• 대한기계학회논문집B
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• 제39권7호
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• pp.625-631
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• 2015

이번 연구는 패킹 모듈로 채워진 축열조의 방열 성능을 수치해석 하였다. 해석에는 PCM의 상변화 현상을 계산하기 위해 엔탈피-공극률 방법을 이용하였다. 이 방법을 통해서 방열 시 축열조 상부로부터 열전달유체가 흐를 때 모듈에서의 녹는 현상을 계산하였다. 축열조 디자인에 모듈 배치, 모듈 수 등의 다양한 인자가 있지만, 본 해석에서는 유량의 변화에 따라 나타나는 축열조 출구온도, 전체 PCM의 시간에 따른 녹은 양 및 축열밀도를 확인하였다. 결과적으로 유량이 증가할수록 출구온도가 높게 형성되었으며, 전체 PCM이 녹는데 필요한 시간이 짧아지고 축열 밀도 역시 증가하여 목표치의 93% 수준에 도달하는 것으로 나타났다.

• Applied Biological Chemistry
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• 제37권6호
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• pp.463-471
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• 1994

고구마 생전분에 0.5% 농도의 계면활성제, SSL(sodium stearoyl-2-lactylate), Dimodan(mono/diglyceride), SE 1670(sucrose fatty acid ester 1670)을 첨가하여 이들 전분의 이화학적 성질과 호화 및 노화특성을 측정하였다. 고구마 전분 입자의 모양과 결정형은 계면활성제 첨가 후에도 변화되지 않았다. 계면활성제 첨가에 의해 총지방 함량이 증가하였으며 아밀로오스 함량은 감소하였고 그 정도는 SE1670>SSL>Dimodan순이었다. $80^{\circ}C$에서의 팽윤력과 용해도는 무처리 전분에 비해 계면활성제 첨가 전분은 감소하였다. 아밀로그래프에 의한 호화개시온도는 무처리 전분이 $72.5^{\circ}C$였고 계면활성제 첨가시 변화는 없었으며 Dimodan과 SE1670 첨가 전분의 경우 최고 점도가 나타났다. 시차주사열량기에 의한 호화 양상은 무처리 전분의 피크 온도와 엔탈피는 각각 $73.7^{\circ}C$, 1.3 cal/g이며, 계면활성제 첨가 전분의 호화 피크 온도는 증가하였으나 엔탈피는 감소하였다. 알칼리 호화 양상은 초기에 급격한 점도의 증가를 보이다 완만해졌으며 계면활성제 첨가 전분의 점도는 무처리 전분에 비해 감소하였으며 계면활성제 종류에 따라 차이를 보였다. ${\alpha}$-아밀라아제-요오드법에 의한 노화도는 무처리 전분에 비해 SSL과 SE1670 첨가한 전분의 노화도는 감소하였다. 시차주사열량기에 의한 노화도는 계면활성제 첨가 전분은 무처리 전분에 비해 모두 감소하였다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2006년도 제33회 KOSCO SYMPOSIUM 논문집
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• pp.209-219
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• 2006

The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. $15^{\circ}$ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated at the trailing edge of the cavity and reflects off the top and bottom wall. For non-reacting flow, static pressures in low equivalence ratio are similar to those in no fuel injection. As equivalence ratio is increased, static pressures are increased in the duct. In the similar equivalence ratio, static pressures are increased when total enthalpy is decreased. For reacting flow, the flame is occurred near the cavity. The combustion is weak locally in the middle of the duct. The up and down pressure distribution in the duct means that the supersonic combustion is generated.

• 한국유체기계학회 논문집
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• 제2권4호
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• pp.16-23
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• 1999

The characteristic of unsteady flowfields on gas turbine, particularly on a rotor blade surface has been numerically investigated. The unsteady flow in a rotor blade passage as a result of wake/blade interaction is modeled by the inviscid flow approach, and solved by Euler equations using a time accurate marching scheme. Unsteady flow in the blade passage is induced by periodically moving a wake model across the passage inlet. The wake model used in this study is the Gaussian wate model in which the wake flow is assumed to be parallel with uniform static pressure and uniform relative total enthalpy. Numerical results show that for the case of Ps/Pr=1.5, the velocity and pressure distribution on the blade surfaces have much more complex profiles than for the case of Ps/Pr=1.0.

