• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.37 no.1
• /
• pp.62-68
• /
• 2009

The interaction between wall blowing and oxidizer flow can generate a very complicated flow characteristics in combustion chamber of hybrid rockets. LES analysis was conducted with an in-house CFD code to investigate the features of turbulent flow without chemical reactions. The numerical results reveal that the flow oscillations at a certain frequency exists on the fuel surface, which is analogous to those observed in the solid propellant combustion. However, the observation of oscillating flow at a certain frequency is only limited to a very thin layer adjacent to wall surface and the strength of the oscillation is not strong enough to induce the drastic change in temperature gradient on the surface. The visualization of fluctuating pressure components shows the periodic appearance of relatively high and low pressure regions along the axial direction. This subsequently results in the oscillation of flow at a certain fixed frequency. This implies that the resonance phenomenon would be possible if the external disturbances such as acoustic excitation could be imposed to the oscillating flow in the combustion chamber.

• Proceedings of the Korean Nuclear Society Conference
• /
• 1998.05a
• /
• pp.783-788
• /
• 1998

국내 프랑스 가압경수형 원전인 울진 1,2호기 캐비티의 격납건물 직접가열에 대한 특성을 분석하기 위하여 노심용융물 고압분출 실험을 수행하였다. 본 연구에서는 환형통로 면적과 파손 직경에 따라 원자로용기 압력을 변화시키면서 용융물을 저온 용융 합금물인 Wood's Metal, 증기를 질소기체로 각각 모의하여 실험을 수행하였으며, 실험 결과는 물을 용융물 상사물로 사용한 전년 실험 결과(1)와 비교.분석하였다. 실험결과, 밀도가 물보다 큰 저온 용융 합금물을 사용한 경우는 물을 사용한 실험결과보다 밀도와 용융물의 벽면 고화고착 때문에 격납건물로 방출되는 용융물 양이 적게 나타났다. 물을 상사물로 사용한 경우와 같이 노심 용융물 고압분출에는 원자로 용기 파손직경이 많은 영향을 미치고 환형통로 면적은 큰 영향을 미치지 않는 것으로 나타났다. 노심용융물 고압분출 실험에 중요한 영향을 미치는 실험 상사물의 밀도와 용융물의 벽면 고화부착에 대해서는 종합적으로 분석하는 추가 연구가 필요하다.

• Proceedings of the Korean Nuclear Society Conference
• /
• 1998.05a
• /
• pp.571-576
• /
• 1998

고온의 증기가 과냉각 상태의 물과 직접접촉에 의해 발생하는 응축현상(DCC Direct Contact Condensation)을 실험적으로 고찰하였다. 본 연구는 두단계로 나누어 수행하였다. 1단계 연구에서는 간단한 원형관 형태의 수평 노즐을 통하여 증기제트가 대기압 상태의 과냉각수로 분출될 때 증기제트 및 주위의 거동을 측정·분석하였다. 수조의 온도와 증기유량의 변화에 따른 증기제트의 축방향과 반경방향 온도분포와 수조 벽면에서의 동압을 측정하였으며, 고속 비디오 카메라를 사용하여 각각의 경우에 대하여 증기제트의 분출이미지를 촬영하였다. 벽면에서의 동압은 노즐의 분출구직경과 응축수의 온도에 비례하여 증가하였다. 2단계 연구에서는 몇가지 형태의 증기분사기 축소 모형에 대한 응축성능을 비교하였다. 이때에는 수조의 온도상승으로 인해 수조가 가압되는 정도를 알아보기 위해 수조를 밀봉한 상태로 실험을 수행하였다. 실험시 수조의 압력은 시간의 경과에 따라 계속적으로 증가하였으나, 이는 방출된 증기의 불완전한 응축에 의한 것은 아니고 증기의 분출과 응축으로 인한 응축수의 부피팽창과 수조 온도의 상승으로 인한 증기압의 상승 때문인 것으로 판단된다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.13 no.2
• /
• pp.54-63
• /
• 2009

Large eddy simulation was conducted for flow development in a chamber with wall injection which simulates the cold flow in an idealized hybrid rocket motor. It was found that a peculiar timescale, roughly corresponding to St~0.5, resides in the flowfield resulting from the interaction between the main oxidizer and wall injected flows. However, the fact that this time characteristics is absent in the temperature field in the vicinity of the wall indicates that even a small regression rate renders the passive scalar, such as temperature, dissimilar to the velocity field. This implies that a classical approach, which assumes that constant turbulent Prandtl number, should be replaced by a more sophisticated turbulence models to accurately predict the temperature field in the hybrid motor.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.39 no.10
• /
• pp.966-978
• /
• 2011

Transpiration cooling is the most effective cooling technique for the high-performance liquid rockets and air-breathing engines operating in aggressive environments with higher pressures and temperatures. When applying transpiration cooling, combustor liners and turbine blades/vanes are cooled by the coolant(air or fuel) passing through their porous walls and also the exit coolant acting as an insulating film. Practical implementation of the cooling technique has been hampered by the limitations of available porous materials. But advances in metal-joining techniques have led to the development of multi-laminate porous structures such as Lamilloy$^{(R)}$ fabricated from several diffusion-bonded, etched metal thin sheets. And also with the availability of lightweight, ceramic matrix composites(CMC), transpiration cooling now seems to be a promising technique for high-performance engine cooling. This paper reviews recent research activities of transpiration cooling and its applications to gas turbines, liquid rockets, and the engines for hypersonic vehicles.

