• Proceedings of the Korean Vacuum Society Conference
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• 2014.02a
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• pp.141.1-141.1
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• 2014

오일 증기의 제트를 분사하여 잔류가스를 배기하는 오일확산펌프는, 구조가 간단하여 고장이 적고 저렴하며 소음 및 전기노이즈가 적게 발생하는 많은 장점을 가지고 있다. 그러나 오일의 증기압에 의해 그 도달압력이 10-9 Torr 이상으로 제한되어, 액체질소로 냉각되는 배플형태의 저온 트랩을 사용하지 않는 한 10-10 Torr영역의 초고진공 배기용으로는 사용하지 못하는 것으로 알려져 있다. 유회전펌프로 뒷받침 배기(foreline pumping)하는 700l/s의 배기속도를 가진 오일확산펌프에 300 liter/sec의 컨덕턴스를 가진 액체질소 트랩을 부착하여 메탈 실링을 사용하는 초고진공 챔버를 배기하였다. 액체질소트랩에 액체질소를 투입하면 $1{\times}10-8Pa$이하의 초고진공이 얻어졌으나, 액체질소가 증발하여 트랩의 온도가 상온으로 상승하면 압력도 $1{\times}10-7Pa$ 이상으로 상승하였다. 50 liter/sec의 배기속도를 가진 터보분자펌프로 오일확산펌프를 뒷받침 배기하면 액체질소를 투입하지 않은 상태에서 $5{\times}10-9Pa$이하의 초고진공이 얻어졌으며, 액체질소를 투입하여도 압력은 거의 변화하지 않았다. 잔류가스분석장치로 얻은 잔류가스 성분 스펙트럼은 수소가 잔류가스의 대부분을 차지하는 것을 보여주었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.147-150
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• 2007

In this study, cooling characteristics of combustion gas were investigated by injecting liquid nitrogen into liquid rocket combustion chamber. A injection ring of liquid nitrogen was installed between a combustion chamber and a mixing chamber which was designed for mixing of combustion gas and nitrogen. At first, a ignition test of liquid rocket engine was conducted to verify a stable combustion process and 10 second combustion tests were successfully conducted. The results showed that combustion gas of LRE could be cooled by using liquid nitrogen.

• Electrical & Electronic Materials
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• v.4 no.2
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• pp.114-122
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• 1991

본 논문에서는 최근의 고온초전도체 재료의 개발에 주목하여 액체 질소의 절연파괴특성에 전극이 미치는 영향에 관하여 연구하였다. 액체 질소의 극성효ㅗ가는 액체 헤리움과는 달리 전극간 거리에 따라 다르며 단 간격에서의 파괴정압은 평등전계가 가장 높고, 정침, 부침의 순서이며 장 간격에서는 역전한다. 그리고 conditioning효과, 불순물효과, 피복효과, 압력의존성 등의 실험으로 부터 액체 질소의 파괴기구는 정침에서는 정 스트리머, 부침에서는 기포파괴의 가능성이 높은 것으로 생각된다. 또한 극저온 절연 설계에서는 전극을 절연물로 피복하고 고순도 액체 질소보다는 불순물이 혼입된 액체 질소, 즉 상용 액체 질소를 냉각 및 절연재료로 사용하면 유리하다.

• Journal of Energy Engineering
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• v.23 no.3
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• pp.174-180
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• 2014

Experimental study of liquid nitrogen pool spread is carried out when it is continuously released. The liquid nitrogen spreads over a cement mortar plate with continuous release. Evaporation rate per unit area of the liquid nitrogen is measured using a digital balance, and a spreading distance of the liquid pool is measured by thermocouples. It is discovered that the evaporation rate per unit area of liquid nitrogen tends to decrease as the liquid pool spreads.

• Journal of the Korean Society of Marine Environment & Safety
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• v.18 no.3
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• pp.279-285
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• 2012

It is necessary to install the inert gas system(IGS) for preventing fire and explosion in LNGC main diesel engine crankcase besides oil mist detector(OMD) unit with $CO_2$ gas injector. Therefore, to design the liquid nitrogen IGS, analytical work is conducted for predicting the heat input load of liquid nitrogen heater with two-phase stratified flow model. This paper also presents the effects of changes in pipe diameter, saturated pressure, and inclination angle by ship's movement on cryogenic two-phase stratified flows. It is found that the stratified model gives reasonable predictions, and the model is effective to predict the heat input load of liquid nitrogen IGS.

• Journal of Aerospace System Engineering
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• v.14 no.5
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• pp.26-32
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• 2020

In this study, a facility was constructed to supply liquid nitrogen to simulate combustion instability in a liquid rocket combustor. The pressurization and supply performances were predicted and verified through different experiments. The liquid nitrogen supply system was composed of a pressurized supply system, and a dome regulator was used to adjust the pressure of the pressurant. A cavitation venturi was used to control the mass flow rate of liquid nitrogen. The condition of liquid nitrogen supply was a mass flow rate of 2.55 kg/s and the venturi inlet pressure was above 100 bar. Based on the initial experiment, it was observed that the predicted amount of the pressurant was not sufficiently supplied and the target pressure was not supplied due to a drop in tank pressure. Through the modification of the established facilities, the target mass flow rate was successfully supplied and the cryogenic liquid nitrogen supply facility was verified.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.1
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• pp.64-70
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• 2007

A test facility was developed where an inducer for a liquid rocket engine turbopump can be tested using liquid nitrogen as a working fluid. At the facility, a hydrodynamic performance test and a cavitation performance test for an oxidizer turbopump were carried out. Head-flow relation at liquid nitrogen test was similar to the case at water test. However, cavitation performance at the liquid nitrogen was superior to the case at water test, which results from the thermodynamic effect of cavitation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.93-99
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• 2006

A test facility was developed where an inducer for a liquid rocket engine turbopump can be tested using liquid nitrogen as a working fluid. At the facility, a hydrodynamic performance test and a cavitation performance test for an oxidizer turbopump were carried out. Head-flow relation at liquid nitrogen test was similar to the case at water test. However, cavitation performance at the liquid nitrogen was superior to the case at water test, which results from the thermodynamic effect of cavitation.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.2
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• pp.41-47
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• 2017

By using liquid and gaseous nitrogen as simulants, effects of pintle opening distance and simulant supplying condition on spray from pintle injector were investigated qualitatively. The experiment was performed by fixing the liquid supply pressure and varying the opening of the pintle and the supply pressure of gaseous nitrogen. Shadowgraph method with CCD camera was used for image visualization, and the differences of liquid-gas spray were compared by image post processing. In case of liquid nitrogen single injection, as the opening distance was increased, the injection speed was decreased. Therefore, the end of liquid sheet were converged to the center of spray. In the case of liquid nitrogen/Gaseous nitrogen spray, although shadowgraph images look similar to each other, It is shown that it can be analysed by image post processing.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.10
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• pp.1001-1009
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• 2012

In this study, the cooling characteristics of combustion gas were investigated by injecting liquid nitrogen ($LN_2$) into a liquid rocket combustion chamber, which uses liquid oxygen (Lox) and kerosene as propellants. $LN_2$ injectors and an extended chamber for mixing were installed at the end of the ordinary LRE combustion chamber, and a nozzle was installed after the chamber for mixing. First, an ignition test of the liquid rocket engine was conducted to verify the stable combustion process. Next, a hot firing test was performed step-by-step for safety. Finally, the test was performed for 20 s. The results showed that the combustion gas of the LRE could be successfully cooled by using $LN_2$.