• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.4
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• pp.348-353
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• 2011

Characteristics of cryogenic single jet flow were investigated. Liquid nitrogen was injected into a high-pressure chamber and formed single jet. Ambient condition around jet was changed from subcritical to superctirical condition of nitrogen. Injector geometries also were changed. A shape of the jet and core diameter were measured by flow visualization technique, and core spreading angle was calculated. Flow instability was found at atmospheric pressure condition. As ambient pressure increased, core spreading angle was increased and maintained after certain pressure.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.597-600
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• 2010

Cold flow injection test was conducted to investigate the characteristics of cryogenic liquid nitrogen jet at sub to supercritical condition. Single jet injector element was installed in high pressure chamber to investigate the effect of ambient pressure around the jet, injector geometry and flow conditions. Experimental results showed obvious differences between jet characteristics under subcritical and supercritical condition. Effect of injector inlet shape also was investigated.

• 발명특허
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• v.26 no.10 s.306
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• pp.76-83
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• 2001

본 발명은 승화성 고체 미립자 제트를 이용한 분사로 표면의 오염물을 제거하는 공정이다. 이는 극저온에서 고화된 입자가 표면에 고속 충돌 후 오염물을 제거하고 자신은 승화되어 잔사를 남기지 않는 청정 세척 공정을 말하는데 반도체 장비, 정밀 제품, 인쇄회로 기판 등의 다양한 표면의 각종 오염막 제거에 널리 사용될 수 있다. 본 장치의 특징은 세정 매체인 $CO_2$와 Carrier gas인 $N_2$를 사용하였고 현재 특허에 출원되어 있는 단순한 액체$CO_2$를 이용한 세정범위를 넘어 다양한 세정매체 즉, 복합인자($CO_2$ + ice, Ar + ice)를 이용하여 세정효율의 다변화를 이루었고 자체 개발한 냉동기를 이용하여 고화율이 액체 $CO_2$보다 상대적으로 낮은 기체 $CO_2$의 고화율을 증대 시킴으로써, 세정매체의 소모시간이 현격히 감소되어 원가절감 효과를 증대 시켰다. 세정대상물을 효과적으로 제거하기 위해 주 세정 매체인 $CO_2$의 수농도를 조절할 수 있는 Multi-Nozzle의 개발과 이로 인하여 세정력의 강도를 조절하도록 하였다. 세정 후 발생되는 오염입자를 효과적으로 제거하도록 국부 Exhaust를 Nozzle전단에 달아 재 오염의 방지효과를 극대화 시켰다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.150-155
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• 2010

Liquid rocket injectors play crucial roles on propulsive performance, combustion stability, and heat transfer characteristics. Nevertheless, their developments have mainly relied on empirical methods and expensive hot-firing tests due to lack of fundamental understanding of high pressure combustion phenomena in the near-injector regions. The present study was motivated by recent efforts to develop reliable modeling of liquid rocket combustion. The turbulent combustion model based on the flamelet concept has been extended to take into account real-fluid behaviors occurred at supercritical pressures, and validated against measurements for a cryogenic nitrogen injection, a non-premixed turbulent jet flame at atmospheric pressure, and a LOx/$GH_2$ coaxial shear injector at a supercritical pressure.

• Journal of ILASS-Korea
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• v.18 no.3
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• pp.140-145
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• 2013

Sub/supercritical spray experiments were conducted, and cryogenic nitrogen and gaseous argon were selected for simulants. liquid nitrogen and gaseous argon were injected in subcritical case, and supercritical nitrogen and near-critical gaseous argon were injected in near-critical/supercritical cases. shadowgraph method was used to visualize spray, and analyzed about the breakup length. The breakup length was measured from numbers of Instantaneous shadowgraph Images from each case, and they were compared with momentum flux ratios and density ratios. It was observed that the relation between breakup length and momentum flux ratio was fitted into former experiment results. and the reasonable constant was suggested about the relation between breakup length and density ratio.