• 한국연소학회지
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• 제7권3호
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• pp.32-36
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• 2002

A numerical study was carried out to investigate combustion phenomena in a model Scramjet engine, which had been experimentally studied at the University of Tokyo using a high-enthalpy supersonic wind tunnel. The main airflow was Mach number 2.0 and the total temperature of hot flow was 1800K. Equivalence ratio was set to be 0.26 which is higher than that of experiment to investigate the effect of strong precombustion shock. The results showed that self-ignition occurred at the rear bottom wall of the combustor and combined with the shear layer flame between fuel jet and main airflow. Then, precombustion shock was generated at the step location and reversely enhanced the mixing and combustion process behind the shock. Due to the high equivalence ratio, the precombustion shock moved upstream of the step compared with that of experiment.

• 한국연소학회지
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• 제12권1호
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• pp.21-27
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• 2007

The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. $15^{\circ}$ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated at the trailing edge of the cavity and reflects off the top and bottom wall. For non-reacting flow, static pressures in low equivalence ratio are similar to those in no fuel injection. As equivalence ratio is increased, static pressures are increased in the duct. In the similar equivalence ratio, static pressures are increased when total enthalpy is decreased. For reacting flow, the flame is occurred near the cavity. The combustion is weak locally in the middle of the duct. The up and down pressure distribution in the duct means that the supersonic combustion is generated.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2001년도 제22회 KOSCI SYMPOSIUM 논문집
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• pp.127-132
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• 2001

A numerical study was carried out to investigate the combustion phenomena in a model Scramjet engine, which had been experimentally studied in the University of Tokyo using a high-enthalpy supersonic wind tunnel. The main airflow was 2.0 in Mach number and the total temperature of hot flow was 1800K. Equivalence ratio was set to be rather higher value of 0.26 than that of experiment to investigate the effect of strong precombustion shock. The results showed that self-ignition occurred at the rear bottom wall of the combustor and combined with the shear layer flame between fuel jet and main airflow. Then, precombustion shock was generated at the step location and reversely enhanced the mixing and combustion process behind the shock. Due to the high equivalence ratio, the precombustion shock moved upstream of the step compared with that of experiment.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.98-101
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• 2003

본 연구는 극초음속으로 비행하는 탄도발사체의 선두부분의 유동현상에 대해 기술하였다. 호주국립대학의 자유 피스톤 충격파 관 T3을 이용하여 수행한 Hyperbolic 선두형상의 실험 모델에 대해 이를 수치적으로 해석하였다 98%의 $N_2$와 2%의 $O_2$의 유동조건에 대해 전엔탈피 8MJ/kg에서의 실험결과를 수치결과와 비교를 하고, 2-temperature 모델링을 적용하여 1-temperature 모델링과의 차이를 확인하였다.

• 한국전산유체공학회지
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• 제14권1호
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• pp.35-44
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• 2009

To adequately analyze flows in pipe or duct network system, traditional node-based junction coupling methods require the junction loss which is specified by empirical or analytic correlations. In this paper, a new finite volume junction coupling method using a ghost junction cell is developed by considering the interchange of linear momentum as well as the important wall-effect at junction without requiring any correlation on the junction loss. Also, boundary treatment is modified to preserve the stagnation enthalpy across boundaries, such as pipe-end and the interface between junction and branch. Also, the computational accuracy and efficiency of the Godunov-type finite volume schemes are investigated by tracing the total mechanical energy of rapid transients due to sudden closure of valve at downstream end.

• 한국농공학회:학술대회논문집
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• 한국농공학회 2000년도 학술발표회 발표논문집
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• pp.333-339
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• 2000

This study was performed to investigate the performance of heat recovery device attached to exhaust gas funnel connected to combustion chamber of greenhouse heating system. The experiment heat recovery system is mainly consisted of LPG combustion chamber and two heat recovery units; unit-A is attached directly to the exhaust gas funnel, and unit-B is connected with unit-A. Heat recovery performance was evaluated by estimating total energy amount by using enthalpy difference between two measurement points together with mass flow rate of gas and/or air passing through each heat recovery unit depending on 5 different flow rates controlled by voltage meter. The results of this experimental study, such as heat exchange behavior of supply air pipes and exhaust air passages crossing the pipes, pressure drop between inlet and outlet, heat recovery performance of exchange unit, etc., will be used as fundamental data for designing optimum heat recovery device to be used for fuel saving purpose by reducing heat loss amounts mostly wasted outside of greenhouse through funnels.