• Transactions of the Korean Society of Automotive Engineers
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• v.4 no.1
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• pp.165-176
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• 1996

The flow field and spray characteristics for loop scavenged type 2stroke engine having pancake shape was numerically computed using KIVA-Ⅱ code. The cylinder has 1intake port, 2side intake ports and 1exhaust port with induced flow angle 25 deg. In engine calculation, the chop techniques is used to strip or add planes of cells across the mesh adjacent to the TDC and the BDC(ports parts) for preventing the demand of exceed time during the computation, providing a control on cell height in the squish region. The modified turbulent model including the consideration of the compressibility effect due to the compression and expansion of piston was also used. The case of 25 deg.(injection angle) which is opposite to scavenging flow direction shows better the distribution of droplets and the evaporation rate of droplets compared to other cases(0 deg., - 25 deg.). When injection pressure was increased, the spray tip penetration became longer. When injection pressure was increased, the interaction between the upward gas velocity and spray droplets strongly cause. Thus the breakup of droplets is strongly occurred and the evaporation rate of droplets was found to be better.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.97-101
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• 2007

The spray characteristics of the oxidizer-rich preburner are investigated. From the PDPA measurement, droplet SMD of $210{\mu}m$ and droplet axial velocity of 38 m/s are measured at 100 mm distance from the nozzle tip on the fuel pressure of $25kgf/cm^2$ and oxidizer pressure of $10kgf/cm^2$. The droplet velocity is decreased with the axial distance and the oxidizer spray makes dominant effect on the combined spray characteristics of the oxidizer-rich preburner injector.

• Proceedings of the Safety Management and Science Conference
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• 2012.04a
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• pp.639-654
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• 2012

최근 글로벌 경쟁이 치열해 지면서 가격경쟁력이 뒷받침되지 않으면 신흥 시장에 대한 대응이 어려워져 가격경쟁력의 중요성이 부각되고 있으며, 구조적인 비용 상승 추세로 기업의 원가 압력이 증대되고 있고, 이러한 변화된 경쟁 환경에서 생존하기 위해서는 전체적인 생산성 향상이 필수이다. 가격경쟁력 강화 및 원가압박을 해소하고 품질, 가격, 납기 전반에 모방할 수 없는 차별화된 경쟁력의 확보는 생산성 향상을 통해서 실현할 수 있고, 생산성 향상을 통한 경쟁력 있는 기업 육성은 우리 제조업을 발전시키는 토대(infra structure)이며, 기반 시설의 확충이다. 본 연구에서는 현재 외국의 혁신방법을 우리산업 현실에 대한 고려 없이 단순 도입으로 국내 실정에 맞지 않아 상당한 시행착오를 격고 있으며, 국내에 벤치마킹 할만한 제조혁신 방법론이 거의 없고, 벤치마킹하려고 해도 기업의 영업비밀이라 배우기도 쉽지 않은 상황에서 우리산업 현실에 맞는, 중소 중견기업의 맞춤형 생산성 혁신 지원도구로 중소기업의 자생적인 혁신을 위해 중소기업의 수준에 맞는 제조혁신 방법을 국내외 제조혁신 전문가로 컨소기엄을 구성하여 한국생산성본부에서 개발된 한국형제조혁신 방법론을 제조기업에 적용하여 성공적인 결과를 다른 기업에 적용 할 수 있도록 하는데 목적을 둔다. 연구목적을 달성하기 위해 문헌연구를 통해 일본의 TPS(Toyota Production System), 미국의 Lean 시스템 및 6시그마 시스템에 대하여 살펴보았고, 한국형 제조혁신 모델인 KPS(korea production system)를 통신장비 제조회사인 M. 사에 적용하여 실증하였으며, 그 결과 우수한 성과를 보임을 확인할 수 있었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.46-51
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• 2012

This study aims to develop the performance analysis program on the staged combustion cycle of the liquid rocket engine using liquid oxygen(LOx) as oxidizer, liquid hydrogen(LH2) and RP-1 as fuel. The developed analysis program can obtain the propellant mass flow rate, the specific impulse, and representative design values of engine components for the required thrust satisfying pressure, mass flow, and energy balance conditions. The analysis results show that the the specific impulses (Isp) compared to those of the real engines have been less than 1%. With additional constraints, the program will be improved for the system optimization.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.517-524
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• 2019

