• Journal of the Korean Society for Aeronautical & Space Sciences
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• 제31권10호
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• pp.66-72
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• 2003

The cooling mechanism for a liquid rocket engine of 10tf-thrust using kerosene as a fuel was studied from the viewpoint of both the regenerative and curtain cooling. Based on the concept of a highly-stratified gas flow in the combustion chamber, the cross section of the combustion chamber was spilt into 2 independent parts, core and exterior part. Additional fuel is injected into the exterior section and gas temperature can be reduced in the exterior section. Consequently, the heat flux into the coolant and wall temperature are reduced and the thermal stability of a liquid rocket en g i.ne could be improved.

• 연구논문집
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• 통권34호
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• pp.11-19
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• 2004

An Experimental study on the characteristics of high pressure gas quenching system was carried out in the present study. The characteristics of gas quenching system have been studied with high pressure gas chamber and specimen for various gas pressure and velocity which are the design parameter of quenching system. The quenching gas was used compressed air which properties are very similar with Nitrogen gas usually used in industrial gas quenching system. The result shows that the quenching rate of mid surface of specimen is lower than each ends of them which are close to low temperature quenching surface. And to increases the quenching intensity, the increment of quenching gas pressure is more efficient than the increment of quenching gas velocity at the point of reducing the circulation fan power.

• Journal of the Korean Society of Propulsion Engineers
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• 제19권1호
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• pp.61-67
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• 2015

The cooling of hot exhaust gas is an important issue for the construction of combustor test facility. Water spray is an effective method for exhaust gas cooling due to its large latent heat in process of evaporation. In this study, 1-D analysis has been performed based on continuity, energy conservation, and saturated vapor property to understand water spray cooling of combustion gas. In the exhaust duct of combustor test facility, the injected water decreases combustion gas temperature, and evaporates in the combustion gas. However, some of the injected water is collected in the sump due to condensation. The evaporation of water helps combustion gas cooling, but causes pressure increase inside the exhaust duct due to increase of vapor pressure. These phenomena has been analyzed by 1-D modeling in this study. From 1-D analysis, the adequate mass flow rate of water spray to cool combustion gas and to avoid excessive pressure rise inside the exhaust duct has been decided.

• Journal of the Korean Society of Propulsion Engineers
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• 제22권6호
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• pp.84-93
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• 2018

Three-dimensional (3D) numerical simulations have been carried out to study how coolant injection conditions influence the cooling efficiency and projectile ejection performance in a mixture-gas ejection system (or gas-steam launch system). The 3D single-phase computational model was verified using a 1D model constructed with reference to the previous research and then a two-phase flow computation simulating coolant injection on to hot gas was performed using a DPM (Discrete Phase Model). As a result of varying the coolant flow rate and number of injection holes, cooling efficiency was improved when the number of injection holes were increased. In addition, the change of the coalescence frequency and spatial distribution of coolant droplets caused by the injection condition variation resulted in a change of the droplet diameter, affecting the evaporation rate of coolant. The evaporation was found to be a critical factor in the design optimization of the ejection system by suppressing the pressure drop while the temperature decreases inside the breech.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 한국추진공학회 2007년도 제29회 추계학술대회논문집
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• pp.170-173
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• 2007

Cooling characteristics of a liner were investigated by a film cooling method using a gas nitrogen in a rocket engine. High temperature gas of this test was made by mixing liquid nitrogen with combustion gas of a liquid rocket. A supply system of gas nitrogen was additionally constructed to the existing test facility of liquid rocket engine, and a new test section consisted of a liner and a gas injection ring was manufactured. A 10 second firing test for finding cooling characteristics of the liner was successfully conducted and liner surface temperatures and hot gas temperature was obtained.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.198-204
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• 2004

Using liquefied natural gas as a fuel, water, natural gas and liquefied natural gas-cooled firing tests were conducted. With the viewpoint of characteristic velocity, and specific impulse, the effect of OF mixture ratio and fuel inlet temperature into a combustion chamber were analyzed. OF mixture ratio and fuel inlet temperature into a combustion chamber have great influence on the performance. Characteristic velocity and theoretical specific impulse attain the maximum value at 0.72~0.75 and 0.75 of OF mixture ratio, respectively. Engine performance has a tendency to increase, proportional to fuel inlet temperature into a combustion chamber affected by the regenerative cooling.

