• 대한기계학회논문집
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• 제18권4호
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• pp.933-945
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• 1994

A shock-wave in a supersonic flow can be theoretically determined by a given pressure ratio at upstream and downstream flowfields, and then the obtained shock-wave is stable in its position. Under the practical situation in which the shock-wave interacts with the boundary layer along a solid wall, it cannot, however, be stable even for the given pressure ratio being independent of time and oscillates around a time-mean position. In the present study, oscillations of a weak normal shock-wave in a supersonic diffuser were measured by a Line Image Sensor(LIS), and they were compared with the data of the wall pressure fluctuations at the foot of the shock-wave interacting with the wall boundary layer. LIS was incorporated into a conventional schlieren optical system and its signal, instantaneous displacement of the interacting shock-wave, was analyzed by a statistical method. The results show that the displacement of an oscillating shock-wave increase with the upstream Mach number and the dominant frequency components of the oscillating shock-wave are below 200 Hz. Measurements indicated that shock-wave oscillations may not entirely be caused by the boundary layer separation. The statistical properties of oscillations appeared, however, to be significantly affected by shock-induced separation of turbulent boundary layer.

• 대한기계학회논문집B
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• 제21권5호
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• pp.602-614
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• 1997

In order to evaluate the effects of equivalence ratio, initial pressure and temperature on the laminar flame propagation process, and combustion radicals characteristics, experimental approaches are carried out in methane-air premixture using a constant volume chamber. Local and average radical intensities were measured to determine the time and spatial correlations between each radicals; C $H^{*}$(431 nm), $C_{2}$$^{*}$ (517 nm) and O $H^{*}$(309 nm) . The results are showed that two kinds of equation were proposed for the cases of continuous flame and intermittent flame type to evaluate actual equivalence ratio using relative intensities with each radicals. Both equations were agreed with actual equivalence ratio within 10% errors range. And schlieren photo and CCD image were compared with flame sizes at equivalence ratio 1.0.o 1.0.

• 한국수소및신에너지학회논문집
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• 제23권5호
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• pp.493-502
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• 2012

Syngas laminar burning velocity measurements were carried out at atmospheric pressure and ambient temperature using the Bunsen flame configuration with nozzle burner as a fundamental study on flame stability of syngas fuel. Representative syngas mixture compositions ($H_2$:CO) such as 25:75%, 50:50% and 75:25% and equivalence ratios from 0.5 to 1.4 have been conducted. Average laminar burning velocities have been determined by the stabilized nozzle burner flames using the angle method, radical surface area method and compared with the data obtained from the other literatures. And the results of each experimental methodologies in the various composition ratios and equivalence ratios were coincided with the result of numerical simulation. Especially, it was confirmed that there was necessary to choice a more accurate measurement methodology even the same static flame method for the various composition ratios of syngas fuel including hydrogen. Also, it was reconfirmed that the laminar burning velocities gradually increased with the increasing of hydrogen content in a fuel mixture.

• 대한기계학회논문집B
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• 제34권11호
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• pp.1005-1013
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• 2010

본 연구는 HCCI 엔진의 운전조건을 고려한 혼합연료의 감압비등 분무제어방법을 평가하기 위하여 수행하였다. 2상영역이 존재하는 혼합연료는 고비점성분의 증발촉진과 함께 연료분무의 급격한 증발을 유도할 수 있는 감압비등분무를 이용함으로써 저온 및 저밀도장에서 혼합기형성과정의 제어가 가능하다. HCCI 엔진은 이러한 분위기조건에서 연료를 조기분사하기 때문에 착화성이 높은 경유와 휘발성이 높은 가솔린성분으로 함유한 혼합연료의 감압비등현상을 이용함으로써 액체연료의 분열, 미립화와 같은 물리적 제어 및 착화연소에 의한 화학적 제어를 실현할 수 있다. 본 연구는 혼합연료의 성분과 몰분율을 주요변수로 설정하여 정적용기 내에 분사된 연료분무의 감압비등현상을 슐리렌 화상 및 Mie 산란광을 촬영한 후, 화상처리과정을 통하여 이루어졌다. 그 결과로 감압비등현상은 비교적 저온 및 저밀도장에서 분무구조가 크게 변화함을 알 수 있었으며, 조기 연료분사시기에서 감압비등분무를 이용한 혼합기형성을 제어함으로써 HCCI 연소에 적용이 가능할 것으로 분석하였다.