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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
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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
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A Numerical Study on Effects of Displacement of a Variable Area Nozzle on Flow and Thrust in a Jet Engine
Park, Junho ; Sohn, Chae Hoon ; Park, Dong Chang ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 1~9
DOI : 10.6108/KSPE.2013.17.5.001
Variable area nozzle, where both throat and exit area vary, is required for optimal expansion and optimal nozzle shape upon operation of after-burner. Steady-state and transient analyses are carried out for each condition with and without afterburner operation and as a function of the location of the nozzle flap. Effects of that nozzle displacement on flow and thrust characteristics are analyzed from numerical results. With variable area nozzle adopted, the combustion field is variable in time, leading to periodically variable thrust. For off-design conditions, flow separation shows up due to over expansion at the flap tips and shock wave does in the nozzle due to under expansion. The undesirable phenomena can be solved by control of variable area nozzle.
The Study on Minimum Smoke Propellant to Reduce Afterburning Reaction
Yim, Yoojin ; Lee, Jongseop ; Park, Euiyong ; Choi, Sunghan ; Yoo, Jichang ; Cho, Young ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 10~17
DOI : 10.6108/KSPE.2013.17.5.010
This paper describes a study on after-burning suppressant in a solid propellant to reduce the plume formed outside of rocket nozzles, which could expose the launch site and the flight track. The minimum smoke propellant to enhance the stealth ability was formulated in terms of the kinds and the effects of after-burning suppressant on the ballistic performance and the amount of primary smoke. A after-burning suppressant,
of about 1.1% weight content was found to show profound reduction of the rocket plume, giving negligibly slight increase in pressure exponent of burning rate. Also minimum smoke propellant with less than 1.1% of
corresponds to A-class satisfaction in primary smoke by AGARD standard.
Study of the Inhibition on the Combustion of PEBAX/AP Thermoplastic Propellant
Lee, Hyoungjin ; Jung, Haeyoung ; Cho, Junhyun ; Lee, Youngguen ; Lee, Hojin ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 18~26
DOI : 10.6108/KSPE.2013.17.5.018
This study suggested techniques to reduce burning rate and their effects for the AP thermoplastic composite propellant. Burning rate obtained through ground tests using a small size motor were analyzed to investigate the effects of AP particle size and LiF of 0.5~2.0% on the inhibition reaction for the PEBAX/AP thermoplastic propellant. The results showed that utilization of large size particle of AP and addition of LiF under 2.0% can reduce the burning rate sufficiently and their quantitative effects were suggested in this paper.
Linear Stability Analysis for Combustion Instability in Solid Propellant Rocket
Kim, Hakchul ; Kim, Junseong ; Moon, Heejang ; Sung, Honggye ; Lee, Hunki ; Ohm, Wonsuk ; Lee, Dohyung ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 27~36
DOI : 10.6108/KSPE.2013.17.5.027
Linear stability analysis for combustion instability within a cylindrical port of solid rocket motor has been conducted. The analysis of acoustic energy has been performed by a commercial COMSOL code to obtain the mode function associated to each acoustic mode prior to the calculation of stability alpha. An instability diagnosis based on the linear stability analysis of Culick is performed where special interests have been focused on 5 stability factors(alpha) such as pressure coupling, nozzle damping, particle damping and additionally, flow turning effect and viscous damping to take into account the flow and viscosity effect near the fuel surface. The instability decay characteristics depending on the particle size is also analyzed.
Combustion Performance of a Coaxial Porous Injector using Ethanol/N
Kim, Dohun ; Lee, Keonwoong ; Koo, Jaye ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 37~46
DOI : 10.6108/KSPE.2013.17.5.037
The gas jet from a coaxial porous injector for two-phase flows is discharged radially from the porous surface, which encloses the center liquid jet. Several hot-firing test using ethanol/nitrous oxide propellants was conducted to analyze the effect of oxidizer/fuel ratio on the combustion performance, and the uncertainty analysis was performed for the results. The characteristic velocity was affected by oxidizer/fuel ratio similarly with the results of CEA calculation except that the maximum characteristic velocity was appeared in the stoichiometric ratio. The characteristic velocity efficiency was increased as the oxidizer/fuel ratio increases.
