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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
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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 Numerical Study on the Performance Characteristics of a Partial Admission Axial Supersonic Turbine with Swept Rotor Blades
Jeong, Sooin ; Kim, Kuisoon ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 1~8
DOI : 10.6108/KSPE.2013.17.3.001
In this study, we performed three-dimensional CFD analysis to investigate the effect of the rotor blade sweep of a partial admission supersonic turbine on the stage performance and the flow field. The computations are conducted for three different sweep cases, No sweep(NSW), Backward sweep(BSW), and Forward sweep(FSW), using flow analysis program, FLUENT 6.3 Parallel. The results of the BSW model show reduced mass flow rates of tip leakage and increased total-to-static efficiency. The strength of leading edge bow shock was decreased a little with BSW model. And the BSW model also shows a good performance around the hub region compared to other models.
Combustion Test of a Mach 5 Scramjet Engine Model
Yang, Inyoung ; Lee, Yang-Ji ; Kim, Young-Moon ; Lee, Kyung-Jae ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 9~14
DOI : 10.6108/KSPE.2013.17.3.009
Combustion tests were conducted for a hydrogen-fueled Mach 5 scramjet engine model using a blow-down facility. No fuel and two fuel flow rate cases were tested for two different model configurations. Time history of the wall static pressures inside the model and their time-averaged spatial distribution were used for the analysis of the flow and combustion characteristics. For shorter model, supersonic combustion was occurred for both of the fuel flow rate cases. For longer model, supersonic combustion was occurred for less fuel case, whereas thermal choking and subsonic combustion were occurred for more fuel case. Intake started even for this subsonic combustion case.
Wear Properties of Seal Graphite at Elevated Temperature
Yang, Ho-Young ; Kim, Jaehoon ; Ha, Jaeseok ; Kim, YeonWook ; Park, Sunghan ; Lee, Hwankyu ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 15~20
DOI : 10.6108/KSPE.2013.17.3.015
The graphites as airtight structure seals prevent high-pressure and high-temperature gas from flowing into actuator of propulsion system and generate lubricant film during wear procedure to assist lubricant and sealing. In this study, the tribological characteristics of the graphite in high-temperature are evaluated. In order to evaluate the tribological characteristics of high density graphite(HK-6), variables which are temperature, sliding speed and contact load are set. this study suggest optimized environment conditions through the wear properties of graphite. Consequeantly, high temperature is better than at room temperature to generate lubricant film, so that friction coefficient of graphite is lower at high temperature than at room temperature.
An Evaluation of Numerical Schemes in a RANS-based Simulation for Gaseous Hydrogen/Liquid Oxygen Flames at Supercritical Pressure
Kim, Won Hyun ; Park, Tae Seon ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 21~29
DOI : 10.6108/KSPE.2013.17.3.021
Turbulent flow and thermal fields of gaseous hydrogen/liquid oxygen flames at supercritical pressure are investigated by turbulence models. The modified Soave-Redlich-Kwong (SRK) EOS is implemented into the flamelet model to realize real-fluid combustions. For supercritical fluid flows, the modified pressure-velocity-density coupling are introduced. Based on the algorithm, the relative performance of six convection schemes and the predictions of four turbulence models are compared. The selected turbulence models are needed to be modified to consider various characteristics of real-fluid combustions.
A Study on the Storage Life Estimation Method for Applying Gamma Process Model to Accelerated Life Test Data
Park, Sungho ; Kim, Jaehoon ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 30~36
DOI : 10.6108/KSPE.2013.17.3.030
This paper presents a method to estimate a storage life for loss of stabilizer content as storage periods using accelerated life test data. The estimate of storage life based on deterministic accelerated life test and degradation data cannot describe a condition distribution and storage life distribution. Previously, the method to show the condition distribution and storage life distribution by using gamma process has been studied. But it has limitation because it is impossible to collect the deterioration data at initial production phase. The estimated storage life presented by this study shows the similar value to previous studies and the method can describe the condition distribution and storage life distribution. So, the estimation method studied in this paper can be used for a life cycle management about deterioration of propellant for propulsion unit or components of missile, too.
