• Proceedings of the Korean Society of Marine Engineers Conference
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• 2012.06a
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• pp.123-124
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• 2012

Effervescent atomizer in which the liquid is ejected from nozzle with bubble caused by gas injection into the liquid is one of twin-fluid atomizers. Effervescent atomizer is operated with the lower injection pressure and the smaller air flow rate when compared with those of other twin-fluid atomizers. In this study, we attempted experiment study to investigate the atomization characteristics of effervescent atomizer related with the internal flow condition. The nozzle was made with acrylic material to investigate the nozzle internal flow. The macroscopic spray analysis was conducted with internal flow images and spray images. Furthermore, SMD was measured by using the laser diffraction method. According to this study, the internal flow condition changed from bubbly flow to annular flow as the air-liquid mass ratio(ALR) increases. At that time, the atomization characteristics were improved.

• Fire Science and Engineering
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• v.26 no.3
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• pp.73-78
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• 2012

This study is intended to understand flame behavior of pool and whirl fire by height of fire source. Liquid fuel was methanol which is used in many studies for pool and whirl fire. Size of vessel was $100{\times}100{\times}50$ and the vessel was made by stainless steel. Combustion time, mass loss rate, flame temperature, flame height and air entrainment rate from the outside to flame were measured, and flame behavior was visualized with video camera. Based on the experiment, it was found that combustion characteristics by height of fire source got a more effect on whirl fire than pool fire.

• Journal of ILASS-Korea
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• v.2 no.2
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• pp.35-42
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• 1997

An innovating technique of atomizer has been proposed to supply and to atomise molten materials. Both of a simple geometry of nozzle and an improved nozzle have been fabricated in the present study. With these nozzles, characteristics of the suction and disintegration have been empirically investigated. The important conclusions are as follows; In the case of a simple nozzle: 1) Although the sucking up and supplying of molten materials are available, the applications of powder metallurgy are limited. 2) It is concluded that the more air flow rate, $W_A$ or the shorter the height of air nozzle from the surface of supplied water, $L_h$, the more the atomizing mass of liquids, $W_L$. In the case of an improved nozzle: 3) The stable liquids can be supplied due to cut off the passage of surrounding air entrainment by air jets. 4) The atomizing mass of liquids, $W_L$ has affected not so much on the height of nozzle from the surface of supplied water, $L_h$ as that from the orifice, hc.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.358-361
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• 2007

Most aircraft cruise in the stratosphere at which temperature is below $-50^{\circ}C$ md, as a result, the surface of aircraft can be iced up. Ice on the wing can change aerodynamic characteristic and results in the deterioration of its performance. Ice on the engine inlet increases the possibility of compressor blade damage and affects the performance and safety of the engine. This paper focused on the development of icing simulation device for analyzing effect of icing on engine performance. Icing simulation tests were conducted with a liquid air system and a icing simulation device and results show that icing could be simulated with this system.

• Journal of Aerospace System Engineering
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• v.11 no.1
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• pp.8-13
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• 2017

This study was performed to evaluate the turbine performance of a turbopump in the third stage engine of the Korea Space Launch Vehicle-II. The turbine is a supersonic impulse type with a single rotor. One nozzle is for starting and four remaining nozzles are for steady operation. A similarity test was carried out in the high air test facilities at the Korea Aerospace Research Institute. Test results showed that turbine efficiency changed much more from rotational speed variations than by pressure ratio variations. These results showed characteristics similar to other supersonic impulse turbines.

• Journal of the Korean Chemical Society
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• v.34 no.6
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• pp.555-560
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• 1990

High temperature superconducting films of $YBa_2Cu_3O_{7-x}$ were fabricated on the (100) single crystal faces of YSZ (yttria stabilized zirconia) and SrTi$O_3$ by aerosol spray using ultrasonic atomization. The superconducting phase was formed by a three-step process: (a) spraying of a stoichiometric solution of nitrates of yttrium, barium, and copper on heated substrates kept at 250$^{\circ}C$, (b) preheating of the sprayed films in air at 550$^{\circ}C$, and (e) sintering of the films in flowing oxygen at 950$^{\circ}C$, followed by furnace cooling. Resistances of the films were measured by the dc four-probe method and superconductivity was confirmed above the liquid nitrogen temperature.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.2
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• pp.78-86
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• 2006

