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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 16, Issue 6 - Dec 2012
Volume 16, Issue 5 - Oct 2012
Volume 16, Issue 4 - Aug 2012
Volume 16, Issue 3 - Jun 2012
Volume 16, Issue 2 - Apr 2012
Volume 16, Issue 1 - Feb 2012
Selecting the target year
A Study on the Performance Prediction Method for an Axial Compressor with Variable Inlet Guide Vane
Kim, Dong-Hyun ; Kim, Sang-Jo ; Kim, Kui-Soon ; Son, Chang-Min ; Kim, You-Il ; Min, Seong-Ki ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 1~8
DOI : 10.6108/KSPE.2012.16.4.001
In this study, numerical method, stage stacking method based on the result of numerical method and scaled stage stacking method have been applied to predict the performance of a multi-stage axial compressor with inlet guide vane. The results obtained through three different methods for off-design conditions were compared with performance test data. And the effect the angle of variable inlet guide vane was also investigated. The three-dimensional numerical simulation has been performed by using flow analysis program,
6.3 and the performance prediction based on the stage stacking method has been performed with compressor analysis code from NASA.
Failure Behavior of Pin-jointed Cylindrical Composites Using Acoustic Emission Technique
Yoon, Sung-Ho ; Hwang, Young-Eun ; Kim, Chan-Gyu ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 9~15
DOI : 10.6108/KSPE.2012.16.4.009
In this paper, the bearing strengths and fracture behaviors of the pin-jointed carbon fiber/epoxy composites were investigated through pin loading test with acoustic emission technique. The composites were fabricated by a filament winding process, and three types of laminated patterns were considered. Type 1 was fabricated with stitch, Type 2 was fabricated without stitich and Type 3 was fabricated with prepregs. According to the results, bearing strength of Type 1 was 3.3% lower than that of Type 2 and that of Type 3 was highest. Type 1 and Type 2 revealed a net-tension failure mode, respectively, whereas Type 3 pattern exhibited a bearing failure mode. Also, acoustic emission energy of the Type 3 was higher than that of the Type 1 and Type 2. Therefore, the Type 3 was found to be structurally safer than the Type 1 and Type 2.
Determination of Explosive Weight for Cable Cutter through Impact Test
Choi, Chang-Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 16~22
DOI : 10.6108/KSPE.2012.16.4.016
We performed impact test to estimate necessary explosive charge weight for cutting the cable whose diameter is 22 mm. The impact test results were analyzed by Probit method. The cutting energy was calculated 37.7 J with 99.99% probability at 99% reliability compared to the average energy of 24.9 J. The cable was cut 3 times without failure with 150 mg of Zirconium Potassium Perchlorate (ZPP), which was considered to generate 24.5 J of mechanical energy with assumption that only 10% of explosive energy converts to mechanical energy. The calculated energy from measured pressure with 150 mg ZPP was 26.1 J, which is almost same with both impact test result and expected mechanical energy. We can argue that the cable can be cut with 99.99% probability at 99% reliability by 230 mg of ZPP.
An Approach for the Integrated Performance Analysis of a Small Turbofan engine with Variable Inlet Guide and Variable Stator Vane
Kim, Sang-Jo ; Kim, Dong-Hyun ; Son, Chang-Min ; Kim, Kui-Soon ; Kim, You-Il ; Min, Seong-Ki ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 23~32
DOI : 10.6108/KSPE.2012.16.4.023
The present study is aimed to develop an integrated performance analysis approach for the application of a compressor with variable inlet guide vane (VIGV) and vairable stator vane (VSV) in a small turbofan engine. For the integrated analysis approach, an engine performance analysis program, NPSS and a computer program used for predicting of axial flow compressor performance based on stage stacking method, STGSTK were linked with an optimisation package, Isight. This enables off-design performance analysis for the turbofan engine with VIGV and VSV hence provides the capability to predict stable operation condition of the engine with acceptable surge margin.
Estimation of Shelf Life for Propellant KM6 by Using Gamma Process Model
Park, Sung-Ho ; Kim, Jae-Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 33~41
DOI : 10.6108/KSPE.2012.16.4.033
The aim of the study is to investigate the method to estimate a shelf life of KM6 single base propellant by stochastic gamma process model. The state failure level is assumed that the degradation content of stabilizer is below 0.8%. The constant of time dependent shape function and the scale parameter of stationary gamma process are estimated by moment method. The state distribution at each storage time can be shown from probability density function of deterioration. It is estimated that the
life, a time at which the cumulative failure probability is 10%, is 25 years and the
life is 36 years from cumulative failure distribution function curve. The
life can be treated as the average shelf life from the practical viewpoint and the lifetime can be expressed as distribution curve by using stochastic process theory.
Critical Speed Analysis of a 75 Ton Class Liquid Rocket Engine Turbopump due to Load Characteristics
Jeon, Seong-Min ; Kwak, Hyun-D. ; Hong, Soon-Sam ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 42~49
DOI : 10.6108/KSPE.2012.16.4.042
Critical speed of high thrust liquid rocket engine turbopump is obtained through a rotordynamic analysis and a unloaded turbopump test is peformed for validation of the numerical model. The first critical speed predicted by the numerical analysis is correlated well with the test result for the bearing unloaded rotor condition only considering mass unbalance load. Using the previous rotordynamic model, critical speed variation is estimated as a function of varied bearing stiffness due to pump and turbine radial loads with relative angle difference. From the numerical analysis, it is found that the relative angle difference of pump and turbine radial loads greatly affects the critical speed. However, additional axial load reduces the effect derived from the relative angle difference of radial loads.
