• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.548-553
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• 2011

The device for studying combustion characteristic of aluminum powder and water was developed. The device has ability to adjust temperature, pressure, and equivalent ratio to some specified value which effect on combustion characteristic of aluminum and water mixture. Methane combustor, water supply device, aluminum powder feeder, and linear combustor are assembled to aluminum combustion test device. Each device has the ability to supply matter to combustor on steady and quantitatively controlled manner and test sequence specified by user can be automatically controlled. The combustion of aluminum powder was observed when integrated device was operated normally.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.173-178
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• 2003

The study was performed to understand combustion characteristics of the slinger combustor. Liquid fuel is discharged radially outwards through injection holes drilled in the high speed rotating shaft. We observed atomizing characteristics with variation of fuel nozzle rotating speed by using PDPA system. The mean drop diameter highly depends on fuel nozzle rotating speed. In KARI combustion test facility, Ignition and combustion tests were performed by using real scale combustor. In the test results, ignition and combustion efficiency were increased according to increasing fuel nozzle rotating speed. The measured radial temperature distribution at the combustor exit shows stable and fairly good distribution.

• Proceedings of the Korean Society of Computer Information Conference
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• 2011.06a
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• pp.127-128
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• 2011

본 논문에서는 Flow 모니터링 및 제어, Graph 출력, Test, History 등의 기능을 제공하는 연소기 제어 시스템을 설계하고 구현한다. Flow 모니터링 및 제어 기능은 각 채널의 현재 유량을 표시하고, 제어할 수 있다. Graph 출력 기능은 현재 채널의 상태를 그래프로 나타낸다. Test는 현재 구성된 환경이 정상적으로 동작하는지 시험하는 기능을 제공하며, Setting은 각 채널의 채널명, Point set, Range, 허용오차를 설정한다. 그리고 History는 저장된 데이터를 읽어와 Error기록, 사용자에 의해 저장된 데이터, 24시간마다 자동 저장되는 데이터를 그래프로 표시해 준다. 본 논문에서 제안한 연소기 제어 시스템을 이용해서 실제 유량을 측정한 결과, 정확한 유량의 측정을 할 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.3
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• pp.41-48
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• 2008

One of main functions of the firing control system applied to a rocket propulsion test has been to provide electric current for ignition of a solid rocket motor. This paper describes the design and implementation of an enhanced firing control system for ground propulsion test that can also control and verify various types of squib events and flight sequences.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.157-161
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• 2004

The colse type of engine system, in which the combustion gas after the gas-turbine with high temperature is supplied to the combustion chamber, was selected to increase the energy characteristics in making the rocket engine scheme which makes 1700kN thrust. The nozzle was designed with consideration of film cooling, nozzle efficiency, and the real state of cobmustion gas during the expansion in nozzle. The change of gas state and the composition of the gas through the nozzle was studied by the graphic, too.

• 한국연소학회:학술대회논문집
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• 1999.10a
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• pp.189-200
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• 1999

Combustion characteristics of a regenerative combustor for high temperature air combustion have experimentally studied. Temperature measurement on regenerative ceramic material and combustor has been carried out with changing equivalence ratio at constant turn-over period. Stable and unstable combustion region have been found and also detailed averaged temperature profile with respect to various air flow conditions have been obtained.

• 한국연소학회:학술대회논문집
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• 2013.06a
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• pp.13-14
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• 2013

The aim of this study is to investigate the parametric characteristics on regenerative system with oxy-fuel combustion by experiment. Regenerative system with a pair of oxygen burners and regenerators is used for evaluating regenerator characteristics according to design parameters such as ball (regenerator medium) size, regenerator weight, and bypass of exhaust gas. The temperature profiles with time are varied by ball size and regenerator weight. The bypass of exhaust gas shows that the heat recovery ratio increases while the regenerating temperature efficiency slightly decreases.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.12 no.2
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• pp.1005-1012
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• 2011

This research carried out a 3-dimensional simulation using computerized fluid dynamics (CFD) for the flow characteristics, temperature distribution, velocity distribution and residence time, etc. in a reactor in order to derive the optimal combustion conditions of an innovative combustion system. The area-weighted average temperature of the outlet of a furnace during combustion at a condition of fuel input rate 1.5 ton/hr, residence time 1.25 sec and air/fuel ratio 2.1 was $1,077^{\circ}C$, which is a suitable temperature for energy recovery and treatment of air pollutants. Exhaust gas is discharged through a duct at a 40~50 m/s maximum speed along strong vortexes at the center of a combustion chamber, so strong turbulence is created at the center of a combustion chamber to enhance the combustion speed and combustion efficiency. In this system, the optimum operation conditions to prevent incomplete combustion and suppress the formation of thermal NOx were air/fuel ratio 1.9~2.1 and fuel input rate 1.25~1.5 ton/hr.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.343-346
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• 2010

The construction plan of a combustion chamber test facility(CTF), a turbopump real propellant test facility(TPTF), a rocket engine ground/high altitude test facility(ReTF, HAReTF) and a propulsion system test complex(PSTC) for KSLV-II is briefly described. The development/qualification tests of 75ton-class liquid rocket engine system and engine component will be performed in CTF, TPTF, ReTF and HAReTF and the development test of $1^{st}/2^{nd}/3^{rd}$ propulsion systems for KSLV-II will be performed in PSTC. These propulsion test facilities will be built in NARO space center considering construction schedule, cost, safety distance and utility factor of propulsion test facilities.

• 한국연소학회:학술대회논문집
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• 2014.11a
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• pp.233-234
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• 2014

Lean-rich combustion system was composed both fuel-lean and fuel-rich flame at once. Each of fuel-lean and fuel-rich combustion types to reduce Thermal $NO_x$ and obtain flame stability. This study was confirmed a stability of flame through variation of flame shape that EGR was applied and compared the emission characteristics of EGR lean-rich combustion system to normal premixed combustion system at real condition to review a utility of the system. As a result, emission index of $NO_x$ and CO generated from EGR lean-rich combustion system at global equivalence ratio is 0.85 just half level($NO_x$ 0.31 g/kg, CO 0.08g/kg) compared to the amount generated from normal premixed combustion system at equivalence ratio is 0.78.