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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 15, Issue 6 - Dec 2011
Volume 15, Issue 5 - Oct 2011
Volume 15, Issue 4 - Aug 2011
Volume 15, Issue 3 - Jun 2011
Volume 15, Issue 2 - Apr 2011
Volume 15, Issue 1 - Feb 2011
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Structural Variation of Methane/Air Premixed Flame Caused by the Intervention of Ultrasonic Standing-wave
Seo, Hang-Seok ; Lee, Sang-Shin ; Kim, Jeong-Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 1~6
An experimental study has been conducted to scrutinize into the influence of ultrasonic standing wave field on the variation of methane/air premixed flame structure. Visualization technique utilizing the Schlieren method is employed for the observation of premixed flame propagation. The shape of flame front and local flame velocity are measured according to the variation of reactants pressure and chamber opening/closing condition. The flame fronts affected by the standing wave are clearly distorted but the vertical locations of frontal dents do not undergo any appreciable change. The influence of standing wave on the flame front becomes more prominent as the flame propagates downward. It is found that the propagation velocity of flame front with excitation of standing wave is greater than the case without the excitation. It is eventually revealed that the flame is deformed to lotus-shaped one by the vivid interaction of ultrasonic standing-wave with the reflected wave coming from the right side.
Effects of Catalyst Granule Failure in Monopropellant Satellite Thruster
Hwang, Chang-Hwan ; Lee, Sung-Nam ; Baek, Seung-Wook ; Kim, Su-Kyum ; Yu, Myoung-Jong ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 7~14
Various sizes of hydrazine monopropellant thruster have been used on satellite and space launcher vehicle. The test and handling procedure of hydrazine monopropellant thruster are usually difficult because of the toxicity of hydrazine and its decomposition product gases. Therefore, the numerical analysis can help understand the effects of various design parameters and can reduce the time as well as expenses. In this study, the numerical analysis is performed by modelling the catalyst bed as one dimensional porous medium. Thereby, resulting physical phenomena are examined by considering the variation of catalyst bed characteristics incurred by catalyst granule failure.
Combustion Modeling of Nano/Micro Aluminum Particle Mixture
Yoon, Shi-Kyung ; Shin, Jun-Su ; Sung, Hong-Gye ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 15~25
One dimensional combustion modeling of aluminum combustion behavior is proposed. Combustion model is assumed that region consists as follows ; preheat, reaction, post reaction region. Flame speed as a function of particle size, equivalence ratio for unitary particles and fraction ratio of micro to nano particle size for binary particles were investigated for lean burn condition at 1 atm. Results were compared with experimental data. For unitary particles, flame speed increase as particle size decreases, but opposite trend with equivalence ratio. For binary particles, flame speed increases proportionally as nano particle fraction increases. For flame structure, separated or overlapping flames are observed, depending on the fraction of nano sized particles.
Cold flow Test and Ignition Test of a 75-tonf-Class Thrust Chamber with Ablative Material for Technology Demonstration
Lee, Kwang-Jin ; Kim, Jong-Gyu ; Kim, Mun-Ki ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 26~37
A 75-tonf-class LRE(liquid rocket engine) thrust chamber with ablative material for technology demonstration was manufactured on the basis of development technologies of 30-tonf-class LRE. Hydraulic characteristics of the thrust chamber were examined through cold flow test and ignition test of low flow condition. Test result showed that hydraulic function was good. Side ignition method with igniter ring also showed a fine function of ignition in operating ways of static condition. But a close review is required to understand the phenomena of generation and extinction of specific frequencies showed in dynamic characteristics ways. To achieve these, a large combustion test facility which is capable of performing combustion test at design condition of the 75-tonf-class thrust chamber should be constructed as soon as possible.
Development of Numerical Code for Interior Ballistics and Analysis of Two-phase Flow according to Drag Models
Sung, Hyung-Gun ; Jang, Jin-Sung ; Yoo, Seung-Young ; Roh, Tae-Seong ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 38~46
In order to simulate the ignition-gas injection in the interior ballistics, a two-dimensional analytic code for two-phase flows has been developed. The Eulerian-Lagrangian approach and the low-dissipation simple high-resolution upwind scheme(LSHUS) have been adopted in the numerical code for the propellant combustion of the gun propelling charges. The ghost-cell extrapolation method has been used for the moving boundary in the chamber with the projectile movement. The calculation results of the developed code have been compared and verified through those of the dimensionless IBHVG2 code and the previous one-dimensional code. In comparison with the two-phase flows according to the drag models, the numerical analysis of the muzzle velocity has been affected by the drag model.
Numerical Analysis of the Effect of Rounded Tube at the Counter Flow Manifold on the Performance of a Heat Exchanger Used in High Temperature and High Pressure System
Kim, Sang-Jo ; Choi, Byoung-Ik ; Kim, Kui-Soon ; Son, Chang-Min ; Ha, Man-Young ; Jeong, Ji-Hwan ; Go, Jeong-Sang ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 47~55
The present paper deals with numerical analysis to investigate the effect of rounded tube on the pressure drop and heat transfer in a compact tubular heat exchanger designed for high temperature and high pressure system. The pressure drop and heat transfer in the tubular heat exchanger greatly depend on the location of rounded tubes. The effect of locations of the rounded tubes was also analyzed. Three different locations which were tube inlet, tube outlet, and inlet&outlet were considered. In this paper, the tube with a rounded inlet&outlet showed the minimum pressure drop with decreased heat transfer while the tube with a rounded outlet showed better characteristics of pressure drop and heat transfer compared with the results of original model.
