• 한국가스학회지
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• 제2권1호
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• pp.14-22
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• 1998

본 연구에서는 LNG 저장탱크에서 액면화재(pool fire) 발생시 복사열속(radiation flux)의 정량적인 예측과 복사열 피해를 줄이는 방법을 제안하기 위하여 RISC모델을 사용하여 여러 조건에서 복사열속을 계산하였다. 모델 예측결과 LNG 탱크의 액면화재에 의한 복사열 피해에 가장 큰 영향을 미치는 인자는 풍속임을 알 수 있었다. 화염과 피해 대상물사이의 복사피해 정도는 높은 풍속에서 보다 낮은 풍속에서의 풍속변화에 따라 크게 변하였다. 또한 액면화재 발생시 복사열 피해는 탱크 또는 공장 주위에 방풍시설을 함으로써 크게 줄일 수 있음을 알 수 있었다. 방풍시설은 다른 방법들 보다 경제적이기 때문에 냉각시설 및 소방시설과 연계하여 가스 저장탱크 주위에 설치하는 것이 바람직하다.

• 한국통신학회논문지
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• 제35권2B호
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• pp.197-209
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• 2010

본 논문은 10 Gb/s $\times$ 4 레인으로 구성되는 40 인치 FR-4 백플레인 채널을 설계 및 분석하고, 이를 바탕으로 제안된 40 Gb/s 급 수신 적응 등화기 (Receive and Adaptive Equalizer), 고속 등화 알고리즘 설계 및 시뮬레이션 결과에 관하여 기술한다. 백플레인을 통과하는 40 Gb/s 고속 데이터 통신 채널을 위해 FFF를 사용하지 않는 DFE의 10Gb/s 4채널의 수신 등화기가 제안된다. 본 수신 & 등화기는 46 인치 백플레인 채널의 수신종단에서 등화를 수행하기 위한 IEEE Std P802.3ba 표준 기반 등화기 요구조건을 만족한다.

• 대한기계학회논문집
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• 제18권4호
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• pp.912-919
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• 1994

The engine combustion is one of the most important processes affecting performance and emissions. One effective way to improve the engine combustion is to control the motion of the charge inside a cylinder by means of optimum induction system design, because the flame speed is mainly determined by the turbulence at compression(TDC) process in S.I. engine. It is believed that the tumble and swirl motion generated during intake stroke breaks down into small-scale turbulence in the compression stroke of the cycle. However, the exact nature of this relationship is not well known. This paper describes the tumble flow measurements inside the cylinder of a 4-valve S.I. engine using laser Doppler velocimetry(LDV) under motoring(non-firing) conditions. This is conducted on an optically assesed single cylinder research engine under motored conditions at an engine speed of 1000rpm. Three different cylinder head intake port configurations are studied to develop a better understanding the tumble flow generation, development, and breakdown mechanisms.

• 한국추진공학회지
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• 제10권2호
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• pp.115-128
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• 2006

스크램제트 추진기술에 대한 최근 개발동향과 주요기술을 분석하였다. 스크램제트엔진은 지난 10여년간 급속한 기술 발전으로 지상시험에서 비행시험 단계에 접어들고 있으며, 수년 내 실용시험을 목표로 활발하게 연구개발 중이다. 광범위한 비행 마하수를 만족하는 이중연소램제트와 이중모드램제트 형태의 엔진은 각각 군용과 민수용으로 개발되고 있으며, 복합엔진은 차세대 우주발사체의 대안으로 개발되고 있다. 엔진 작동 특성의 미케니즘에 대한 정확한 이해와 이에 상응되는 기술, 흡열연료 및 CSiC 복합재료를 사용한 내열 문제 해결, 가변 흡입구와 노즐을 이용한 안정된 추진력 구현을 목전에 두고 있다.