• Transactions of the Korean Society of Mechanical Engineers
• /
• v.13 no.6
• /
• pp.1282-1291
• /
• 1989

본 연구에서는 이러한 연구의 시작단계로 노즐내의 열 경계층 방정식을 정리하고 압축성 와점도모델을 도입하여 유한 차분법을 이용한 전산프로그램을 작성 하였다. 한편 실제로 추진모테에서는 고온 고속의 열기류가 분출되기 때문에 추진 하고 있는 동안 노즐벽을 형성하고 있는 내열재가 심하게 손상되어 표면의 상태가 매우 거칠게 된다. 더구나 경우에 따라서는 내열재가 용발(ablation)하게 된다. 이러한 상태를 감안하여 마찰계수와 열전달 계수를 합리적으로 추정해야만 노즐의 설계와 주변장치를 합리적으로 수행할 수 있다. 따라서 본 연구에는 주로 경계층 내의 압력구배, 압축성의 효과, 물성치의 변화를 고려한 기존 난류모델에 근거하여 프로그램을 작성하고, 이것을 토대로 노즐표면 조도의 영향 및 분출(blowing)의 영 향을 중점적으로 고려하여 그 특성을 연구하였다. 노즐벽에서 분출을 고려한 이유는 표면이 용발할 때 표면의 온도가 거의 일정하게 유지된 상태로 노즐표면이 화학작용을 수반하면서 가스화됨을 초보적으로 고려해보기 위함이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.235-240
• /
• 2010

Transpiration cooling is the most effective cooling technique for liquid rocket and air-breathing engines operating in aggressive environments with higher pressures and temperatures. Combustor liners and turbine vanes are cooled by the coolant(air or fuel) passing through their porous walls and also the exit coolant acting as an insulating film. However, its practical implementation has been hampered by the limitations of available porous materials. The search for more practical methods of increasing the internal heat transfer within the walls has led to the development of multi-laminate porous structures, such as Lamilloy$^{(R)}$ and Transply$^{(R)}$. This paper reviews recent research activities of transpiration cooling for the propulsions of liquid rocket, gas turbine, and scramjet.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.40 no.9
• /
• pp.745-751
• /
• 2012

Hybrid rocket shows interesting characteristics of complicated mixing layers developed by interactions between turbulent oxidizer flow and mass flow from surface due to fuel vaporization. In this study, compressible LES with a ring structure attached at the entrance of the combustor are performed. According to one recent report, adding a ring structure in the middle of the combustor helps increasing regression rate. From the numerical results, it is seen that vortex structures near the wall becomes stronger due to the interaction with surface mass injection, and the local heat flux increases due to the vortices. This phenomenon is obviously related to the generation of dimple structures which are seen in the number of experiments. Also, the ring structure at the entrance induces strong vortex flow which enhances heat transfer to the wall surface and mixing between fuel and oxidizer as well as reaction efficiency.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.42 no.5
• /
• pp.383-389
• /
• 2014

POD analysis has been done to investigate the internal flow characteristics using LES calculation results of hybrid rocket combustion chamber. The special emphasis was put on the change in the mode energy distribution caused by the installation of diaphragm compared to the baseline case. Also the comparison was made to investigate the effect of wall blowing on the changes in the mode energy between the regions near and far from the diaphragm. For baseline case, POD results clearly distinguish the primary mode containing most of flow energy from the rest of flow modes (2-9 mode) depicting small scale modes. Also, the increase in the energy of flow modes 2-5 is responsible for the formation of relatively large scale structures due to diaphragm. In addition, the comparison of mode energy distributions of flow fields with diaphragm shows similar patterns in both wall blowing and no blowing case. This implies that the local increase in regression rate just after the diaphragm is directly associated with the increase in energy distributions of 2-5 modes.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.38 no.1
• /
• pp.64-72
• /
• 2010

Due to the interaction between main oxidizer flow and the wall injected flow resulting from the regression process, a specific time characteristics identified in the frequency spectrum of streamwise velocity is generated in the hybrid rocket motor. In order to understand the response of the turbulent flow to two different types of external momentum forcing, LES analysis was conducted without considering the combustion. It turns out that both concentrated and distributed forcings do not lead to the disastrous resonance phenomenon. Energy contents are enhanced due to the added momentum but the peak frequency was not modified in the turbulent flow near the end of the rocket motor. Natural frequency of the flow system should be taken into account to further pursue the instability issue by using external forcing.