• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2012.04a
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• pp.373-376
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• 2012

건축 재료가 다변화됨에 따라 화재 시 발생되는 연소가스 또한 다양해지고 있다. 그중 HBr은 NES 713과 BS 6853에서 연소 가스의 독성 평가를 위해 측정되는 독성가스이다. 특히 산업안전물질보건자료(MSDS)에서는 HBr가스를 흡입할 경우 화상을 일으키며 호흡부전, 두통 등을 유발시킬 수 있고 50ppm의 HBr가스에 노출된 사람은 생명과 건강에 즉시 영향을 받을 수 있는 매우 유독한 연소가스이다. 본 논문에서는 HBr 표준가스를 사용하여 건축법에서 규정한 가스유해성 시험결과와 HBr가스에 노출된 mouse의 병리학적 관찰 결과를 비교 분석하여 HBr의 연소 독성에 관하여 연구를 진행하였다.

• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2011.04a
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• pp.155-159
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• 2011

건축법에서 건축마감재료의 연소독성은 설치류(마우스)를 사용한 가스유해성시험으로 평가되고 있다. 최근 동물시험에 대한 최소화 및 대체시험개발의 필요성으로 인해 연소가스의 정량분석을 통한 독성지수연구가 요구되고 있다. 본 연구에서는 이미 철도차량에서 적용되고 있는 BS6853의 연소독성평가를 통해 기존 가스유해성시험결과의 상대적인 비교분석을 수행하여, 건축재료의 연소독성평가에 대한 다양한 가능성을 제시하고자 하였다.

• Transactions of the Korean Society of Automotive Engineers
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• v.3 no.6
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• pp.112-122
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• 1995

As an alternative fuel producing less exhaust emissions, natural gas is of interest for use both in SI and CI engines. The potential of natural gas fuelled dual-fuel engine is considered high enough. However, much effort has to be made so that gaseous fuel is used efficiently with simultaneous minimum use of pilot oil. Hence, a simplified three-dimensional model, using a finite volume method in cylindrical coordinates, has been developed to facilitate an understanding of the dual-fuel combustion phenomena and to predict the complex interactions between the pilot distillate and natural gas. The computer model was calibrated by comparing it with the experimental results obtained from diesel engine like combustion bomb tests. In the pre-mixed natural gas combustion, the fuel burning was highly reliant on the injection condition and subsequent burning nature of the pilot distillate.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.450-459
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• 2010

고체추진제의 첨가제 또는 연료로써 주로 사용되는 알루미늄 단일 입자 연소시험 장비를 제작하고 연소 실험을 수행하였다. 산화 알루미늄으로 피복된 금속입자는 약 30~100 ${\mu}m$의 크기를 사용하였다. 단일 입자는 Electrodynamic Balance (EDB) 방법에 의해 공중 부양된 상태로, 중력에 의한 영향이 배제되어 금속입자 고정용 또는 측정용 장치들의 접촉에 의한 열손실을 제거시켜 실험 정확도를 높였다. Standard Hyperbolic Electrodynamic Levitator (SHEL) 내에서 부양된 입자에 $CO_2$ 레이저를 사용하여 점화시킨 후, 입자로부터 방사되는 열복사를 이용한 two wavelength pyrometry를 적용하여 알루미늄 입자 크기에 따른 연소시간, 평균 화염온도, 점화온도, 점화시간을 획득하였으며, 단일 알루미늄 입자의 점화-연소특성을 평가하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.5-5
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• 1999

액체추진 로켓엔진의 개발과정에서 고주파 연소불안정은 엔진의 비행 안정성 및 성능의 보장을 위해 반드시 고려해야 하는 중요한 인자이다. 특히 액체추진 로켓엔진에 사용되는 다양한 추진제 조합 중 LOX/RP-1은 그 성능, 가용성, 경제성 등의 측면에서 우수한 추진제이지만 F-1 엔진의 개발과정에서와 같이 여타 추진제 조합에 비해 고주파 연소불안정 특성이 강하게 나타난다. 액체추진 로켓엔진의 음향불안정 특성 예측을 위해 다양한 방법이 제시되어 왔다. 그 중 n-$\tau$ 2 매개변수 법은 연소불안정 특성 예측에 실험적 고찰을 통한 간단한 연소모델을 포함하는 것으로 신속한 결과를 얻을 수 있다는 장점 때문에 엔진의 예비설계 및 본 설계과정에서 인정성 측면의 분석을 위해 널리 사용되고 있고 기존의 엔진 개발과정을 통해 그 신뢰성이 검증되어 왔다.

• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.22 no.3
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• pp.156-164
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• 2010

Combustion instability is a major issue in design of gas turbine combustors for efficient operation with low emissions. Combustion instability is induced by the interaction of the unsteady heat release of the combustion process and the change in the acoustic pressure in the combustion chamber. In an effort to develop a technique to predict self-excited combustion instability of gas turbine combustors, a new stability analysis method based on the transfer matrix method is developed. The method views the combustion system as a one-dimensional acoustic system with a side branch and describes the heat source as the input to the system. This approach makes it possible to use not only the advantages of the transfer matrix method but also well established classic control theories. The approach is applied to a gas turbine combustion system, which shows the validity and effectiveness of the approach.

• Proceedings of the SAREK Conference
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• 2009.06a
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• pp.1449-1457
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• 2009

Combustion instability is a major issue in design of co-generation gas turbine combustors for efficient operation with low emissions. Combustion instability is induced by the interaction of the unsteady heat release of the combustion process and the change in the acoustic pressure in the combustion chamber. In an effort to develop a technique to predict self-excited combustion instability of co-generation gas turbine combustors, a new stability analysis method based on the transfer matrix method is developed. The method views the combustion system as a one-dimensional acoustic system with a side branch and describes the heat source as the input to the system. This approach makes it possible to use not only the advantages of the transfer matrix method but also well established classic control theories. The approach is applied to a simple co-generation gas turbine combustion system, which shows the validity and effectiveness of the approach.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.5
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• pp.567-573
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• 2010

In this study, we evaluated the structural integrity and weight of a rocket motor with a torispherical dome by size optimization. Size optimization was achieved by first-order and sub-problem methods, using the Ansys Parametric Design Language (APDL). For rapid design verification, a modified 2D axisymmetric finite-element model was used, and the bolt pre-tension load was expressed as function of the ratio of the cross-sectional area. The thickness of the dome and the cylindrical part of the rocket motor were selected as the design parameters. Our results showed that the weight and structural integrity of the rocket motor at the initial design stage could be determined more rapidly and accurately with the modified 2D axisymmetric finite-element model than with the 3D finite-element model; further, the weight of the rocket motor could be saved to maximum of 17.6% within safety limit.

• Journal of Energy Engineering
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• v.16 no.3
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• pp.120-127
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• 2007

The purpose of this study is experimentally to analyze that the fuel mass fractions of multi-component mixed fuels have an effect on the characteristics of spray ignition and combustion under the ambient conditions of diesel combustion fields. The characteristics of ignition and combustion were investigated by chemiluminescence images and direct photography. The experiments were conducted in the RCEM(rapid compression expansion machine) with optical access. Multi-component fuels mixed with i-octane, n-dodecane and n-hexadecane are injected in RCEM by the electronic control of common rail injector. Experimental conditions set up 42, 72 and 112 MPa in injection pressure, 700, 800 and 900 K in ambient gas temperature. The results show that the ignition delay was dependent on high cetane number. In case of low ambient temperature, the more low boiling point fuels were mixed, the lower luminance regime had a remarkable effect and also shortened diffusion combustion by increasing heat release rate.

• Journal of the Korean Ceramic Society
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• v.41 no.1
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• pp.76-80
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• 2004

Nano-sized ZnO colloids were prepared by use of spray combustion method. for combustion reaction, $Zn(NO_3)_2{\cdot}6H_2O$ and $CH_6N_4O$ were employed as an oxidizer and a fuel. Exothermic peak was shown at $230^{\circ}C$ by DTA/TGA, and it was considered as a combustion reaction followed by ignition of the precursor mixture. In case of spray combustion method, because insufficient contents of molecules and radicals generated from precursor droplets may lead an incomplete igmition, the ignition temperature of combustion chamber was chosen at $500^{\circ}C$. For diminishing aerosol coagulation, the droplet number concentration was reduced by filter media. The fluid was laminar with 2.5 seconds of aerosol residence time. The synthesized colloids had spherical shape with 180 nanometer size, and the crystalline phase was ZnO with hexagonal structure.