• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.171-178
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• 2005

An acoustic analysis of a fuel-rich gas generator for the drive of a turbopump in a liquid rocket engine has been performed and the length of a simulating duct has been determined by comparing the resonant frequency of unstable acoustic modes to simulate an actual flight model gas generator. To simulate more realistically, a realistic short-length simulating duct has been determined by considering 1 or 2 wavelength of the unstable modes. Duct-length adjustment to turbopump can be a method to suppress a combustion instability problem by decoupling of acoustic mode and combustion characteristics. This method has been set up and validated with acoustic analysis and hot firing tests.

• 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 Propulsion Engineers Conference
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• 2017.05a
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• pp.1165-1168
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• 2017

This paper suggests a fault diagnosis of damage on inner liner of regeneratively-cooled combustion chamber during gas generator cycle rocket engine hot firing test. This method focuses on a phenomenon that fuel flow rate difference between two flow estimate methods changes under an inner liner damage of combustion chamber causing fuel leakage and it is expected that it contributes to detect a damage on the combustion chamber in early stage and prevent further destruction during the hot firing test.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1999.05a
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• pp.39-44
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• 1999

발전용 연료로 사용하는 석탄은 취급의 어려움과 가스 및 석유에 비해 품질이 낮은 단점이 있으나, 매장량이 풍부하고 가격이 저렴하여 발전용 연료로의 사용은 더욱 증대될 전망이다. 이에 따라 석탄의 안정적 수급 측면에서 구입원의 다양화가 예상되고 있으나, 현재 발전용 연료의 연소특성 평가는 주로 실험실적 기초 시험에 의존함에 따라 정확한 평가가 곤란한 실정이므로 시험연소로를 이용하여 각종 연소특성을 비교 평가하여 탄종별 최적 연소조건 규명과 적정 흔탄비에 대한 Data Base를 구축하고자 한다.(중략)

• Fire Science and Engineering
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• v.20 no.4 s.64
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• pp.26-32
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• 2006

Nowadays in Korea, KS F 2271 has been using for the test of fire safety performance of sandwich panels. Smoke toxicity test is the test for the toxicity evaluation of smoke and hazardous gas, caused by combustion of building materials and finishing materials. Smoke toxicity can be evaluated by the mean incapacitation time of mice; however this method is not a quantitative way. This test result can be influenced by the health status of mice and test condition. Specific optical density can be quantitatively measured by ISO 5659-2 single chamber method and toxic gases can be quantitatively measured by FTIR analysis. In this study, specific optical density of sandwich panel insulations, which are widely used in Korea, were tested using the ISO 5659-2 single chamber test method and compared with each test. Also, in the second test of three tests for each specimen, FTIR analysis was performed and quantitative test results(HCl, $NO_2$, etc) were compared with each test result.

• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.49-56
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• 2005

Hot firing performance test of hydrazine decomposition catalyst used for monopropellant thruster of the satellite and the launch vehicle was performed. Test equipment for catalyst test was developed in collaboration with Hanwha Corp., reaction delay time, catalyst activity and granule stability of the catalyst firing performance were measured and analyzed with the equipment. In addition, the current development of prototype catalyst is introduced.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.3
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• pp.48-55
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• 2014

In present study, design and hot fire tests of the pryostarter are conducted. To prevent the turbopump RPM overshoot, regressive mass flow rate profile is applied. Sudden decrease of the mass flow rate at the end of the propellant burning is realized as well. Firing test results show good agreements with the design requirements. Through the study with ignition substance variations, combustion products and ignition performances are improved.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.108-111
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• 2017

High performance upper stage engine is necessary for space launch vehicles of geostationary orbit, and staged combustion cycle engine is suitable due to high specific impulse. Technology demonstration model for 9 tonf class staged combustion cycle engine, which is consisted of turbopump, preburner, combustion chamber and supply system, was assembled, and hot-firing test was conducted for three seconds in Upper-stage Engine Test Facility of Naro Space Center. Ignition, combustion and shut down of engine system was performed normally, and its performance parameters were evaluated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.11a
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• pp.209-212
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• 1996

접촉발화성 액체추진제를 사용하는 소형 추진기관의 성능을 확인하기 위해 핵심 부품의 상온 성능 시험 및 추진기관 조립품의 연소성능시험을 실시하여 추력 400 파운드급의 로켓엔진의 설계성능을 확인하였다. 로켓엔진의 성능측정은 요소분사기의 미립화, 혼합성능의 측정을 위한 상온수류시험과 추진기관 조립체의 지상연소시험으로 실시하였으며, 연소성능은 산화제로 질산을 연료로는 아민계 혼합물로 구성된 접촉발화형 이원 액체추진제를 사용하여 가압방식에 의해 연소실에 분사하는 방법으로 수행하였다. 성능시험결과는 설계성능 및 이상성능과 비교함으로서 이들의 상관관계를 파악하였다.