• Coupled systems mechanics
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• 제1권3호
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• pp.285-295
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• 2012

In this paper, two types of porous burners with radial and axial flow have been modeled numerically and compared. For this purpose, governing equations were solved one-dimensionally for methane-air premix gas. The mechanism used in simulating combustion phenomenon was 15 stage reduced mechanism based on GRI3.0. In order to compare the two burners, the inlet flow rate and fuel-air ratio have been assumed equal for the two burners. The results of the study indicated that reduction in speed and increase in cross-section area in the direction of flow have a considerable influence on the behavior of radial burner in comparison to axial burner. Regarding temperature distribution inside the burner, it was observed that the two above mentioned factors can be influential in temperature of flame propagation region. Also, regarding distribution of CO and NO emission, the results indicate that the porous radial burner has lower emissions in comparison to the axial once. The output radiative heat transfer efficiency of the two burners was also compared and in this case also even the radial porous burner was found to be preferable.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회B
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• pp.3306-3310
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• 2007

Many researches have been studied on in-cylinder flow as one of dominant effects for an engine combustion. Specially because the combustion flame speed is mainly determined by the turbulence at the end of compression process. Tumble and Turbulence ahead of combustion is very important phenomenon. As this phenomenon make research certainly, combustion condition will effectively be improve. This paper describes analytical results of the tumble flow, intensity, turbulence inside the cylinder of maritime engine. 3-D computation has been performed by using STAR-CD v3.26 solver and es-ice

• 한국연소학회:학술대회논문집
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• 한국연소학회 2014년도 제49회 KOSCO SYMPOSIUM 초록집
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• pp.215-218
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• 2014

High combustion efficiency of hydrogen could make it an ideal source of green energy in the future. At this time, high pressure vessel is the most reasonable method of storing hydrogen. However, such a high pressurized vessel could pose a critical threat if ruptured. For this reason, it is important to understand the mechanism of hydrogen's self-ignition when a high-pressure hydrogen released into air. This paper presents several visualization images as experimental results using high-speed camera. From the visualization images, the ignition is initiated near rupture disk immediately after failure of disk. And the initial ignition and flame is stronger as a rupture pressure increases. However, this ignition region do not affect the general self-ignition mechanism when a high-pressure hydrogen is released into air through tue after failure of disk.

• 대한기계학회논문집
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• 제16권1호
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• pp.175-179
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• 1992

본 연구에서는 LPG 기관을 천연가스 이용기관으로 변경하고자 할 때 발생하는 출력 감소를 보안하기 우하여, 공기연료 혼합비 조절, 점화시기조절, 과급효과 방법에 의한 출력향상 효과를 파악하였다.

• International Journal of Automotive Technology
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• 제6권6호
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• pp.585-590
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• 2005

The effects of spark timing and exhaust valve timing change on exhaust gas temperature during cold start period of an SI engine are studied through engine bench tests. The exhaust gas temperature increases when the spark timing or valve timing are retarded individually, due to late combustion or slow flame speed. Therefore, exhaust gas temperature shows a large increase when the two timings are retarded simultaneously. However, it is considered that combustion stability during cold start deteriorated under these retarded conditions. To increase exhaust gas temperature for fast warmup of catalysts while maintaining combustion stability, an optimal condition for spark and valve timing retard should be applied for the cold start period.

• 한국항공운항학회지
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• 제22권1호
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• pp.1-6
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• 2014

In this paper, controller propose to prevent compressor surge and improve the transient response of the fuel flow control system of turbojet engine. Turbojet engine controller is designed by applying Artificial Neural Network PID control algorithm and make an inference by applying Levenberg-Marquartdt Error Back Propagation Algorithm. Artificial Neural Network inference results are used as the fuel flow control inputs to prevent compressor surge and flame-out for turbojet engine for UAV. High Gain Observer is used to estimate to compressor rotation speed of turbojet engine. Using MATLAB to perform computer simulations verified the performance of the proposed controller. Response characteristics pursuant to the gain were analyzed by simulation.