Numerical Simulation of the Effect of Finite Diaphragm Rupture Process on Micro Shock Tube Flows
Arun Kumar, R. ; Kim, Heuy Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 37~46
DOI : 10.6108/KSPE.2013.17.3.037
Recent years have witnessed the use of micro shock tube in various engineering applications like micro combustion, micro propulsion, particle delivery systems etc. The flow characteristics occurring in the micro shock tube shows a considerable deviation from that of well established conventional macro shock tube due to very low Reynolds number and high Knudsen number effects. Also the diaphragm rupture process, which is considered to be instantaneous process in many of the conventional shock tubes, will be crucial for micro shock tubes in determining the near diaphragm flow field and shock formation. In the present study, an axi-symmetric CFD method has been applied to simulate the micro shock tube, with Maxwell's slip velocity and temperature jump boundary conditions. The effects of finite diaphragm rupture process on the flow field and the shock formation was investigated, in detail. The results show that the shock strength attenuates rapidly as it propagates through micro shock tubes.
Flow Characteristics Investigation of Gel Propellant with Al
Nano Particles in a Curved Duct Channel
Oh, Jeongsu ; Moon, Heejang ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 47~55
DOI : 10.6108/KSPE.2013.17.3.047
Curved duct channel flow characteristics for non-Newtonian gel fluid is investigated. A simulant gel propellant mixed by Water, Carbopol 941 and NaOH solution has been chosen to analyze the gel propellant flow behavior. Rheological data have been measured prior to the flow analysis where water-gel propellant and water-gel propellant with
nano particles are both used. The critical Dean number examined by the numerical simulation in the U-shape duct flow reveals that although water-gel-nano propellants have higher apparent viscosity, the critical Dean number do show no notable difference for both the two gel propellant. It is found that the power-law index may be a dominant parameter in determining the critical Dean number and that the gel with particles addition may be more vulnerable to Dean instability.
Weight Reduction of the Reusable Launch Vehicles Using RBCC Engines
Kang, Sang Hun ; Lee, Soo Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 56~66
DOI : 10.6108/KSPE.2013.17.3.056
Weight reduction of the VTHL / TSTO type of the reusable launch vehicles using RBCC engines are investigated. To predict weight and thrust of the vehicles, equations of motion are analyzed. Analysis results are compared with specifications of existing launch vehicles for validations. For the mission of inserting 2.5 ton payload to 200 km circular orbit, the case A, which uses the RBCC engine in the 1st stage shows smaller weight than the case B, which uses the RBCC engine in the 2nd stage. The weight of the case A shows only 25.8% of a existing rocket launch vehicle's weight.
Numerical Analysis on Cooling Characteristics of Oxidizer-Rich Preburner
Lee, Seon-Mi ; Ha, Seong-Up ; Lee, Soo Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 67~75
DOI : 10.6108/KSPE.2013.17.3.067
The numerical analysis for the verification of preburner's cooling characteristics applying to kerosene-LOx rocket engine has been fulfilled. The distribution of combustion gas properties in primary combustion zone was calculated by the mixture ratio based on head injector arrangement, the properties of oxygen flowing in wall channels as coolant were applied under real-gas conditions, and multi-phase mixing model was employed to calculate the mixing process of primary combustion zone with liquid oxygen which was used for wall cooling. The results of numerical analysis were compared with the experimental results, hence thermo-physical properties in cooling channels and a combustor could be quantitatively identified.
Technology Trend of Hypergolic Igniter and Rupture Disc
Yoo, Jaehan ; Lee, Soo Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 3, 2013, Pages 76~82
DOI : 10.6108/KSPE.2013.17.3.076
Survey on the hypergolic igniter and its rupture discs for liquid rocket engines was performed. The patents of the igniters for US MC-1 and Russia RD-170 engines and the discs for NASA's space vehicle were analyzed. The types of discs and holders, characteristics related to rupture pressures and working fluids, and ASME standards of the discs were examined. Also, survey on structural analyses of the disc were performed. Typical design features and experimental results of the currently developing igniter by the authors were presented.