• Journal of Advanced Marine Engineering and Technology
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• 제34권2호
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• pp.259-266
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• 2010

The heat flowrate and pressure dorp of $CO_2$ in a multi-tube-in-tube helical coil type gas cooler were predicted using LMTD method and compared with the experimental data. The mass flowrate of $CO_2$ and coolant were varied from 0.06 to 0.075 [kg/s], and the cooling pressure of gas cooler were from 8 to 10 [MPa], respectively. The LMTD method is used to predict the heat flowrate and pressure drop of supercritical $CO_2$ during in-tube cooling. The equations used by LMTD method were Gnielinski correlation for $CO_2$ and Dittus-Boelter correlation for coolant, respectively. The equation used to predict the pressure drop of $CO_2$ and coolant is Blasius correlation. In comparison of heat flowrate and pressure drop of $CO_2$ measured by experiment to that predicted by LMTD method, the experimental heat flowrate and pressure drop of $CO_2$ in the multi-tube-in-tube helical coil type gas cooler shows a relatively good agreement with that predicted by LMTD method.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.211-217
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• 2003

A liquid rocket engine(LRE) Using LO$_2$/LNG(Liquefied Natural Gas) propellants was experimentally evaluated. The purpose of this study was to investigate the performance of the LO$_2$/LNG rocket combustor that is composed of three sect ions(igniter spacer, cylinder and nozzle section), especially focused on the influence of regenerative cool ing effect in association with the phase of regenerative coolant Series of tests were conducted under the conditions of water cool ing and regenerative cool ing with LNG in the cylinder section and independent cool ing with water in the igniter spacer and nozzle sections. Parametric studies on the variation of a chamber pressure and mixture ratio were undertaken. In addition, effect of propellant(LNG) composition and its enthalpy on the performance is examined.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 한국에너지공학회 1994년도 추계학술발표회 초록집
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• pp.51-58
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• 1994

가스터빈 발전은 연료를 연소하여 연소가스로 직접 터빈을 회전시켜 터빈에 연결된 발전기에 의해 발전하는 방식으로 연료로는 중유, 원유, 경유, 가스등을 사용한다. 주요설비는 공기압축기, 연소기, 터빈 및 발전기로 구성되며 이중 고온부는 연소기와 터빈이다. 가스터빈의 효율은 터빈입구온도(TIT : TBN INLET TEMP)에 의존하는데 현재까지 약 1,30$0^{\circ}C$ 급의 가스터빈이 운전중이며 앞으로 1,50$0^{\circ}C$ 급의 고효율 가스터빈에 도전하고 있으며 연소가스의 고온화는 고온부의 재료개발, 냉각기술, 코팅기법의 향상과 더불어 이루어질 수 있다. 가스터빈의 고온부 부품인 연소기, 터빈의 동익(Moving blade) 및 정익(Fixed blade) 재료로 초내열합금이 계속 개발중이며 또한 각 부품에 대한 공기냉각기술, 코팅재료 및 기법도 개발중이다. 그러나 현재 국내에서 가동중인 가스터빈은 빈번한 기동정지로 열 사이클에 의한 부품의 손상이 심각한 실정이므로 고효율 가스터빈 개발과 이에 대한 정비기술 개발이 병행하여야만 안정된 전기공급을 이룰 수 있다는 차원에서 가스터빈은 고온부품의 정비기술에 대한 그 현황과 전망에 대해 살펴보고자 한다.

• 기계와재료
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• 제23권3호
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• pp.156-163
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• 2011

쥴톰순 냉동기는 스터링 냉동기, GM 냉동기, 스터링형 및 GM형 맥동관 냉동기 등 기계적 극저온냉동기에 비해 단순한 구조, 수 초의 급속한 냉각특성을 장점으로 중대형의 가스액화사이클 뿐만 아니라 적외선검출기의 급속냉각, 저온수술 등 다양한 분야에서 널리 사용되어지고 있다. 일반적으로 100K 이하의 작동온도 및 수 초 수준의 빠른 냉각을 요구하는 적외선검출기의 냉각을 위해서는 수 백기압 이상 고압의 질소 및 아르곤 가스를 사용하는 쥴톰슨 냉동기가 주로 사용되고 있다. 쥴톰슨 냉동기는 핀-관(fin-tube) 형태의 열교환기와 열교환기의 구조적 기반을 제공하는 멘드렐(mandrel), 쥴톰슨 노즐 등으로 구성되며, 열교환기의 열전달 성능 및 유량조절기구의 특성은 냉동기 저온부의 냉각온도, 냉각시간 및 운전시간에 큰 영향을 미친다.