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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
Editor in Chief :
Volume & Issues
Volume 17, Issue 6 - Dec 2013
Volume 17, Issue 5 - Oct 2013
Volume 17, Issue 4 - Aug 2013
Volume 17, Issue 3 - Jun 2013
Volume 17, Issue 2 - Apr 2013
Volume 17, Issue 1 - Feb 2013
Selecting the target year
A Study on the Combustion Instability of the Hybrid Rocket Motor with a Diaphragm
Lee, Jungpyo ; Kim, Youngnam ; Kim, Jinkon ; Moon, Heejang ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 1~10
DOI : 10.6108/KSPE.2013.17.6.001
In this paper, the main cause on excitation of the combustion instability which may occur in the hybrid rocket motor with a diaphragm was studied. Hybrid rocket motor propulsion tests considering various experimental conditions such as with a diaphragm or not, a diameter of diaphragm, oxidizer mass flow rate, fuel length, etc were performed, and the combustion visualization for the inside of a hybrid rocket motor with a diaphragm was performed. With these experimental results, it was confirmed that the main cause of a large excitation was the hole-tone, and it was shown that the hole-tone model can be predicted experimental primary pressure oscillation frequency quite well.
A Study on High-Temperature Fuel Injection Characteristics through Swirl Injectors
Lee, Hyung Ju ; Choi, Hojin ; Kim, Ildoo ; Hwang, Ki-Young ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 11~19
DOI : 10.6108/KSPE.2013.17.6.011
An experimental study was conducted to investigate fuel injection characteristics through swirl injectors when the fuel was heated to very high temperature conditions. Three swirl injectors with different orifice diameters and swirler geometries were used to measure the flow coefficient (
) for the injection pressure ranges between 3 and 10 bar and the fuel temperature from 50 to
. The results showed that the variation characteristics of
with respect to cavitation number (
) were highly dependent on both the orifice diameter and the swirler geometry. In addition, the characteristics of
variation with respect to AR, the area ratio of the flow through the swirler and the orifice, has revealed that the effect of boiling is retarded but the slope of decreasing
after the boiling effect is present tumbles as AR increases.
Numerical Study of Turbulent Flow and Combustion in a Micro Combustor with a Baffle Plate
Kim, Won Hyun ; Park, Tae Seon ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 20~29
DOI : 10.6108/KSPE.2013.17.6.020
Turbulent flow and combustion characteristics in a micro can combustor with a baffle plate are investigated by a Reynolds Stress Model. In order to examine the geometric effects on the turbulent combusting flow, several baffle configurations are selected. The interrelation between the flow structure and the thermal field are investigated by examing the variation of recirculation region, flame length and heat loss. For the flow mixing, the decreasing air hole is more efficient than the decrease of the fuel hole. As the fuel or air hole diameter decreases, combustion efficiency is enhanced and flame length is decreased. Additionally, as the diameter of air hole decreases, the heat loss and combustion temperature are increased, while they are reduced with decreasing the diameter of fuel hole.
An Approach to the Optimization of Catalyst-bed L/D Configuration in 70 N-class Hydrazine Thruster
Jung, Hun ; Kim, Jong Hyun ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 30~37
DOI : 10.6108/KSPE.2013.17.6.030
A ground hot-firing test was conducted to take out the optimal design configurations for the catalyst bed of liquid-monopropellant hydrazine thruster which could be used for primary engine or attitude control thruster of space vehicles. Performance characteristics with the variation of thrust-chamber length are investigated in terms of thrust, specific impulse, chamber pressure, characteristic velocity, and hydrazine decomposition rate. Additionally, the correlations between propellant-supply pressure and performance parameters are given. As results, increase of catalyst-bed length leads to performance degradation in this test condition, and also decreases propellant consumption efficiency with the supply pressure variation.
Synthesis and Characterization of Tetrazine Derivatives as High Energy Propellants
Lee, Woonghee ; Park, Youngchul ; Joo, Young-Hyuk ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 38~47
DOI : 10.6108/KSPE.2013.17.6.038
Traditional propellants release toxic gases during combustion that are harmful to the environment. This study describes a novel synthetic process of two high nitrogen containing tetrazines, TATTz and BTATz, which can be adapted as solid fuels for a solution to environmental concerns. The compounds were characterized by NMR, IR spectroscopy, and differential scanning calorimetry(DSC). Detonation properties were calculated with the EXPLO5 program based on calculated heats of formation and measured densities.
