• 한국추진공학회지
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• 제15권2호
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• pp.23-28
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• 2011

제트연료변경에 따른 엔진 운용 특성 변화를 살펴보기 위해 JP-8 연료와 JP-S 연료를 사용하여 소형터 보제트엔진의 지상시험 및 고도시험을 수행하였다. 비중이 18% 높은 JP-S 연료에 대한 연료조절시스템 특성은 동일 연료공급명령에 대한 실 연료공급량이 JP-8 연료보다 8% 많이 공급되었다. 시동특성은 연료조절시스템의 명령 대비 공급량의 차이로 인한 점화시점 및 엔진 회전수 가속율 등의 변화를 제외하고는 유사한 특성을 보였다. 정상상태 성능 특성은 순 추력의 일부 구간을 제외하고는 순 추력과 공기유량, 배기가스온도 등 대부분의 엔진 성능 변수가 1% 이내로 유사하였으나 연료소모량만은 연료의 발열량 차이로 인해 최대 5 %이상 차이가 발생하였다. 이를 동일 추력 대비 비 연료소모율로 비교할 때 지상시험에서는 약 1.1~2.6 %, 고공환경시험에서는 5 % 이상 차이가 발생하였다.

• 한국추진공학회지
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• 제14권1호
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• pp.56-64
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• 2010

한국형 발사체 (KSLV-II, Korea Space Launch Vehicle II)에 적용될 액체로켓엔진의 시스템 설계를 수행하였다. 진공 추력 76톤, 진공 비추력 297 sec인 본 엔진은 가스발생기 사이클로 터보펌프 가압방식을 적용한다. 연소기는 재생냉각형이며 연소압 60 bar이다. 추진제는 액체산소/케로신 조합이다. 엔진 시동은 파이로시동기를 이용하며 연소기 점화는 TEA (TriEthylAluminium)를 사용한다. 에너지 밸런스 해석을 통해서 엔진 시스템 성능과 서브시스템 요구 성능을 결정하였다. 연소압, 비추력 및 엔진무게의 적정성을 사례분석을 통하여 평가하였다. 터보펌프-가스발생기 연계시험과 비교하여 시동 해석방법을 검증함으로써 향후 적용을 위한 준비를 마쳤다. 본 엔진은 능동제어를 적용하지 않으며 모드해석과 분산해석을 통해서 성능 보정 방안을 확정하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2010년도 제35회 추계학술대회논문집
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• pp.410-415
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• 2010

제트연료변경에 따른 엔진 운용 특성 변화를 살펴보기 위해 JP-8 연료와 JP-S 연료를 사용하여 소형터보제트엔진의 지상시험 및 고도시험을 수행하였다. 비중이 18% 높은 JP-S 연료에 대한 연료조절 시스템 특성은 동일 연료공급명령에 대한 실 연료공급량이 JP-8 연료보다 8% 많이 공급되었다. 시동 특성은 연료조절시스템의 명령 대비 공급량의 차이로 인한 점화시점 및 엔진 회전수 가속율 등의 변화를 제외하고는 유사한 특성을 보였다. 정상상태 성능 특성은 순 추력의 일부 구간을 제외하고는 순추력과 공기유량, 배기가스온도 등 대부분의 엔진 성능 변수가 1% 이내로 유사하였으나 연료소모량만은 연료의 발열량 차이로 인해 최대 5 %이상 차이가 발생하였다. 이를 동일 추력 대비 비 연료소모율로 비교할 때 지상시험에서는 약 1.1~2.6 %, 고공환경시험에서는 5 % 이상 차이가 발생하였다.

• 한국항공우주학회지
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• 제37권10호
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• pp.1038-1047
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• 2009

추력 30톤급 펌프공급방식 액체로켓엔진을 위한 가스발생기 개발 과정에 관하여 기술하였다. 액체산소와 케로신을 추진제로 연료 과농 조건에서 작동하는 가스발생기의 개발을 위해 분사기 개발에서부터 시작하여 축소형, 실물형 개발시제를 거쳐 가스발생기 단품 개발을 성공적으로 완료하였다. 가스발생기 설계 과정에서 다양한 해석적 방법을 적용하였으며 점화 시험, 연소성능 및 연소안정성 평가시험, 내구성 평가시험 등을 통해 가스발생기의 성능요구사항을 시험적으로 검증하였다. 개발된 가스발생기는 연소압 및 혼합비 운용 영역 내에서 안정적으로 작동하며 성능 및 수명 요구조건을 만족시킴을 확인하였다.

