• 한국산업융합학회 논문집
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• 제5권4호
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• pp.295-299
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• 2002

Specific fuel consumption or specific power output characteristics of an internal combustion engine are likely, in conventional applications, the most important operating criteria. In this work, the test method for the engine performance was introduced in a compression ignition(diesel) engine.

• 한국추진공학회지
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• 제18권1호
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• pp.85-90
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• 2014

액체 추진 엔진 개발을 위해서는 서브시스템인 연소기 개발이 선행되어야 하고 설계 및 제작된 연소기의 성능 검증은 연소기 연소시험설비(CCTF)에서 수행된다. 연소기 연소시험설비는 로켓 엔진의 연소기를 개발하기 위한 시험 설비로 산화제로는 액체산소(Liquid Oxygen)를 사용하고 연료로는 케로신(Kerosene)을 사용한다. 이러한 추진제는 질소가스를 사용하여 고압으로 추진제 런탱크를 가압하여 연소실로 공급하게 된다. 우주센터에 구축 예정인 연소기 연소시험설비에 대한 상세설계가 수행되었으며, 본 논문에서는 고압가스 공급시스템에 대한 설계 결과를 소개하고자 한다.

• 대한기계학회논문집B
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• 제20권10호
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• pp.3381-3386
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• 1996

The engine performance and combustion characteristics of methanol blended fuel in spark ignition engine were discussed on the basis of experimental investigation. The effects of methanol blending fuel on combustion in cylinder were investigated under various conditions of engine cycle and blending ratio. The results showed that the engine performance was influenced by the methanol blending ratio and the variations of operating conditions of test engine. The increase of fuel temperature brought on the improvement of combustion characteristics such as cylinder pressure, the rate of pressure rise and heat release in an engine. The burning rate of fuel-air mixture, the exhaust emissions and the other characteristics of performance were discussed also.

• 한국분무공학회지
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• 제4권3호
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• pp.24-31
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• 1999

The engine performance and combustion characteristics of methanol blended fuel of spark ignition engine were discussed on the basics of experimental investigation. The effects of methanol blending fuel on combustion in cylinder were investigated under various conditions of engine cycle and blending fuel on combustion in cylinder were investigated tinder various conditions of engine cycle and blending ratios. The results showed thai the engine performance was influenced by the methanol blending ratio and the variations of operating conditions test engine. The increase of fuel temperature brought on the improvement of combustion characteristics such as cylinder pressure. the rate of pressure rise and heat release in an engine. The burning rate of fuel-air mixture, the exhaust emissions and the other characteristics of performance were discussed also.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.94-98
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• 2017

고성능 상단엔진 개발을 위한 9톤급 다단연소사이클 엔진의 선행연구가 진행 중에 있다. 다단연소사이클 엔진 기술검증시제(TDM0)를 제작을 완료하여, 나로우주센터 엔진 연소시험설비에서 예연소기와 터보펌프로 구성된 파워팩 연소시험과 주 연소기까지 장착된 엔진 연소시험을 차례로 수행하였다. 다단연소사이클 엔진 유공압 라인의 진공화 과정과 연소시험에서 나타난 터보펌프의 및 유공압 라인의 특성을 간략히 기술한다.

• 한국연소학회지
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• 제22권1호
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• pp.46-52
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• 2017

High-frequency combustion instabilities may occur during the development of feasible engine combustors. These instabilities can result in irreparable damages to the wall of combustors or the degradation of engine performance. So, it is essential to identify injectors that have high stability characteristics during the early stages of development. The objective of present study was to assess the stability of coaxial injectors and an impinging injector with different recess lengths in order to develop stable injectors optimally. Stability margin was evaluated based on the distance from operating condition to the unstable regions. A simulating combustion test method was used to analyze the stability of injectors. A small-scale combustion chamber was designed to simulate the first tangential acoustic mode of the actual combustor. Gaseous oxygen and a mixture of methane and propane were used as simulant propellants to satisfy their flow similarity to the actual propellants of a combustor in a liquid rocket combustor. The results indicated that injectors having small recess lengths showed relatively large combustion stability margins. For the injectors of large recess lengths, instability regions with large and super-large amplitude oscillations were observed. Thus, injector with shorter recess lengths had a higher stability than that of longer one due to the different mixing processes.

