• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.225-227
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• 2011

The geometrically sub-scaled wall-injection test model was employed to visualize interactions of internal flow of a solid rocket motor equipped fin/slot grain and submerged nozzle. Symmetric vortex and circumferential flow patterns were visualized.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.1
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• pp.44-53
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• 2004

This paper is to investigate the combustion characteristics with a three dimensional chemical reacting flow on the aspect ratio of an exit configuration of the slit type nozzle for the fuel injection and to device the methods of combustion／mixing enhancement. The results show that both inside inflow and slit side vertices should be considered from a viewpoint of the mixing. The combustion efficiency becomes the smallest at aspect ratio, where the aspect ratio is less and more than unity, respectively. The total pressure loss becomes the largest at aspect ratio of unity due to the high penetration. All results imply that a streamwise very long slit is desirable with respect to the combustion and the pressure loss.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.38 no.4
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• pp.365-371
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• 2014

A numerical simulation was conducted for the combustion chamber of a 4-step grate-firing boiler for wood pellet fuel. The flame is extended to the exit of combustion chamber, which is reproduced by present numerical method based on a homogeneous reaction model. Flow field from the simulation shows a strong recirculation flow at the upstream corner of the chamber, along which the flame is extended to the exit. These combustion and flow characteristics remain unchanged for partial load operations, which suggest modification of the combustion chamber structure rather than resizing should be effective to improve combustion characteristics. Possible modifications for combustion chamber are suggested such as relocating its exit, increasing the number of grate steps or installing internals such as guide baffles.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.10a
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• pp.49-52
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• 2002

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2001.11a
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• pp.70-72
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• 2001

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.14-14
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• 1998

램제트 엔진은 초음속에서 공기가 충격파를 통해 아음속으로 속도가 낮아지고 압력이 증가하는 램 압축 현상을 이용하되 압축기를 사용하지 않고 아음속 상태에서 연소하는 구조로 되어 있다. 따라서 각 부품의 성능은 독립적이지 않으며 전체적인 성능을 규명하기 위해서는 공기 흡입구와 연소실, 연료 분사체계 등의 상호작용을 고려하여 유동의 특성과 그에 따른 연소현상의 특성을 함께 고려해야만 한다. 본 연구에서는 속도 범위 Mach 5이내, 고도 30km이내의 운항조건을 갖는 유도 무기에 장착될 램제트 엔진 개발을 위한 연구의 첫 번째 단계로써, 램제트 연소실내의 유동장해석을 실험과 수치해석 두 분야로 나누어 수행하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.460-466
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• 2010

단일 알루미늄의 연소 모델을 사용하여 알루미늄 분말의 점화 과정에 대한 전산유체 해석 기법을 개발하였다. 유동의 계산은 Reynolds averaged Navier-Stokes식을 사용하였으며, $k-{\epsilon}$ 난류모델을 적용하였다. 입자는 Eulerian-Lagrangian 방법을 사용하여 유동과 독립적으로 계산을 수행하였으며 상용 전산유체해석 프로그램인 Fluent 6.3을 사용하여 해석을 수행하였다. 단일 모델에서 사용한 대류 및 복사 열전달, 표면이상반응, 알루미늄의 용융열을 입자 가열원으로 고려하였다. 같은 조건을 사용하여 단일 입자 모델 계산과 전산유체해석을 수행하였으며, 두 결과는 5% 이내로 잘 일치 하였다. 이를 통해 전산유체해석에서 알루미늄의 점화를 모사할 수 있음을 확인하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.363-366
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• 2011

Mixing and combustion experiments with a vent slot mixer were performed in Mach 2 supersonic wind tunnel. Helium and hydrogen gases each were used for the mixing and the combustion experiment with a plasma jet (PJ) torch. The vent slot mixer holds plenty of fuel in the downstream mixing region, even though the fuel is transversely injected. In case of the combustion, the injected fuel is ignited by the PJ torch, and then unburned mixture is burned by shock-induced combustion downstream. Thermal choking in the combustor leads to shock trains in the isolator, causing the unstable combustion.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.536-542
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• 2017

A great deal of difficulty is encountered in the thermo-mechanical analyses of nozzle assembly for solid propellant rocket motors. The main issue in this paper is the modeling of the boundary conditions and the connections between the various components-gaps, relative movements of the components, contacts, friction, etc. This paper evaluated the complex phenomena of nozzle assembly during burning time with co-simulation which include fluid, thermal surface reaction/ablation and structural analysis. The validity of this approach was verified by comparison of analysis results with measured strains.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.4
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• pp.36-43
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• 2018

A great deal of difficulty is encountered in the thermo-mechanical analyses of nozzle assemblies for solid propellant rocket motors. The main issue in this paper is the modeling of the boundary conditions and the connections between the various components-gaps, relative movements of the components, contacts, friction, etc. This paper evaluates the complex phenomena of nozzle assemblies during burning time with co-simulations that include fluid, thermal surface reaction/ablation, and structural analysis. The validity of this approach is verified via comparison of analysis results with measured strains.