• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.87-92
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• 2003

In rocket systems, somtimes special devices or equipments are installed near the nozzle exit area where high temperature and pressure combustion gas flows. To pretect these subsystems from severe thermal environment, it is necessary to have accurate thermal data measured from the experimental liquid rocket firing test. Test variables were combustion pressure (200, 300, 400 psi) and mixture ratio (1.5, 2.0, 2.5) and quartz was used as a heat probe. Measurement technique used in this research can be also applied to measure the radiative heat flux inside the combustion chamber which is important imput data for the liquid rocket regenerative cooling system design.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.16 no.3
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• pp.1605-1610
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• 2015

The present study has been accomplished to elucidate the effect of radiation heat transfer in the heat transfer analysis of refrigerator gasket, which has near 30% of refrigerator heat loss. The numerical heat transfer analysis has been conducted with the simplified modeling of refrigerator gasket. From the present CFD analysis, heat loss at the gasket is $25.6W/m^2$ for the case without radiation effect and that for the case with radiation effect is $55.0W/m^2$, which is 2.2 times greater heat loss. The radiation protection layers were installed in the gasket from 0 to 7 and the case with 7 layers has 33% reduction effect of heat loss compared with the case without any radiation protection layer. Additionally, it is better effect of radiation heat loss reduction that the radiation protection layers would be placed to the outer or inner side of gasket rather than placing to the center of gasket.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.2-3
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• 2002

일반적으로 연소과정에서 발생한 고온고압의 연소가스로 인하여 액체추진기관의 연소실 및 노즐 벽면 그리고 추진기관 후방부위에 대류열전달(Convective heat transfer)과 복사열전달(Thermal radiative heat transfer)이 발생하는 것으로 알려져 있으며, 액체추진기관에서 발생하는 복사열전달 현상은 재생냉각장치의 열입력량 예측 및 발사체의 추진기관 후방부위에 탑재되는 전자장이 및 구조물의 열적환경(Thermal environmental phenomena)을 분석하는데 매우 중요하다. 이에 본 연구에서는 노즐 후방부위에서 발생하는 복사열전달량(Radiative heat transfer rate)을 측정하고 연소압(Chamber pressure)과 혼합비(Mixture ratio)에 따른 영향을 파악하였다.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1995.05a
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• pp.150-156
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• 1995

보일러 화로내의 3차원 복사열전달 현상을 비교적 간단하게 수행할 수 있는 프로그램을 개발하여 중유를 연료로 사용하는 산업용 보일러의 화로해석을 수행하였다. 프로그램 개발시에는, 공학적으로 수용이 가능한 범위내에서의 경험값 및 가정을 도입하여 화로내에서 존재하는 현상들을 해석하기 위한 연립편미분방정식을 가능한 분리(decoupling)시켜 3차원 복사열전달 현상을 비교적 간단하게 수행할 수 있게 하였으며, 특히 보일러 제조업체의 설계부서에서 직접 화로해석을 수행하고 그 결과를 기본설계에 반영할 수 있게 시도하였다. 실제 보일러의 화로에 대한 설계자료를 이용하여 화로해석을 수행하였으며, 그 결과의 신뢰성을 입증하였다.

• Fire Science and Engineering
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• v.21 no.4
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• pp.18-24
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• 2007

The purpose of this study is focussed on the numerical predictions of temperature distribution by radiation heat transfer in atrium fire using the field fire model and the CCRHT-3D code. This code uses standard $k-{\varepsilon}$ turbulent model with SIMPLE algorithm and weighted sum of gray gases model regrouping(WSGGM-RG). The WSGGM-RG calculates radiative properties on the reduced computational loads while reserving the accuracy. The numerical results show that lower temperature distributions on the wall and the top ceiling wall can be obtained by considering radiative heat transfer. The temperature on the top ceiling wall can be an important parameter in predicting the operating condition of the sprinkler head.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.2
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• pp.72-79
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• 2003