Optical Diagnostic Study for Flame Characteristic Analysis in Aluminum Dust Clouds
Lee, Sanghyup ; Ko, Taeho ; Lim, Jihwan ; Lee, Dohyung ; Yoon, Woongsup ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 47~53
DOI : 10.6108/KSPE.2013.17.5.047
In this study, In order to develop the measurement method of high energy density metal aluminum dust cloud combustion, flame temperature and emission spectrum was measured using spectrometer. Because of the ultra high
-sized aluminum flame temperature more than 2400 K, it was measured by non-contact optical technique which is the modified two wavelength pyrometry with 520, 640 nm and spectrum comparison method. These methods were applied to experiment after accurate verification. As a result, we could identify that flame temperature is more than 2400 K in bottom of combustor in both methods. And on the emission spectrum analysis, we could measure AlO radical which is occurred dominantly in aluminum combustion.
Experimental Study of the Shock Wave Dynamics in Micro Shock Tube
Park, Jinouk ; Kim, Gyuwan ; Kim, Heuydong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 54~59
DOI : 10.6108/KSPE.2013.17.5.054
Micro shock tubes are now-a-days used for a variety engineering applications such as in the field of aerospace, combustion technology and drug delivery systems. But the flow characteristics of micro shock tube will be different from that of well established conventional macro shock tube under the influence of very low Reynolds number and high Knudsen number formed due to smaller diameter. In present study, experimental studies were carried out to a closed end (downstream) Micro Shock Tube with two different diameters were investigated to understand the flow characteristics. Pressure values were measured at different locations inside the driver and driven section. The results obtained show that with the increase in diameter the shock propagation velocity increases as well as the effect of reflected shock wave will be more significant under the same diaphragm rupture pressure.
Development of Hybrid/Dual Jet Combustor for a MGT (Part I: Experimental Study on Geometric Optimization)
Park, Tae-Joon ; Hwang, Cheol-Hong ; Lee, Kee-Man ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 60~69
DOI : 10.6108/KSPE.2013.17.5.060
An optimum configuration of the hybrid/dual swirl jet combustor for a micro-gas turbine was investigated experimentally. Location of pilot nozzle, angle and direction of swirler vane were varied systematically as main parameters under the conditions of constant thermal load. The results showed that the variation in locations of inner fuel nozzle and pilot burner resulted in significant change in flame shape and swirl intensity due to the changes in recirculating flow pattern and minimum flow area near burner exit, in particular, with the significant reduction of CO emission near lean-flammability limit. In addition, it was observed that the co-swirl configuration produced less CO and NOx emissions compared to the counter-swirl configuration.
Development of Hybrid/Dual Swirl Jet Combustor for a MGT (Part II: Numerical Study on Isothermal Flow)
Mun, Sun-Yeo ; Hwang, Cheol-Hong ; Lee, Kee-Man ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 70~79
DOI : 10.6108/KSPE.2013.17.5.070
The isothermal flow structure and mixing characteristics of a hybrid/dual swirl jet combustor for micro-gas turbine (MGT) were numerically investigated. Location of pilot burner, swirl angle and direction were varied as main parameters with the identical thermal load. As a result, the variations in location of pilot nozzle, swirl angle and direction resulted in the significant change in turbulent flow field near burner exit, in particular, center toroidal recirculation zone (CTRZ) as well as turbulent intensity, and thus the flame stability and emission performance might be significantly changed. With the comparison of experimental results, the case of swirl angle
and co-swirl flow including optimum location of pilot burner were chosen in terms of the flame stability and emissions for the development of hybrid/dual swirl jet combustor.
A Probabilistic Structural Design Method of Composite Propulsion System
Hwang, Tae-Kyung ; Kim, Hyung-Kun ; Kim, Seong-Eun ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 80~85
DOI : 10.6108/KSPE.2013.17.5.080
This paper describes a probabilistic structural design method of composite propulsion system by comparing safety factor based on average value and allowable value with structural reliability. Generally, the required structural safety factor and reliability of composite pressure vessel are 1.5 and 0.999, respectively. In the case of structural design using average strength, the safety factor which satisfies the required structural reliability depends on the variation of fiber strength. However, the structural design using allowable value shows constant safety factor for the variation of fiber strength, because the allowable value of fiber strength is calculated by considering the variation of fiber strength. Through the analysis results, it was known that the fiber strength is the most important design random variable for the structural design of composite pressure vessel and the variation of fiber strength must be minimized to develop the high performance composite propulsion system.