Study on Thermophysical Property Characteristics of a 4 Species Kerosene Surrogate in a Swirl Injector at Supercritical Pressure Condition
Kim, Kukjin ; Heo, Junyoung ; Sung, Honggye ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 48~58
DOI : 10.6108/KSPE.2013.17.6.048
Characteristics of thermophysical properties and flow structures in a swirl injector at supercritical pressure have been investigated using the kerosene surrogate consisting of four species and various ideal and real gas equations of state. The quantitative comparisons of thermophysical properties for equations of state have been performed. Also, a large eddy simulation and preconditioning technique for getting an effective convergence rate are applied to analyze turbulent flow in a swirl injector. The flow characteristics in the injector has significantly different behaviors depending on the equations of state due to the different thermophysical properties in the injector. The Redlich-Kwong-Peng-Robinson equation of state provides the most suitable results in the wide range of temperature.
Analysis of Supercritical Shear Coaxial Jet Using Density Gradient Magnitude
Lee, Keonwoong ; Kim, Dohun ; Son, Min ; Han, Choyoung ; Koo, Jaye ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 59~66
DOI : 10.6108/KSPE.2013.17.6.059
Spray characteristics of single round jet with liquid nitrogen and coaxial spray with liquid nitrogen and gaseous argon were observed. Shadowgraph method was used for spray visualization, and density gradient magnitude image was used to analyse the result. In subcritical condition, irregularity of the jet surface was harder in the coaxial spray. In supercritical condition, diffusion of nitrogen injected from shear coaxial injector was faster than single jet. Jet diameter was induced by averaging images, in supercritical condition, difference of diameter of coaxial jet was rapidly decreased than that of single jet.
Experimental Study on Combustion Instability Characteristics of Model Gas Turbine Combustor at Various H
Yoon, Jisu ; Lee, Min-Chul ; Joo, Seongpil ; Kim, Jeongjin ; Yoon, Youngbin ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 67~74
DOI : 10.6108/KSPE.2013.17.6.067
IGCC(Integrated Gasification Combined Cycle) system is candidates which can solve the environmental problems including global warming, since it can be easily combined with CCS(Carbon Capture System). In this research, combustion instability characteristics were studied at various fuel which are composed of
mixture. Mode analysis for instabilities observed experimentally was conducted and the linearly increasing tendency of frequency was observed as the hydrogen content in fuel increases.
Combustion Characteristics Study using Hyper-mixer in Low-enthalpy Supersonic Flow
Kim, Chae-Hyoung ; Jeung, In-Seuck ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 75~80
DOI : 10.6108/KSPE.2013.17.6.075
In this study, a forced ignition method with a plasma jet torch is studied in Mach 2 laboratory scaled wind-tunnel. The hyper-mixer is used as a mixer. For two normal injection cases, the one is collided against a wedge plate of the hyper-mixer and the other is directly injected into the cold main flow. For the first case, the hyper-mixer disperses the injected fuel, leading to the mixing enhancement. Furthermore, the fuel-air mixture is provided into the plasma hot gas, which enhances the combustion performance. However, the direct injection into the main flow method spends amount of fuel without ignition in the cold supersonic flow. In the end, for the forced combustion, it is important to supply the fuel-air mixture into the heat source.
Analysis of Dual Combustion Ramjet Using Quasi 1D Model
Choi, Jong Ho ; Park, Ik Soo ; Gil, Hyun Young ; Hwang, Ki Young ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 81~88
DOI : 10.6108/KSPE.2013.17.6.081
The component based propulsion modeling and simulation of an dual ramjet engine using Taylor-Maccoll flow equation and quasi 1-D combustor model. The subsonic and supersonic intake were modeled with Taylor-Maccoll flow having
cone angle, the gas generator which transfers a pre-combustion gas into supersonic combustor was developed using Lumped model, and the determination of the size of nozzle throat of a gas generator was described. A quasi 1-D model was applied to model a supersonic combustor and the variation of temperature and pressure inside combustor were presented. Furthermore, the thrust and specific impulse applying fuel regulation by pressure recovery ratio and equivalence ratio were derived.
