• Journal of the Korean Institute of Gas
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• v.11 no.3
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• pp.44-48
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• 2007

The cooling heat transfer characteristics of supercritical $CO_2$ in a helical coil gas cooler on the change of coil diameters are experimentally investigated. The main components of the refrigerant loop are a receiver, a variable speed pump, a mass flow-meter, a pre-heater and a helical coil gas cooler (test section). The test sections are made of a copper tube which the inner diameter is 4.55 mm and the helical coil diameters are done of 26.75 mm and 41.35 mm. The mass fluxes of refrigerant are varied from 200 to 800 [$kg/m^2s$] and the inlet pressures of gas cooler are 7.5 to 10.0 (MPa). A gas cooler with helical coil diameter of 26.75 mm has larger heat transfer coefficient than that of 41.35 mm. Also, when compared with experimental data and published correlations avaliable, most of correlations are under-predicted, but Pitla published correlations avaliable, most of correlations are under-predicted, but Pitla et al.'s correlation shows a relatively good coincidence with the experimental data except the region of pseudo critical temperature.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.139-143
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• 2005

Combustion Test Facility for Liquid Rocket Engine using kerosene and liquid oxygen has been developed for the purpose of cooling and performance study. Test engine of thrust 0.5 KN(design thrust) is tested to confirm the normal operation. Therefore, water-cooled firing tests using kerosene engine with injectors of fuel-centered coaxial type are conducted. With the viewpoint of characteristic velocity, and specific impulse at sea level, and chamber pressure on OF mixture ratio are analyzed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.224-227
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• 2011

In order to determine the enthalpy profile in the high temperature transpiration cooling test facility for the air-breating engine compartments, theoretical calculation and measurement for the flow of the test section are performed. The mass averaged enthalpy value determined by the heat balance and sonic throat methods is 10 MJ/kg. The centerline enthalpy value measured using the slug type copper calorimeter is 15 MJ/kg. Typically, the ratio of centerline and mass averaged enthalpy should be varies from 1.4 to 4. This facility has lower bound of enthalpy profile. It will be effective in testing of high temperature transpiration cooling.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.2
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• pp.50-55
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• 2011

A preburner for the high performance, staged combustion cycle liquid rocket engine is being developed. For the structural design processes, strength experiments and finite element analyses on specimens simulating the brazing joints of the preburner, were performed and compared. Total two kinds of the specimen were manufactured for the tests. One simulated the joints between the oxygen injectors and the head junctioned by the conventional vacuum brazing. The another was made to test the brazing surfaces by vacuum compression between the combustion chamber cooling channel and the outer wall. During the burst experiments, it was observed that the fractures were occurred not at the brazed joining but in the middle of the face plate and the cooling wall. In addition, the analysis showed that the predicted fracture locations and the strains were well matched with the experiment results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.71-74
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• 2010

Using the technology demonstration model of 75-tonf-class combustor which is expected to be used to the rocket engine of a korean space launch vehicle, 2 times of firing tests were carried out. Firing tests were done at 50% of the nominal flow rate because of incapability of the test facility and limit of the test bed strength. Through the low pressure firing tests of 75-tonf-class channel cooling thrust chamber, reliability and stability at the ignition and combustion phases were confirmed. Additionally it was foreseen that the 75-tonf-class thrust chamber would satisfy the performance requirements.

• Proceedings of the Korean Vacuum Society Conference
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• 2010.08a
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• pp.11-11
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• 2010

고도의 진공 환경을 요구하는 반도체 생산 라인에 적용되는 고진공 펌프는 주로 복합 분자펌프와 크라이오 펌프가 사용되고 있다. 이 중 크라이오 펌프는 극저온으로 냉각되는 냉각판에 기체 분자를 응축 또는 흡착시켜 기체를 제거하는 방식으로 복합 분자 펌프로 무게가 가볍고 증발 온도가 낮은 네온, 수소, 헬륨 기체 제거에 장점이 있다. 본 연구에서는 현재 상용화된 크라이오 펌프에 적용되는 GM 극저온 냉동기를 대체하기 위한 2단 GM형 맥동관 냉동기를 개발하여 기초 성능 시험을 수행하였다. 1단과 2단 모두 U-자형 형상으로 제작되었으며, 압력과 질량 유동 사이의 위상 조절을 위하여 오리피스 밸브와 이중 유입 밸브를 사용하였다. 개발된 맥동관 냉동기의 냉각 성능 목표는 1단(80 K)과 2단(20 K)에서 각각 45 W와 5 W이다. 기초 시험에서는 위상 조절용 밸브들의 개도와 작동 조건에 대한 냉각 특성과 부하 특성 시험을 수행하였다. 특히, 본 연구에서는 로터리 밸브 및 위상 조절 기구의 배치로 인해 고온부 형상이 복잡한 맥동관 냉동기를 크라이오 펌프로의 적용 편의성을 위하여 고온부 외형 구조를 단순화하였으며, 개발된 맥동관 냉동기와 기존에 크라이오 펌프에 적용되는 GM 극저온 냉동기를 비교, 고찰하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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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 Korea Foundry Society
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• v.21 no.3
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• pp.192-197
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• 2001

본 연구에서는 여러 다른 냉각속도로 냉각되는 강의 조직과 경도를 예측하는 수치 해석을 수행하였다. 해석 프로그램은 확산과 비확산 변태에 대한 변태 이행 방정식과 유한차분법을 이용하여 제품에 대해서 온도분포 및 조직변태에 대한 예측을 수행하고 또한 경도를 예측하도록 하였다. 해석 결과와의 비교를 위해 여러 다른 냉각속도로 냉각되는 AISI 410시편들에 대한 일련의 시험을 행하여 각각의 조직과 경도를 구하였으며 특히 온도해석에 사용하는 열전달계수는 실험을 통하여 구한 값을 사용하였다. 실험에 의해 구해진 결과는 해석 프로그램을 이용한 값과 잘 일치 하였다.

• Proceedings of the Korean Nuclear Society Conference
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• 1996.05a
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• pp.440-445
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• 1996

본 논문에서는 가압기에 기포가 형성되기전 원자로 냉각재계통의 압력을 자동으로 제어할 수 있는 원자로 냉각재 압력 제어기를 개발하여 원전 시뮬레이터를 통해 설계된 제어기의 성능시험을 수행하였다. 그 결과 냉각재의 압력변동을 주는 환경 요인 발생시에도 설정치에 안정된 압력제어 특성을 보여주었다. 원전 기동시 압력제어에 본 논문에서 제안한 제어기를 적용할 경우 운전원의 운전부하를 줄여줄 것으로 예측된다.

• Journal of Hydrogen and New Energy
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• v.7 no.2
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• pp.121-128
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• 1996

A direct cooling equipment for hydrogen liquefaction has been developed and tested. A direct cooling equipment consists of a liquefaction vessel, a radiation shield, a cryostat and a GM refrigerator. The cool-down and warm-up characteristics of the liquefaction apparatus have been investigated in detail. It is found that the hydrogen starts to be liquefied in the liquefaction vessel after 45 minutes of cool-down. The cool-down and warm-up tests of helium gas are also performed. The cool-down and warm-up characteristics of helium gas are found to be very different from those of hydrogen gas, since helium is not liquefied under the present operating conditions. When the liquefaction vessel is evacuated, natural convection phenomena of charged gas in liquefaction vessel can be removed. It is seen that the cool-down time of liquefaction vessel is substantially increased in vacuum environment.