• 한국연소학회:학술대회논문집
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• 한국연소학회 1997년도 제15회 KOSCO SYMPOSIUM 논문집
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• pp.135-151
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• 1997

The preliminary design and performance test for determining dimensions of gas turbine combustor were investigated. The combustor design program was developed and applied to design our combustor. and detailed design for determining of swirler. dome and liner holes were performed experimentally. The swirler. which govern the combustion characteristics of combustor, was determined $40^{\circ}$ as swirl angle at first performance test. After second performance test the swirler was re-determined by 24 mm i.d.. 34 mm o.d., and swirl angle of $45^{\circ}$. The geometry of liner holes were determined by considering the flame stability and recirculation zone size. It was found that flame can be more easily stabilized by adjusting the swirier dimensions rather than liner holes. The geometry of swirler and liner holes were re-determined by final performance test with dilution holes. Also. the performance of combustor was evaluated by analysis of exhaust gases.

• 한국건축시공학회:학술대회논문집
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• 한국건축시공학회 2018년도 춘계 학술논문 발표대회
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• pp.45-46
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• 2018

The fire at the pilotis parking lot shows the fire propagation paths that are propagated to the ceiling materials and insulation materials and propagated through the external walls. In addition, there is a high risk of fire caused by vehicles with high combustion loads spreading throughout the parking lot. In particular, the omission of the ceiling materials at the parking lot in recent fire cases has contributed to the spread of the fire. In this study, the combustion performance of the ceiling materials between the insulation material and the vehicle is considered to prevent fire from spreading. Based on field research, the type of ceiling material used in the piloti structure showed that SMC ceiling materials have the highest percentage. Combustion performance test (KS F ISO 5660-1) was carried out on the SMC ceiling materials and the AL ceiling materials to review the fire safety of the ceiling finish based on the field investigation. The results of the test showed that the SMC ceiling materials has a THR 28.973[MJ/㎡] and peek HRR 273.93 [kW/㎡], while the AL ceiling material has a THR 0.584[MJ/㎡] and peek HRR 15.215[kW/㎡].

• 한국화재소방학회논문지
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• 제26권6호
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• pp.85-91
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• 2012

건축물에서 화재 시 인명과 재산의 피해를 줄이기 위해서는 초기의 화염의 확산을 억제하는 것이 우선되어야 한다. 화염의 확산을 방지하기 위한 화재확산방지 대책은 일반적으로 방화구획에서의 구조부재의 내화 성능 확보, 마감재료의 연소 성능에 따른 사용 제한 등이 있다. 마감재료의 연소 성능 판단은 화염의 확산을 판단하기 위해 가장 기초적인 화재 안전 설계이지만 국내의 연소 시험은 시편 크기의 화재 시험 방법으로 연소 성능을 판단하고 있어 샌드위치패널 등과 같은 복합재료의 연소 성능을 판단하기에는 많은 제약을 가지고 있다. 특히 외벽 마감재료의 경우 내부 마감재료에 비해 드라이비트, 알루미늄복합패널, 메탈패널 등과 같은 다양한 복합재료 등이 사용되고 있기 때문에 본 연구에서는 외벽 마감재료의 국제시험규격인 ISO 13785-2 시험방법을 통해 외벽 마감재료의 실물 화재 실험을 통해 외벽 마감재료의 수직화재 확산 특성을 판단하고자 하였다.

• 한국추진공학회지
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• 제22권4호
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• pp.18-23
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• 2018

나로우주센터에 구축/개발된 3단 엔진 연소시험설비에서 다단연소사이클 액체 로켓엔진의 시험을 수행하였다. 수류시험과 점화시험, 연소시험이 이루어졌으며 예연소기의 연소압력 제어를 위한 TTR의 개도를 $143^{\circ}$에서 $185^{\circ}$까지 변화시키며 시험을 수행하였다. 시험 결과 엔진의 주요성능과 TTR 개도에 의한 수력학적 변화를 확인하였지만 연소압력의 제어성 확인을 위한 결과는 얻지 못하였다. 향후 본 논문의 연구에서 도출된 개선점을 보완한 예연소기 압력제어 연구가 이루어질 것이다.