A system design has been performed for a vacuum thrust 88 ton staged combustion cycle rocket engine. Previous research has been used to estimate the performance of the engine components. And the algorithm has been proposed to evaluate the converged engine system performance. The present methodolgy has been verified by comparing the published data for RD-180. The present work adopts the most of the previous KSLV-II engine heritage for both performance improvement and cost competitiveness. The combustion pressure has been decided as 12MPa considering manufacturing difficulty, cost and performance improvement, and as a result the vacuum specific impulse has increased by 23.4s.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.3
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• pp.251-257
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• 2012

This work presents an experimental investigation of NOx emissions according to inlet air temperature (550-660 K), stoichiometric air ratio (${\lambda}$, 1.4-2.1), and elevated pressure (2-5 bar) in a High Press Combustor (HPC) equipped with a double cone burner, which was designed by Pusan Clean Coal Center (PC3). The exhaust-gas temperature and NOx emissions were measured at the end of the combustion chamber. The NOx emissions generally decreased as a function of increasing ${\lambda}$. On the other hand, NOx emissions were influenced by ${\lambda}$, inlet air temperature and pressure of the combustion chamber. In particular, when the inlet air temperature increased, the flammability limit was extended to leaner conditions. As a result, a higher adiabatic temperature and lower NOx emissions could be achieved under these operation conditions. The NOx emissions that were governed by thermal NOx were greatly increased under elevated pressures, and slightly increased at sufficiently low fuel concentrations (${\lambda}$ >1.8).

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.12
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• pp.109-116
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• 2005

Elastic-plastic structural analysis for regenerative cooling chamber of liquid rocket thrust chamber is performed. Uniaxial tension test is also conducted for the copper alloy in order to get material data necessary for the structure analysis. The results of uniaxial tension test reveal that copper alloy become ductile after brazing process and flow stress becomes lower as temperature becomes higher. As a result of structural analysis using the material data, the deformation of cooling channel is more increased by thermal load than by internal pressure of cooling fluid. Therefore, the results of analysis show that structural stability and cooling performance of combustion thrust chamber which is designed to endure mechanical load and minimized a channel thickness are improved by decreased thermal load as possible.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.3
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• pp.222-229
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• 2012

The cooling of a injector effects on the vapor pressure of cryogenic oxidizer spray, and it decides the phase transition point at the ignition process, when the combustion chamber pressure increases drastically. The phase transition of oxidizer spray affects the ignition characteristics, and several ignition tests with the LOx/$GCH_4$ uni-element coaxial swirl injector was performed in the different initial temperatures of oxidizer injector, in order to investigate the effect of injector cooling on the ignition transient characteristics. At the transition point of oxidizer phase, where the combustion chamber pressure increased over the LOx vapor pressure, the temporary quenching phenomenon of the flame occurred. The lower temperature of chilled down injector and tubing tends to move up the phase transition earlier.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.93-96
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• 2011

A genetic algorithm (GA) has been employed to optimize the major design variables of the liquid rocket engine. Mass flow rate to the main thrust chamber, mass flow rate to the gas generator and chamber pressure have been selected as design variables. The target engine is the open gas generator cycle using the LO2/RP-1 propellant. The objective function of design optimization is to maximize the specific impulse with condition of energy balance between the pump and the turbine. The properties of the combustion chamber have been obtained from CEA2. Pump & turbine efficiencies and properties of the gas generator have been modeled mathematically from reference data. The result shows 3~4% errors for the specific impulse and 2~6% errors for the pump power of the gas generator cycle compared to references.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.3
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• pp.58-66
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• 2019

In this study, the start-up characteristics of a staged combustion engine were analyzed numerically based on relational equation modeling of the entire engine components. The start-up characteristics were extensively analyzed considering the transient period of the total engine system from the start-up sequence till the steady-state of the engine. The performance characteristics of the engine components such as RPM of engine power-pack, chamber pressure and O/F ratio of pre-burner, and mass flow of propellants in the start-up period were investigated. Furthermore, the calculated engine data were compared satisfactorily with the experimental data. Through the comparison of data, successful validation of present engine start-up analysis has been obtained.