• 대한기계학회논문집
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• 제17권10호
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• pp.2582-2589
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• 1993

Transient heat transfer characteristics of cooling of a spherical body were investigated in the radiatively active spherical medium. Initially the spherical body and the medium were maintained at their constant temperatures. Then heat transfer begins from spherical body t medium. The heat transfer mode inside the spherical body is just conduction. But heat is transferred by both conduction and radiation inside the medium. All thermodynamic properties were held constant in time. Spherical symmetry is assumed. DOM was adopted to solve RTE. The effect of characteries-tic optical thickness, conduction to radiation parameters, and solid surface emissivity has been studied.

• 한국에너지공학회:학술대회논문집
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• 한국에너지공학회 2000년도 춘계 학술발표회 논문집
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• pp.197-200
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• 2000

• Structural Engineering and Mechanics
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• 제56권3호
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• pp.341-354
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• 2015

The dual-phase lag heat transfer model is employed to study the problem of isotropic generalized thermoelastic medium with internal heat source. The normal mode analysis is used to obtain the exact expressions for displacement components, force stress and temperature distribution. The variations of the considered variables through the horizontal distance are illustrated graphically. The results are discussed and depicted graphically.

• 설비공학논문집
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• 제17권2호
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• pp.101-109
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• 2005

The purpose of this study is to investigate the performance of outdoor heat exchanger for heat pump using carbon dioxide. Two types of fin and tube heat exchangers (2 rows for type A and 3 rows for B) are tested. Both heat exchangers have counter-cross flow and 1-circuit arrangement. Test results such as heat transfer rate, pressure drop characteristics and temperature distribution in the heat exchanger are shown with respect to mass flow rate of refrigerant and frontal air velocity For cooling mode, the minimum temperature difference between air and refrigerant of type B is smaller than that of type A by $1^{circ}C$, but the pressure loss of air side is much higher for type B by $29\%$. It is found that a large temperature gradient of carbon dioxide during gas cooling Process Promotes thermal conduction through tube wall and fins which results in degradation of heat transfer performance. For heating mode operation, type B heat exchanger shows higher heat transfer performance compared to type A. However, because pressure loss of refrigerant side of type B is much greater than that of type A, the refrigerant outlet pressure of type B becomes lower than that of type A.

• 한국생산제조학회지
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• 제22권3_1spc호
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• pp.525-530
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• 2013

The objective of the present study is to investigate the heat transfer characteristics of turbulent impinging jets with bifurcating excitations. Bifurcating excitations use the dual mode, dual frequency forcing, where an axial forcing frequency is equal to double the helical forcing frequency. Under the bifurcating excitation, the heat transfer significantly increases in one plane (bifurcating plane), while nearly no heat transfer occurs in the perpendicular plane (bisecting plane). This result is closely associated with the change in the vortical structures caused by the excitation.

• Journal of Advanced Marine Engineering and Technology
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• 제29권2호
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• pp.161-167
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• 2005

The improvements of the propulsive engine efficiencies could reduce the fuel consumption. Therefore. for a marine main diesel engine the substantial increase of stroke bore ratio. so that the engine speed can be significantly reduced in order to increase the Propulsive efficiency. As a typical example. a Sulzer RTA 60C engine has acylinder diameter of 600 mm and each cylinder is capable of delivering 2.369 kW in the speed range 91-114 rpm. In order to Provide basic data for thermal system of marine engine. this work performs an experimental study of heat transfer in a square channel with one rib-roughened wall under sin91e mode of reciprocating oscillation. A selection of heat transfer measurements illustrates the manner by which the reciprocating channel with two opposite heating walls has the higher heat transfer Performance than with four heating wall.

• Nuclear Engineering and Technology
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• 제25권1호
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• pp.166-177
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• 1993

사용후 핵연료 건식 저장 캐니스터의 핵연료 바스켓 안에 있는 CANDU 37소자 핵연료 다발의 최대 온도를 계산하기 위한 단순화된 열해석 방법과 함께 대기 조건 인자들이 캐니스터 내부의 최대 핵연료 온도에 미치는 영향을 조사하기 위해 수행한 표본 해석 결과를 제시하였다. 3가지 모우드(mode)의 열전달이 공존하는 캐니스터 내부핵연료 다발의 복잡한 기하학적 구조에 대한 다차원열전달 문제를 풀기 위하여 건식저장 캐니스터에 저장된 CANDU 사용후 핵연료 다발들을 등가 및 동심의 핵연료 실린더(cylinder)로 대치하였다. 추가적인 입력 자료 및 열전달 상관식을 이용하여 등가 핵연료 실린더의 단순화된 축대칭, 2차원, 복수 모우드(multi-mode)의 열전달 문제를 기존의 컴퓨터 코드인 HEATING5로 해석하였다. 예측한 온도 분포와 식물 모형 실험 결과의 비교는 만족스러울 정도로 일치함을 보여주고 있다.

• 설비공학논문집
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• 제7권4호
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• pp.556-565
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• 1995

The physical model of interest is based upon the concentric cylinder, where the outside cylinder is filled with optically thick and high temperature phase change material(PCM). The fluid is flowing through the inside cylinder to transfer the appropriate energy. The fluid is flowing through the inside cylinder to transfer the appropriate energy. The governing equations for the phase change material including internal thermal radiation and for the turbulent transfer fluid have been employed and numerically solved. The optically thick phase change justifies the P-l spherical harmonics approximation, which is believed to be appropriate choice particularly for the much coupled problem like in this study. The solid/liquid interface, temperature distribution within the PCM and the heat flux from the PCM to the transfer fluid have been obtained and compared with those of laminar transfer fluid. The numerical results show that the turbulent transfer fluid accelerates the solid/liquid interface and results in the increase of heat transfer rate from the PCM. The internal thermal radiation within the PCM, however, does not always playa role to increase the heat transfer rate throughout the inside cylinder. It is believed that the combined heat flux has been picked up more in the inflowing area than in the pure conductive phase change material.

• 한국추진공학회지
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• 제16권3호
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• pp.82-89
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• 2012

추진제탱크 내의 극저온 추진제는 발사체의 비행 과정동안 주변으로부터 에너지를 흡수하여 온도가 상승한다. 비행 종료 시점에 있어 터보펌프 입구 요구조건 이상으로 온도가 상승된 추진제는 사용할 수 없는 잔류추진제로 남게 된다. 본 논문에서는 극저온 추진제 상층부의 온도변화를 살펴보기 위하여 추진제 표면 근처에서의 열전달계수를 구해보고자 하였다. 추진제 상층부의 열전달을 전도로 단순화하여 열전달계수를 예측하는 방법을 제시하였다. 이를 통해 얻어진 추진제 상층부의 온도를 시험데이터와 비교하여 열전달계수 예측 방법의 적용 가능성을 확인하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제37회 추계학술대회논문집
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• pp.709-716
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• 2011

추진제탱크 내의 극저온 추진제는 발사체의 비행 과정동안 주변으로부터 에너지를 흡수하여 온도가 상승한다. 비행 종료 시점에 있어 터보펌프 입구 요구조건 이상으로 온도가 상승된 추진제는 사용할 수 없는 잔류추진제로 남게 된다. 본 논문에서는 극저온 추진제 상층부의 온도변화를 살펴보기 위하여 추진제 표면 근처에서의 열전달계수를 구해보고자 하였다. 추진제 상층부의 열전달을 전도로 단순화하여 열전달계수를 예측하는 방법을 제시하였다. 이를 통해 얻어진 추진제 상층부의 온도를 시험데이터와 비교하여 열전달계수 예측 방법의 적용 가능성을 확인하였다.