Experimental Study on Dynamic Characteristics of an Impinging Jet Injector
Kim, Jiwook ; Chung, Yunjae ; Lee, Ingyu ; Yoon, Youngbin ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 86~94
DOI : 10.6108/KSPE.2013.17.5.086
Research on dynamic characteristics of injectors gives us insight for preventing combustion instability in a rocket engine. While lots of studies have been done about swirl injectors` dynamic characteristics, little is known about impinging jet injectors` dynamic characteristics. For this reason, this study was aimed to reveal the dynamic characteristics of an impinging jet injector based on experiment using a hydraulic mechanical pulsator. Gain, which is the relationship between input pressure and output value(pressure or velocity) was analyzed with the frequency and manifold pressure change. Pulsating frequency was chosen in the low range: 5, 10, 15 Hz. As a background work, Methods to determine the jet velocity were discussed. Klystron effect was also considered as a factor of this experiment.
A Study on Wear Properties of Solid lubricating Greaphite Materials
Yang, Hoyoung ; Kim, Jaehoon ; Kim, Yeonwook ; Ha, Jaeseok ; Park, Sunghan ; Lee, Hwankyu ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 95~100
DOI : 10.6108/KSPE.2013.17.5.095
The important design factors for designing solid lubricating of dynamic seal are tightness, wear resistance and lubricant films. In this study, the effect factors influenced solid lubricating properties of the graphite were analyzed and wear behaviour caused for various test conditions was compared with results obtained from reciprocating wear tests. Also the optimal conditions for formation of lubricant films were investigate to evaluate wear properties of graphite materials. The repeated procedure for the formation of wear particles and lubricant films, and the dissipation of lubricant films was estimated the wear mechanisms with changes of wear depth. Therefore the lubricant film of graphite seal was generated by adhesion of wear particles on the worn surface and it was very useful in wear characteristics.
Analysis on the Modification of Near-wall Turbulent Characteristics of Temperature Field in a Channel imposed with Linearly Increasing Wall Disturbance
Park, Soo Hyung ; Byun, Yung-Hwan ; Na, Yang ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 101~112
DOI : 10.6108/KSPE.2013.17.5.101
Large eddy simulation was performed to investigate the effect of linearly increasing wall disturbance on the modification of turbulent characteristics of temperature field in the vicinity of the wall. It was noted that temperature variance increased monotonically whereas temperature dissipation decreased significantly, resulting in a noticeable reduction in both time and length-scales. A sudden drop in turbulent Prandtl number down to around 0.25 in the near-wall region indicated that the similarity between velocity and temperature fields decreases near the wall as a result of linear wall disturbance.
A Study of Wear Behavior for Sealing Graphite at Elevated Temperature
Kim, Yeonwook ; Kim, Jaehoon ; Yang, Hoyoung ; Park, Sunghan ; Lee, Hwankyu ; Kim, Bumkeun ; Lee, Seungbum ; Kwak, Jaesu ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 113~120
DOI : 10.6108/KSPE.2013.17.5.113
Graphite is commonly used as a solid lubricant leading to low friction coefficient and abrasion. In this study, wear behavior of sealing graphite(HK-6) at elevated temperature was evaluated. Reciprocating wear test was carried out as wear occurred graphite as a seal(HK-6) is positioned between the liner and driving shaft. Variables which are temperature, sliding speed and contact load are set. This study suggest optimized environment conditions through the wear properties of graphite.
An Experimental Study on the Flame Dynamics in Ducted Combustor
Jeong, Chanyeong ; Kim, Taesung ; Song, Jinkwan ; Yoon, Youngbin ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 121~131
DOI : 10.6108/KSPE.2013.17.5.121
The characteristics of flame dynamics occurring near the bluff body was experimentally investigated in a model combustor with V-gutter bluff body. Measurements of chemiluminescence with high speed camera and PIV were performed for visualization of flame structure. Flashback occurs due to the change of pressure gradient in the combustor, and the flashback distance depends on equivalent ratio. Unstable flames can be classified into three types depending on the flashback distance and structure. When the flame goes over the bluff body, an unusual flame structure occurs at the front of the bluff body. Re-stabilization takes place as the flame moves downstream of the combustor. This process is supported by a strong vortex structure behind the bluff body.
Review of the Liquid Propulsion Technology
Lee, Tae Ho ; Lee, Chang-Hoan ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 5, 2013, Pages 132~139
DOI : 10.6108/KSPE.2013.17.5.132
Liquid-propellant rocket engines are widely used all over the world, thanks to their high performances thrust, in particular high thrust-to-weight ratio. The sucess rate of the launching of the liquid propulsion is similar to the solid one even though it has more complex mechanical system. In general, liquid propulsion is seemed as a mature technology, the requirements of a renewed interest for space exploration has led to the development of a family of new engines, with more design margins, simpler to use and to produce associated with a wide variety of thrust and life requirements.