This paper presents the performance test result of the 30-ton class turbopump turbine. Test has been conducted using high pressure cold air, The turbine overall performance has been measured for various pressure ratio and rotational speed settings. The nozzle-rotor clearance effect on turbine performance also has been tested for the four kinds of the nozzle-rotor clearance values. We found that turbine efficiency rated 51.1% at its design velocity ratio and pressure ratio of 13.5. We also found that turbine efficiency can be increased by 3.5% for approximately 1mm decrement of the nozzle-rotor clearance from its nominal value.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2008.06a
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• pp.43-44
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• 2008

PECVD 방식에 의거 low-k 유전상수를 갖는 층간 절연막 (ILD)를 제작하였다. 전구체 BTMSM 액체를 기화하여 16sccm 에서부터 1 sccm씩 증가하면서 25sccm 까지 p-Si[100] 기판위에 유량비를 조절하였으며 60 sccm으로 일정산소 $O_2$ 가스를 반응 챔버에 도달하도록 하였다. 제작된 시편의 구성성분은 FTIR의 흡수선으로 확인하였고, 알루미늄 전극을 구현한 MIS (Al/SiOCH/p-si(100)) 구조의 커패시터를 가지고 정전용량-전압 (C-V) 특성을 측정하여 유전상수를 계산하였다. BTMSM/$O_2$에 의한 층간절연막의 k ~ 2 근방의 저유전상수는 유량비에 민감하게 의존되고 열처리에 의하여 $CH_3$의 소멸 및 Si-O-Si(C) 성장하는 효과에 의하여 더 낮아짐을 확인할 수 있었다. 또한 상온 및 대기압에서 공기 중에 노출시켜 자연 산화과정을 겪은 시편들의 유전상수는 전체적으로 증가하였지만, 열처리한 박막이 상대적으로 안정화된 것을 확인하였다.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.151.1-151.1
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• 2012

우주발사체와 발사지원설비를 연결하여 추진제 공급과 전기신호 송수신 등을 가능하게 하는 메커니즘을 엄브리칼 장치라고 한다. 국내 우주발사체의 경우 액체산소와 케로신을 추진제로 사용하며, 질소, 공기 및 헬륨 등의 가스를 밸브구동, 공간 퍼지, 추진제 가압에 이용한다. 본 논문에서는 우주센터의 발사대설비에 적용된 엄브리칼 장치 중 추진제 및 고압가스 공급을 위한 자동체결장치(auto coupling device)의 구성, 기능 및 발사 준비를 위한 프로세스에 대해 기술하고 있다. 자동체결장치는 발사체 하부 두 곳에 연결되며, 산화제 공급측의 체결장치(coupling device 1)와 연료 공급측의 체결장치(CD 2)로 구성된다. 이 장치는 발사체와의 접촉면에서 기밀을 확보한 상태에서 내부의 탱크, 밸브, 인터스테이지 등에 추진제 및 각종 가스를 공급하는 통로역할을 하며, 발사준비가 완료된 후에는 발사체 이륙 전 또는 이륙과 동시에 발사체로부터 자동으로 분리된다. 각각의 체결장치 구성품으로는 발사체 이륙시 발생하는 고온의 화염으로부터 장치를 보호하는 PD(protective device), 접촉면에 기밀을 제공하고 추진제 누출을 방지는 MCP(multi-channel plate), 접촉면을 보호하기 위한 덮게, 각종 연결 배관의 전진과 후진을 위한 캐리지, 발사체와의 체결을 지지하는 그립 등이 있다. 발사 준비를 위해서 사전에 장치의 독립운용시험을 통해 각 구성품의 상태와 기능을 점검하고 장치의 작동성을 검증한다. 이후 발사체를 모사하는 기체 및 관제설비와 종합적으로 연계 시험과 모사시험을 수행하여 최종적으로 발사준비상태를 확인하게 된다. 이러한 자동체결장치의 운용 경험은 한국형발사체의 지상지원설비 개발에 활용할 수 있을 것이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.991-994
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• 2017

In hypersonic aircraft, increase of aerodynamic and engine heat lead thermal load in airframe. It could lead structural change of aircraft's component and malfunctioning. Endothermic fuels are liquid hydrocarbon fuels which are able to absorb the heat load by undergoing endothermic reactions. In this study, we investigated the method of measuring the heat sink of catalyst by using exo-tetrahydrodicyclopentadiene as a fuel in a packed bed flow reactor similar to the actual reaction conditions.