• 한국신재생에너지학회:학술대회논문집
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• 2010.11a
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• pp.114.2-114.2
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• 2010

마이크로 반응기술은 작은 반응기 부피, 높은 열전달, 넓은 반응 면적/부피 및 정확한 반응시간 조절이 가능하기 때문에 화학공정의 고집적화, 반응 선택도의 향상 및 안전도 향상을 꾀할 수 있는 장점이 있다. 이러한 마이크로 반응 기술을 중소형 천연가스 및 국내에서 소규모로 국지적으로 발생하는 메탄의 활용 방안으로서 개발함은 청정 합성유를 제조함으로서 석유 자원의 고갈과 고유가에 대비하여 에너지 자원의 다변화 및 자립을 확보 할 수 있다. 본 연구에서는 마이크로 반응기술을 적용한 미세 유로 반응기(Micro Channel Reactor)를 사용하여 메탄 스팀 개질 반응 특성을 연구하였다. 미세유로 반응기는 내부 홀이 존재하는 plate를 적층함으로 반응기내에 반응가스가 이동할 수 있는 미세유로가 존재하게 하였다. 이러한 미세유로는 반응기의 크기가 작음에도 반응기내에서 반응가스가 충분히 반응할 수 있는 시간과 높은 열전달 효율을 가질 수 있게 한다. 메탄 스팀 개질 반응에 사용된 촉매는 Ni 촉매를 사용하였고, 반응에 필요한 열원으로는 수소 연소에서 발생한 열을 사용하여 반응을 유도하였다. 본 반응기는 외부의 열원을 사용하지 않고, 반응기 내부의 수소 연소에서 발생한 열을 사용함으로 적은 발생 열만으로 메탄 스팀 개질 반응에 필요한 에너지를 얻을 수 있고, 열의 손실이 적다. 또한 메탄 스팀 개질 반응으로 발생한 일부의 수소를 열원으로 이용하여 에너지 사용면에서도 효율적인 반응 공정이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.148-151
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• 2007

We made two injectors that were equal to all design except for existence or nonexistence of swirl chamber of fuel part, because we want to find cooling characteristics at the injector face according to existence or non existence of swirl chamber of fuel part. And we set regenerative cooling channel in injector face for protecting injector face for prolonged combustion time. Two injectors were performed hot firing test, and then we compared cooling characteristics of two injectors. Also we compared O/F ratio effects on cooling characteristics and combustion characteristics.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.6
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• pp.571-579
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• 2009

For the flow analysis of reactive compressible media involving energetic materials and metallic confinements, a Hydro-SCCM (Shock Compression of Condensed Matter) tool is developed for handling multi-physics shock analysis of energetics and inerts. The highly energetic flows give rise to the strong non-linear shock waves and the high strain rate deformation of compressible boundaries at high pressure and temperature. For handling the large gradients associated with these complex flows in the condensed phase as well as in the reactive gaseous phase, a new Eulerian multi-fluid method is formulated. Mathematical formulation of explosive dynamics involving condensed matter is explained with an emphasis on validating and application of hydro-SCCM to a series of problems of high speed multimaterial dynamics in nature.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.305-309
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• 2008

This experimental study has been conducted to investigate the installation of the vertical flame holder shape in ramjet combustor, which affects on the film cooling effectiveness. All slot position, the film cooling effectiveness decreases because of the shear layer and high turbulence intensity between separated flows and coolant flows. When the flame holder is installed, film cooling effectiveness decreases abruptly on the beginning of the slot exit region due to the mixing effect. As the blowing rate increases, the film cooling effectiveness is increased for all cases due to the augmented momentum of injected coolant from the slot.

• 한국연소학회:학술대회논문집
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• 2003.05a
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• pp.103-108
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• 2003

The control of flame shapes in a laminar pre-mixed flame has been experimentally investigated for propane/air pre-mixed laminar flames. Flames of different size and shapes are observed with heated wires or by controlling the equivalence ratio and flow rate of a mixture. The characteristics of the partitioning of a flame or the merge of flames are analyzed and explained by considering the balance between laminar flame speed and upstream mixture velocity. A combustor might be sized down while maintaining its heat production rate the same by partitioning a flame established in it. When the equivalence ratio of mixture is decreased, individual flames are merged together and the upstream mixture velocity can be practically decreased on a nozzle having opening ratio less than unity. As a result, the flame shape is to he adjusted until the newly established balanced condition is satisfied, and then. the stable combustion can be achieved again.