Computational Study of Supersonic Chevron Ejector Flows
Kong, Fanshi ; Kim, Heuy Dong ; Jin, Yingzi ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 89~96
DOI : 10.6108/KSPE.2013.17.6.089
Considering the complexity and difficulty on the researching, how to enhance the performance of ejector-diffuser system effectively became a significant task. In the present study, the supersonic nozzle was redesigned using Chevrons installed at the inlet of the secondary stream of the ejector-diffuser system for the purpose of the performance improvement. A CFD method based on Fluent has been applied to simulate the supersonic flows and shock waves inside the ejector. Primary numerical analysis results show that the Chevrons get a positive effect on the ejector flows. The comparison of ejector performance with and without the Chevron was obtained and optimal number of chevron lobe is discussed to increase the performance. The ejector-diffuser system performance is discussed in terms of the entrainment ratio, pressure recovery as well as total pressure loss.
An Efficient Synthesis of GUDN as Green Oxidizer
Sul, Min-Jung ; Joo, Young-Hyuk ; Jeong, Won-Bok ; Park, Young-Chul ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 97~104
DOI : 10.6108/KSPE.2013.17.6.097
N-Guanylurea dinitramide (GUDN) is an energetic material with low sensitivities and good performance for use as propellants or insensitive munitions explosives. The efficient synthesis and characterization of high energy density material of GUDN is reported. GUDN was characterized spectroscopically as well as elemental analysis. In addition, the heats of formation were calculated with the Gaussian 09 suite of programs. For initial safety testing, the impact sensitivity and the friction sensitivity were tested following BAM procedure.
Analysis of Joints Using Metal Seals in Liquid Rocket Engine Turbopump
Yoon, Suk-Hwan ; Jeon, Seong Min ; Kim, Jinhan ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 105~112
DOI : 10.6108/KSPE.2013.17.6.105
Turbopump is typically an assembly of rotors and casings, and there are a number of joints between them. Every joint should be leak-proof, so there is always a seal to accomplish the goal. Among various seals, metal seals are advantageous in that they are robust at high pressure, and at wide range of temperature. In this study, flange joints using conical seal made of stainless steel, solid flat metal seal made of copper and metal C seal made of Inconel 718 were structurally designed and analyzed, considering both initial tightening and operating conditions.
Study for the Development of a Main Oxidizer Shut-off Valve for Liquid Rocket Engines
Kim, Dohyung ; Hong, Moongeun ; Park, Jaesung ; Lee, Soo Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 113~119
DOI : 10.6108/KSPE.2013.17.6.113
A main oxidizer shut-off valve (MOV) controls the supply of cryogenic liquid oxygen to the combustion chamber of liquid rocket engines by on/off operations. The main subjects to be introduced are not only the valve transient response during valve on/off procedures but also the characteristics of pneumatic and seat/poppet parts as core technologies in the development of the MOV, which is expected to be adopted for the Korea Space Launch Vehicle II. It is shown that the analytical prediction of the transient valve travel is in good agreement with experimental results. Friction and elastic forces on the valve moving part are quantitatively evaluated by structural analysis.
State of the Art in the Development of Methane/Oxygen Liquid-bipropellant Rocket Engine
Kim, Jeong Soo ; Jung, Hun ; Kim, Jong Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 6, 2013, Pages 120~130
DOI : 10.6108/KSPE.2013.17.6.120
A study was conducted for the performance characteristics of methane taking recently the limelight in the world as a next-generation propellant, with the survey for state of the art in the development of methane/oxygen rocket engine being accompanied. Liquid methane as a rocket fuel has the favorable characteristics such as non-toxic, low cost, regenerative cooling capability, and potential for in-situ resource utilization (ISRU). The combination of liquid methane and liquid oxygen also provides the excellent performance including high specific impulse and low system mass. For these reasons, many researches have been actively carried out on the methane/oxygen engine, nevertheless, its technology readiness level is not that high enough just yet. Therefore, it is judged that it is the time to mitigate the technical gap with the space technology of advanced countries through a swift onset of the development of methane rocket engine.