• 한국자동차공학회논문집
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• 제6권3호
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• pp.1-10
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• 1998

In this paper, we investigated the improvement of characteristics of knock, emission and fuel consumption rate by optimizing the location and size of water transfer holes in cylinder head gasket without change of engine water jacket design itself. The cooling system was modified in the direction of reducing the metal temperature in the head and increasing the metal temperature in the block. The optimization of water transfer holes in cylinder head gasket was obtained by "flow visualization test". The water transfer holes were concentrated in front side of the engine in order to reduce thermal boundary layer in the water jacket of No. 2 and No. 3 combustion changer in the cylinder head, which would have a large knock intensity, and increase thermal boundary layer in the water jacket of the cylinder block. When the modified coolant flow pattern was applied as proposed in this paper, the knock characteristic was improved. The spark timing was advanced up to 2$^{\circ}$ in low and middle speed range at a full load. In addition, HC emission at MBT was reduced by 5.2%, and the fuel consumption rate was decreased up to 1% in the driving condition of 2400 rpm and 250 KPa. However, since this coolant flow pattern mentioned in this paper might deteriorate the performance of vehicle cooling system due to the coolant flow rate reduction, a properly optimized point should be obtained. obtained.

• 한국유체기계학회 논문집
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• 제19권6호
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• pp.43-49
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• 2016

A performance analysis of a gasoline engine with a 2-stage turbocharger system for unmanned aerial vehicle(UAV) was conducted. One dimensional system analysis was conducted for the requirements of turbochargers and adequate turbochargers were selected from commercially available models for automobiles. Modeling and simulation were performed by Ricardo WAVE. Gasoline engine modeling was based on a 2.4 L 4-cylinder engine specification. The selected turbochargers and intercoolers were added to the engine model and simulated at 40,000 ft altitude condition. The results of the engine model and 2-stage turbocharger system model simulation showed break power 93 kW which is appropriate power required for the engine operation at the ambient conditions of 40,000 ft altitude.

• 한국수소및신에너지학회논문집
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• 제28권1호
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• pp.92-97
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• 2017

Kerosene (Coal oil) is a particularly attractive fuel because it is widely used to power jet engines of aircraft as jet fuel and some rocket engine. This paper describes the performance and emission characteristics according to the collant temperature of combustion chamber head of spark ignition engine fuelled with kerosene. As a result, the following knowledge is obtained. As the collant temperature of combustion chamber head is decreased, torque, volumetric efficiency and brake specific fuel consumption have been increased. When coolant temperature of combustion chamber lower, THC emission increased but CO and $NO_x$ emission decreased.

• 한국자동차공학회논문집
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• 제10권1호
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• pp.24-31
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• 2002

An experimental study was conducted to investigate the effects of EGR (Exhaust Gas Recirculation) variables on performance and emission characteristics in a 2-liter 4-cylinder spark-ignition LPG fuelled engine. The effects of EGR on the reduction of thermal loading at exhaust manifold were also investigated because the reduced gas temperature is desirable for the reliability of an engine in light of both thermal efficiency and material issue of exhaust manifold. The steady-state tests show that the brake thermal efficiency increased and the brake specific fuel consumption decreased with the increase of EGR rate in hot EGR and with the decrease of EGR temperature in case of cooled EGR, while the stable combustion was maintained. The increase of EGR rate or the decrease of EGR temperature results in the reduction of NOx emission even in the increase of HC emission. Furthermore, decreasing EGR temperature by $180^{\circ}C$ enabled the reduction of exhaust gas temperature by $15^{\circ}C$ in cooled EGR test at 1600rpm/370kPa BMEP operation, and consequently the reduction of thermal load at exhaust. The optimization strategy of EGR application is to be discussed by the investigation on the effect of geometrical characteristics of EGR-supplying pipe line.

• 한국군사과학기술학회지
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• 제15권3호
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• pp.241-249
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• 2012

Performance analysis of the interior ballistics has been conducted using the 1-D numerical code called IBcode according to the various conditions such as length of ignition-gas injector, amount of ignition-gas, mass of projectile, and drag force of projectile. In case of the length of ignition-gas injector, the 25~100 % of the full-injector length has been considered as well as the mass & mass flow of the ignition-gas. The mass of the projectile 5~70 kg and its drag force of 0~69 MPa have been also considered. Variables such as breech & base pressure, negative differential pressure and muzzle velocity for the performance analysis have been sorted, too. Firing conditions for the optimal performance have been investigated through these variables.

• 한국자동차공학회논문집
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• 제10권4호
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• pp.77-84
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• 2002

For the purpose of obtaining a fundamental data which is needed to develope the port injection type charged LPLi engine system, we manufactured intake port injection system of liquid charging LPG and modified heavy duty single cylinder LPLi engine from heavy duty diesel engine. Engine output and emission characteristics were analyzed under variable air/fuel ratio and charging pressure. Since LPG is consisted of propane and butane, we investigated combustion characteristics using this two kinds of fuel. From the result of charging engine performance test, engine torque increase about 30% ∼ 40% with 0.3bar charging pressure. In low speed condition, as charging pressure increase, combustion stability improve ill lean bum condition, but, in high speed condition, combustion stability make worse in lean bum condition. We know that engine output decreased rapidly from the condition of air excess ratio 1.3. In addition, we measured emission characteristics under the lean bum and charging condition. From this experiment, we found that CO emission is out of the question in the range from stiochiometric to lean burn and charging condition, but charging pressure has influence on HC emission.