Characteristic Study on Effect of the Vent Mixer to Supersonic Fuel-Air Mixing with Stereoscopic-PIV Method
Kim, Chae-Hyoung ; Jeung, In-Seuck ; Choi, Byung-Il ; Kouchi, Toshinori ; Masuya, Goro ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 50~56
DOI : 10.6108/KSPE.2012.16.4.050
Vent mixer can provide main flow directly into a recirculation region downstream of the mixer to enhance fuel-air mixing efficiency. Based on experimental results of three-dimensional velocity, vorticity and turbulent kinetic energy obtained by a stereoscopic PIV method, the performance of the vent mixer was compared with that of the step mixer which was used as a basic model. Thick shear layers of the vent mixer induced the increase of the penetration height. The turbulent kinetic energy mainly distributed along a boundary layer between the main flow and the jet plume. This turbulent field activates mass transfer in a mixing region, leading to the mixing enhancement.
An Experimental Study on Combustion Instability Characteristics of Various Fuel-Air Mixing Section Geometry in a Model Dump Shape Combustor
Kim, Min-Ki ; Yoon, Ji-Su ; Hwang, Jeong-Jae ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 57~69
DOI : 10.6108/KSPE.2012.16.4.057
The main objective of this study was investigation of natural gas flames in a lean premixed swirl-stabilized dump combustor with an attention focused on the effect of the various fuel-air mixing section geometry on the combustion instability characteristics. The combustor and mixing section length was varied in order to have different acoustic resonance characteristics from 800 to 1800 mm in combustor and 470, 550, 870 mm in mixing section. We observed two dominant instability frequencies in this study. Lower frequencies were associated with a fundamental longitudinal mode of combustor length. Higher frequencies were related to secondary longitudinal mode of coupled with the combustor and mixing section. As a result, combustion instability was strongly affected by acoustic characteristics of combustor and mixing section geometry.
Large Scale Mass Flow Measurement Using Bellmouth and Rake
Kim, Jeong-Woo ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 70~79
DOI : 10.6108/KSPE.2012.16.4.070
For an aerodynamic test facility, it is very important to get the precise measurement data of pressure, temperature and mass flow rate at the upstream to the test article. Hence, a new measurement method using a bellmouth and rakes was studied for the large scale system of which the corrected mass flow is between 5 kg/s and 8 kg/s. The bellmouth was designed by ISO standard for 0.5% accuracy, and the rakes were designed by using the equal area method. From the results of 9 test trials, it is found that the Reynolds number of rakes and the mass flow rate ratio can be simply formulated by an one-dimensional equation. The mass flow rate of rakes was calibrated by this equation. By the result of calibration, The maximum error rate was -0.507%, and the average error rate was -0.000274%.
A Numerical Analysis on the Thermal Protection System Applied Phase Change Material
Oh, Chang-Mook ; Yoo, Yung-Joon ; Min, Seong-Ki ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 80~86
DOI : 10.6108/KSPE.2012.16.4.080
This study is for figuring out a possibility of realization of the thermal protection system(TPS) for temporary use under high temperature condition and improving a design of the future TPS. On this purpose, environmental condition of the system has been simplified: the boundary conditions consist of a internally heating surface and a externally heated surface which is simulating the external high temperature condition. Configuration of the system is simplified as a hexahedon. Melting characteristics of the phase change material(PCM) and air temperature variation of TPS with or without connector have been numerically analyzed and compared. As a result of numerical analysis, the heat from the internally heated surface could not be effectively transferred. Therefore, temperature of inner space has been increased.
Modeling and Simulation of Combustion Chamber Test Facility Fuel Supply System
Chung, Yong-Gahp ; Lee, Kwang-Jin ; Cho, Nam-Kyung ; Han, Yeoung-Min ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 87~92
DOI : 10.6108/KSPE.2012.16.4.087
The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The fuel supply system modeling using AMESim was performed based on the results of the detailed design, and the fuel supply characteristics was analyzed in this paper.
Development of the Drive-away Motor for Cold Launch System
Baek, Gook-Hyun ; Oh, Jong-Yun ; Lee, Young-Won ; Lee, Ji-Hyung ; Jung, Jin-Suk ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 4, 2012, Pages 93~98
DOI : 10.6108/KSPE.2012.16.4.093
To solve the combustion instability, especially chuffing phenomena, happened during development process of a drive-away motor that was required for cold launch system of missile, various technical approaches have been performed through ground firing tests. The ignition energy or its supply system, generally closely related with the chuffing phenomena, does not affect suppression of the chuffing, but the increase of characteristic length(
) as well as the addition of 2% ZrC as a damping material is effective to suppress the chuffing. Therefore we could have a typical experience on the combustion instability in double base propellant.