A numerical calculation was conducted to estimate and to elucidate the role of the radiative heat flux from metal particles(Al, $Al_2O_3$) on the dynamic extinction of solid propellant rocket where the rapid depressurization took place. Anon-linear flame modeling implemented by the residence time modeling for metalized propellant was adopted to evaluate conductive heat flux to the propellant surface. The radiative heat feed back was calculated with the aid of a modified comvustion-flow model as well. The calculation results with the propellant of AP:Al:CTPB=76:10:14 had revealed that the radiative heat flux is approximately 5~6% of total flux at the critical depressurization rate regardless of chamber geometry (open or confined chamber). It was also found that the dynamic extinction in open geometry could be predicted at the depressurization rate about 45% larger with radiative heat feedback than without radiation. Thus, it should be claimed that even a small amount of radiative flux 5~6% could produce a big error in predicting the critical depressurization rate of the metalized propellant combustion.

• Journal of Advanced Marine Engineering and Technology
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• v.21 no.3
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• pp.229-235
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• 1997

The comparison of radiative and convective heat transfer in a room air ventilation is investi¬gated by a numerical simulation. The room air temperature distributions with radiation are appeared more uniform than without radiation at Gr= 1460 and Re=50. The mean Nusselt number in the radiative heat transfer shows less value than convective heat transfer. The total mean Nusselt number is found Wall 1> Wall 3${\fallingdotseq}$Wall 2 7 Wall 4.

• Journal of the Society of Naval Architects of Korea
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• v.39 no.1
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• pp.61-72
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• 2002

The flaring system of FPSO burns out the byproduct natural gas. The thermal loading due to radiative heat of flaring gas leads to undesirable thermal-stresses on itself. Nowadays it needs to understand the amount of thermal loading of flaring system since the requirement for the safety of the flaring system. However, few studies have been performed on the thermal environment and radiative heat flux on the FPSO flaring system. Present study suggests a procedure to model the thermal environment and a FEA process to analyze the temperature distribution and thermal stresses of FPSO flaring system. In order to get the temperature distribution, the radiative heat conditions and convective heat conditions are included in the heat transfer analysis. By making the use of temperature obtained through heat transfer analysis, the thermal stress analyses are performed. The results of the present study can be used to design the flaring system and determine the heat shield in the flaring system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.29-29
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• 1998

고체 추진제 연소불안정에 관한 해석은 준-정상 1차원 해석인 QSHOD(Quasi-Steady Homogcneous One-Dimension)에 의하여 단순화된 지배방정식을 이용하여 응축영역을 해석하는 것이 일반적이다. 이때 외부교란에 대한 기체영역과 표면반응 영역의 응답은 화학반응이 발생하지 않는 고체영역의 응답에 비하여 매우 빠르므로 준-정상적인 거동을 한다. 본 연구에서는 복사열전달에 의한 열속(heat flux)이 고체 추진제의 표면에 존재하며 이 중의 일부가 고체영역에서 흡수될 때 표면에서의 선형교란을 고려한 ZN(Zeldovich-Novozhilov) 방법을 이용하여 연소불안정 현상을 이론적으로 해석하여 연소불안정 현상을 설명할 수 있는 연소 응답함수를 구하였다. 본 연구에서 얻어진 응답함수를 해석함으로써, Zebrowski등$^{(5)}$ 에 의하여 얻어진 복사열 교란에 대한 응답함수가 과소 평가된 응답특성을 나타내고 있음을 알았다. 또한 응답함수의 고유불안정성을 판별하는 민감계수 r과 k의 영역의 해석으로부터 SOn등$^{(6)}$ 에 의하여 밝혀진 안정 경계선의 안정한 영역보다 본 연구에서 구한 안정 경계영역이 줄어드는 경향을 보여주고 있다. 이것은 (6)에서 과소 평가된 복사열전달의 영향을 수정한 결과 때문이다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.14 no.3
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• pp.685-693
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• 1990

The heat transfer coefficients were calculated numerically to see the effects of radiation around the porous medium put on the flat plate at a distance from the leading edge of flat plate for the two-dimensional laminar flows. To verify the analytical model developed and invoke the heat/mass transfer analogy, an experiment was carried out using naphthalene sublimation technique. From the effects of the wake, Sherwood number is maximum around the region where the porous medium is attached. The theoretical results correspond well with the experimental results at small Darcy number. Permeability of ceramic blocks used for experiment was also measured and the Forchheimer equation is applicable in our measurement range.