the two streams were also changed between 2.0 and 15.0 bar. The effectiveness of LITVC was discussed in details using the results of the pressure measurements and flow visualizations

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.1
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• pp.1-16
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• 2009

In this paper, we introduce two-phase versions of RoeM and AUSMPW+ schemes. Both schemes are originally developed for the gas dynamic problems, and have shown superior accuracy, efficiency and robustness. A new shock discontinuity sensing term is derived from the mixture equation of state, which is commonly used in the RoeM and AUSMPW+ schemes for the stable numerical flux calculation. The developed two-phase versions of the schemes are applied to several liquid-gas, large property discrepancy two-phase test problems, including several shock stability test problems. The results show that both schemes maintain the merits exhibited in gas dynamic problems even in two-phase flows.