• 한국연소학회:학술대회논문집
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• 2005.10a
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• pp.221-228
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• 2005

The tribrachial flame in laminar coflow jet has been investigated experimentally with unsteady propagating condition. In this experiment, we found that the tribrachial point has an angle of flame surface because the location of tribrachial point is not on the base point of flame but on the inclined surface of flame. This angle of Flame surface at tribrachial point are increasing when the flame is approaching to the nozzle exit. With considering this angle of flame surface, the radial velocity gradient can affect flame propagation speed by increasing flow-stretch effect. The propagation speed of tribrachial flame was calculated with including above stretch effect. The speed decreases with increasing velocity gradient due to the increment of stretch effect.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.256-259
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• 2007

In this paper, the combustion characteristics of hybrid rocket were studied with various port number of the cylindrical multi-port grain. For the regression rate case, as the port number increases, the both port regression rate and end-surface regression rate tend to increase. For the performance parameter case, as the port number increases, the O/F ratio tends to decreases and the specific impulse tends to increase.

• Journal of the KSME
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• v.25 no.4
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• pp.320-326
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• 1985

지난 10여년간의 연소분야에 대한 연구는 크게 세가지 방향에서 괄목할 만한 발전을 이루어 왔다. 그 첫째는 대용량 컴퓨터의 개발에 따른 수치해석능력의 신장을 들 수 있고, 둘째는 실 험에서 레이저를 이용한 비접촉 계측방법의 발달을 들 수 있다. 또한 이론적 관점에서는 1974 년이래 유체역학에서 프란틀의 경계층 이론에 비견될 수 있는 접합점근방법(matched asymptotic technique)를 이용하여 예혼합 화염의 전파속도, 확산화염의 구조 및 점화/소화현상, 열폭발문제, 화염의 안정성 등에 관한 엄격한 해석이 가능하게 되었다. 이로서, 종래의 현상적, 물리적 설 명으로 이해될 수 없었던 분야를 해석할 수 있었다. 이에 따라 본 강좌에서는 연소분야의 이 론적 연구에 초점을 맞추어 접합점근방법의 기초개념 및 해석방법을 소개하고자 한다. 이를 위해 2장에서 확산 화염과 예혼합 화염의 특성을 설명하고, 3장에서 화염면 극한의 해석, 4장에서 확산 화염의 구조해석을 통한 점화/소화현상 및 5장에서 예혼합 화염에의 응용 등을 소개한다.

• Transactions of the Korean Society of Automotive Engineers
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• v.9 no.4
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• pp.18-26
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• 2001

OSKA engine was developed to remove the dense core of injection sprays. The engine uses impinging spray on a small pip, which spray after impinging is broken into smaller drops and disperses into fee space in chamber. In this paper the pip size is analyzed to give more dispersion of spray and fuel vapor. The gas phase is modelled by the Eulerian continuum conservation equations of mass, momentum, energy and fuel vapour fraction. The liquid phase is modelled following the discrete droplet model approach in Lagrangian form, and the droplet wall interaction is modelled as a function of the velocity normal to impaction lands. The droplet distributions, vapor fractions and gas flows are analyzed for various injection pressure cases. Numerical results indicate that the land diameter of 5.6mm has the best performance of spray dynamics and vaporization in the test sizes.

• Transactions of the Korean Society of Mechanical Engineers
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• v.16 no.12
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• pp.2385-2394
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• 1992

Granular solid propellants having energy and fast burning rate produce great thrusts within extremely short time intervals. Thus numerical researchs prevailed rather than experimental. Using a 2-phase fluid dynamics model among 1-dimensional 2-phase models, a numerical program was set up to describe reacting flow fields, moving boundary with oscillating pressure waves and constitutive laws research. It deserves special emphasis that correlations of convective heat transfer coefficient and viscous drag force among constitutive laws are tested and discussed because slight variations of their constants make a large influence on their results. In this calculations, some of correlations make the large difference in results. Therefore constitutive laws for convective heat transfer coefficient and viscous drag force need more considerations with experiments.