• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1997.04a
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• pp.3-10
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• 1997

본 연구에서는 추력 500 Kgf의 액체 추진기관을 설계, 제작 및 연소시험을 수행하여 연소 특성을 살펴보았다. 추진제로는 우주발사체 Booster용으로 폭넓게 사용되는 탄화수소계 연료인 kerosene과 산화제로 취급이 용이하고 저장 특성을 지닌 98 % White Fuming Nitric Acid(WFNA)를 사용하였고, 엔진 점화를 위해 WFNA와 접촉 발화성 (Hypergolic)을 갖는 Furfuryl Alcohol/Aniline 혼합액을 사용하였다. 로켓엔진은 20 Kgf/$cm^2$의 연소실 압력으로 500 Kgf의 평균 추력을 내도록 설계되었고, 연소실벽을 고온 연소가스로 부터 보호하기 위해 Film Cooling 방식을 적용하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.5
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• pp.51-59
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• 2007

The end-burning combustion field using impinging oxidizer injectors are analyzed with tangential type injectors in order to examine their mixing and combustion characteristics. The impinging type showed further improved mixing effect as well as the combustion efficiency compared to the previously studied tangential injector. A novel injector capable of delivering impinging and swirl effect is introduced in this study where it demonstrated that the grain coning effect can be avoided. It was found that the combined impinging and swirling flow would promote the radial mixing rate increasing the residence time and the turbulent intensity. However, the use of the step combustor which may augment the turbulent intensity did not show any notable difference compared to the basic combustor.

• Proceedings of the Korean Institute of Industrial Safety Conference
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• 2000.06a
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• pp.136-139
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• 2000

현대산업사회의 급속한 발전으로 사용이 편리하고, 깨끗한 연료인 도시가스의 사용량은 점점 더 증대될 뿐만 아니라 사용형태 또한 다양화되고 있어, 이에 따른 사고도 증가하고 있으며 사고의 규모도 대형화 되어가고 있다. 일반적으로 가스폭발의 경우 개방된 영역에서 보다 밀폐된 영역에서 발생할 경우 폭발압력에 의한 파괴효과는 더욱 증가한다. 이러한 부분에 대해 많은 학자들은 단일가스와 산화제를 혼합시킨 형태의 가스 폭발에 대한 특성을 연구하여 왔다. 그러나 산소농도의 변화에 따른 가연성가스의 폭발범위, 폭발시 초기압력의 변화, 최소점화에너지에 관한 연구는 거의 없는 실정이다. (중략)

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.3
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• pp.65-71
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• 2018

There is no significant difference in the initial viscosity of a propellant applied with yellow iron oxide and red iron oxide. In addition, the thermal decomposition rate of the material with added yellow iron oxide is faster than that with the addition of red iron oxide. Specifically, it was confirmed that the pressure exponent was 18% lower at high temperature and high pressure with yellow iron oxide than with red iron oxide. The initial viscosity was lowest at 71% of the large particle to small particle ratio.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.498-503
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• 2017

There is no unusual difference in the initial viscosity of the propellant applied with yellow iron oxide and red iron oxide. In addition, the thermal decomposition rate of the material added with yellow iron oxide is faster than that of the addition of red iron oxide. Especially, it was confirmed that the pressure exponent was 18% lower at high temperature and high pressure. The initial viscosity was lowest at 71% of large particle/small particle ratio

• 유체기계공업학회:학술대회논문집
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• 2003.12a
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• pp.284-306
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• 2003

• Proceedings of the Korean Institute of Industrial Safety Conference
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• 2001.11a
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• pp.259-262
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• 2001

산화성 물질은 소방법상 위험물 제1류 및 제6류에 속하여 있는 것으로서, 그 위험성은 산화성 물질 단독으로 또는 가연물과 혼합에 의해서 폭발성 또는 폭발적 연소성을 갖는 물질로서, 이를 위한 위험성 평가는 현재 국내의 소방법으로 규정하고 있는 위험물에 대한 연소 및 반응위험성과 같은 제반 위험성을 판별하는 기준이 없어 이를 위한 체계적인 시험법의 요구가 필요한 것이다. 따라서, 본 연구는 국내 소방법 중 위험물 제1류로 구분되고 있는 산화성고체에 대한 연소위험성을 평가하기 위한 보다 체계적이고 재현성 있는 판별 기준을 제시하여 보고자 하였으며, 이를 통하여 기준 시험법의 정립을 기하기 위한 기술자료로서 활용하여 보고자 하였다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.285-288
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• 2008

The Present Study describes the numerical investigations concerning a fuel(Hydrogen), inert gas (Nitrogen) or supersonic air stream issued between each other. The basic flow configuration consists of a plane, double shear/mixing layer flow. For the numerical solution, a fully conservative unsteady $2^{nd}$ order time accurate sub-iteration method and a $2^{nd}$ order Total Variation Diminishing(TVD) scheme are used with the finite volume method(FVM). The results are consist of three categories ; single shear layer consist of fuel and supersonic air stream, inert gas stream issued between supersonic air and fuel stream, fuel gas stream issued between supersonic air and fuel stream. The numerical calculations has been carried out in case of 1,2, and 4mm thickness of center stream. The width of total gas stream is 4cm.

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.3
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• pp.31-39
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• 1999

In this paper, numerical experiment is attempted to analyze and compare the combustion efficiency of the burning sprays due to OFO, FOF triplet / FOOF split doublet injectors. Preconditioned Wavier-Stokes equation system with low Reynolds number $\kappa$-$\varepsilon$ model for turbulence closure, is LU-SGS time-integrated. Spray processes are modeled by DSF analysis with experimentally determined injection characteristics. n-heptane/air global reaction model approximates the combustion for simplicity, and the influence of turbulence on the chemical reaction is included using eddy dissipation model. The results showed the FOF triplet injector of highest combustion efficiency, whereas the OFO type of poet performance. It was also observed that the droplet mean diameter and the average gas temperature due to the mixing efficiency, are the representative parameters for the performance design of combustion.

• Proceedings of the Korean Environmental Sciences Society Conference
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• 2001.11a
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• pp.132-133
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• 2001

본 연구결과 혼합광촉매가 수계에 미치는 영향 등으로 인하여 사용되지 못하는 단점을 전자이동 및 산화방지제역할을 하여 수계에 용출되어지는 것을 제어할 수 있었으며, 또한 순수 단일광촉매보다 더 높은 활성을 나타내었다.