A Study on Design of a Catalytic Ignitor for Liquid Rocket Engine using Hydrogen Peroxide and Kerosene
Chae, Byoung-Chan ; Lee, Yang-Suk ; Jun, Jun-Su ; Ko, Young-Sung ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 56~62
An experimental study on design of a catalytic ignitor was performed to use an ignition source for a small bi-propellant liquid rocket engine which use hydrogen peroxide and kerosene as propellants. In the catalytic ignitor, hot gas of hydrogen peroxide which was decomposed by a catalyst induced autoignition of kerosene. Mass flow rate and O/F ratio for the ignitor were calculated by CEA code. A combustion chamber which had a quartz window and thermocouples was manufactured to determine whether the ignition is successful. Ignition performance was investigated according to exit area of fixed rings and mixture ratio. Results showed that reliable ignition performance was achieved at non-choking exit area of fixed ring and O/F ratio of 6~8.
Development of Transient Simulation Program for Smart UAV Propulsion System
Lee, Chang-Ho ; Ki, Ja-Young ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 63~69
The Smart UAV must have the control characteristics of propulsion system necessary for both rotary aircraft and fixed wing aircraft though it equips turbo-shaft engine. To develop an electronic engine controller in the future, it is necessary to accumulate the experience of engine operation and data of tilt rotor aircraft. For this purpose, the computer programs which predict engine performance in the steady state and transient state can be utilized for the supplementation of flight test data. In this work, we developed a dynamic analysis program using engine performance data gathered during the flight tests. In addition the accuracy of the program was verified through comparison with flight test data and the results of steady-state performance analysis program.
Analysis of Dynamic Characteristics and Performances of Vent-Relief Valve
Jang, Je-Sun ; Koh, Hyeon-Seok ; Han, Sang-Yeop ; Lee, Kyung-Won ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 70~77
A ventilation-relief valve performs as a safety-valve assembly for the liquid-propellant feeding system of space launch vehicle. This valve plays a role of relieving the vaporized propellants from propellant tanks during the filling and storing stages of propellants. Also it regulates to maintain the pressure of ullage volume of on-board propellant tanks within the safety-margin during the flight. The simulation model of ventilation-relief valve is designed with AMESim to predict and evaluate the dynamic characteristics and pneumatic behaviors of valve. To validate a valve simulation model, the simulation results of the opening and closing pressures and their operating durations of valve by AMESim analysis are compared with the results of mathematical methods. In addition, the results of internal flow simulation with FLUENT are utilized to improve the accuracy of valve-modeling. This study will serve as one of reference guides to enhance the developmental efficiency of ventilation-relief valves with the various operating conditionss, which shall be used in Korea Space Launch Vehicle-II.
A Survey on Dynamical Modeling for Active Control of Thermo-Acoustic Instabilities
Na, Seon-Hwa ; Ko, Sang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 78~90
This paper surveys the recent research activities regarding dynamical modeling of thermo-acoustic instabilities which are fundamental to actively control such phenomena in gas-turbine engines, rockets, and etc. For this, we introduce reduced-order modeling approaches, mainly conducted after 1990s. Particularly, we survey grey-box approaches, which determine the structure of the model based on physical rules and use system's input-output data for estimating parameters of the model. We also introduce black-box approaches using model structures without physics-based interpretation. Finally, we briefly discuss future directions and feasibilities of the research in this field.
Definition of Engine Component Performance Test Range of 75tf Class Gas Generator Cycle Liquid Propellant Rocket Engine
Nam, Chang-Ho ; Moon, Yoon-Wan ; Seol, Woo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 91~97
A test range for a 75tf class gas generator cycle liquid propellant rocket engine is defined. The engine system test range is defined by the performance variation during flight, the dispersion after engine calibration, and additional margin. The component development test range includes the operation range corresponding to the engine system test range and the component performance margin.
Introduction to Thermoacoustic Models for Combustion Instability Prediction Using Flame Transfer Function
Kim, Dae-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 6, 2011, Pages 98~106
This paper reviews the state-of-the-art thermoacoustic(TA) modeling techniques and research trend to predict major parameters determining combustion instabilities in lean premixed gas turbine combustors. Linear TA modeling results give us an information on eigenfrequencies and initial growth rate of the instabilities. For the prediction, linear relation equation between acoustic waves and heat release oscillations should be derived in the determined system. Key information for this analysis is to determine the heat release fluctuations in the combustor, which is typically obtained by using n-
function from flame transfer function measurements and/or predictions. Great advancement in the linear TA modeling has been made over a couple of decades, and some successful prediction results have been reported in actual gas turbine combustors. However nonlinear TA model developments which are required to analyze nonlinear system behaviors such as limit cycle saturation and transition phenomena are still limited in a very simple system. In order to fully understand combustion instabilities in a complicated real system, nonlinear flame dynamics and acoustic wave interaction with nonlinear system boundary conditions should be explained from the nonlinear TA model developments.