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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
Editor in Chief :
Volume & Issues
Volume 11, Issue 6 - Dec 2007
Volume 11, Issue 5 - Oct 2007
Volume 11, Issue 4 - Aug 2007
Volume 11, Issue 3 - Jun 2007
Volume 11, Issue 2 - Apr 2007
Volume 11, Issue 1 - Feb 2007
Selecting the target year
Model Scramjet Engine Design for Ground Test
Kang, Sang-Hun ; Lee, Yang-Ji ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 5, 2007, Pages 1~13
Scramjet engine is one of the most promising propulsion systems for future transport. For the ground test with T4 shock tunnel, model scramjet engine is designed. Design flight Mach number is 7.6 and flight altitude is 30km. Engine intake is designed by Levenberg-Marquardt optimization method and Korkegi relation. Furthermore, cowl cut out region is installed by the rule of Kantrowitz limit. Inside the combustor, cavity type flame holder is installed. Cavity is designed by Rayleigh line relation and PSR model. Numerical analysis is performed for the design confirm.
The Effect of Inside and Outside Fluids on the Optimization of a Reversed Trapezoidal Fin
Kang, Hyung-Suk ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 5, 2007, Pages 14~22
A reversed trapezoidal fin with variable lateral surface slope is optimized using a two-dimensional analytic method. For a fin base boundary condition, convection from the inside fluid to the inside wall and conduction from the inside wall to the fin base are considered. Heat loss from the fin tip surface is not ignored. The maximum heat loss at the practical fin length, the corresponding optimum fin efficiency, fin length and fin base height are presented as a function of the fin inside and outside convection characteristic numbers. One of the results shows that the optimum fin shape becomes 'fatter and shorter' as the ratio of fin tip height to base height increases.
Study on Dynamics Modeling of Pogo Suppression Device (PSD)
Lee, Jun-Kyoung ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 5, 2007, Pages 23~30
The effectiveness of a pogo suppression device (PSD) on the response of piping system simulating the propellant supply lines of the rocket engines was investigated experimentally by other researchers. In this study, the simplified analytical model was made, and the key parameters which are difficult to derive theoretically were identified in combination with the previous experimental work. In other words, the flow transient equations for a PSD system and the key parameters used to decide the instability of the system from the linearized transfer function including inertance, compliance, and resistance were derived. From the analysis, the values of key parameters could be determined from the experimental results.
Combustion Performance Characteristics of a High Pressure Sub-scale Liquid Rocket Combustor
Kim, Jong-Gyu ; Lee, Kwang-Jin ; Seo, Seong-Hyeon ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 5, 2007, Pages 31~36
Combustion performance characteristics of subscale high-pressure combustor were investigated at 70 bar combustion pressure. All tests were successfully performed without any damage on the combustor. The mixing characteristics and distribution pattern of the injectors were found to have considerable influence on the combustion performance. The characteristic velocity of the combustor was higher in the injector with internal mixing than that of external mixing and in the injector with smaller mass flowrate. The pressure fluctuations at the propellant manifolds and the combustion chamber were measured to be less than 3% of the mean combustion pressure to meet the combustion stability criterion and to prove stable combustion characteristics of the combustor.
Development and Validation of Spray Model of Coaxial Swirl Injector Installed in Liquid Propellant Rocket Engine
Moon, Yoon-Wan ; Seol, Woo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 5, 2007, Pages 37~50
This study investigated the characteristics of spray generated by a liquid coaxial swirl injector used in a combustor of the liquid rocket engine. The linear stability analysis considered long and short wave was introduced in liquid sheet breakup. Through the hydrodynamic analysis the initial liquid sheet thickness spray angle and injection velocity were predicted. To evaluate the effect of turbulence model standard
model were applied to numerical calculation and it was known that RNC
model was more applicable to predict spray characteristics. On the basis of this evaluation validation of the developed model was performed with swirl injector installed in LPRE and the predicted results of breakup length, spray angle, and SMD agreed well with experiments qualitatively and quantitatively.
Reactive Flow Fields Analysis of End-Bunting Combustor with Different Impinging Type Injectors
Min, Moon-Ki ; Kim, Soo-Jong ; Yoon, Chang-Jin ; Kim, Jin-Kon ; Moon, Hee-Jang ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 5, 2007, Pages 51~59
The end-burning combustion field using impinging oxidizer injectors are analyzed with tangential type injectors in order to examine their mixing and combustion characteristics. The impinging type showed further improved mixing effect as well as the combustion efficiency compared to the previously studied tangential injector. A novel injector capable of delivering impinging and swirl effect is introduced in this study where it demonstrated that the grain coning effect can be avoided. It was found that the combined impinging and swirling flow would promote the radial mixing rate increasing the residence time and the turbulent intensity. However, the use of the step combustor which may augment the turbulent intensity did not show any notable difference compared to the basic combustor.
Numerical Analysis on the Startup of a Rocket Engine
Park, Soon-Young ; Seol, Woo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 5, 2007, Pages 60~71
The startup characteristic of liquid propellant rocket engine should be focused on the stable ignition of combustion chamber and gas generator. Also, to lessen the propellants consumption during this period which doesn't contribute to the flight thrust, the engine has to be transferred to the nominal mode quickly. Because of the risk of test, it is impossible to develop all the startup cyclogram or the specifications of engine by test, so the precedent numerical approach is quite necessary. In this study we developed a mathematical model for the startup phenomena in a liquid rocket engine driven by gas generator-turbopump system based on the commercial 1-D flow system analysis program, Flowmaster. Using this program we proposed a methodology to obtain the specifications of turbine starter and the opening time of shutoff valves for the stable startup of the engine. To verify this methodology we qualitatively compared the analysis results to the typical startup curve of the published engine, then found it is quite well matched.
Combustion Tests of Sub-scale Combustor for a Liquid Rocket Engine with Internal Mixing Swirl Injector
Han, Yeoung-Min ; Lee, Kwang-Jin ; Lim, Byoung-Jik ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 5, 2007, Pages 72~77
The combustion test results of the sub-scale combustor having dual swirl injector with internal mixing for a liquid rocket engine are described. The sub-scale combustor uses liquid oxygen(LOx) and kerosene as propellants and has an injector head, an ablative material combustor wall and a water cooled nozzle. The injector head has LOx manifold, fuel manifold, fire face plate, one center swirl injector and 18 main swirl injectors of internal mixing. The combustion tests were successfully performed at design and off-design points without any damages on the injectors. Combustion characteristics velocity of 1756m/s was measured at design point. High frequency combustion instability was not observed but low frequency pulsations occurred at off-design conditions.
Hydrocarbon Fuel Heating Experiments Simulating Regeneratively Cooled Channels of LRE Combustor
Lim, Byoung-Jik ; Lee, Kwang-Jin ; Kim, Jong-Gyu ; Yang, Seung-Ho ; Kim, Hui-Tae ; Kang, Dong-Hyuk ; Kim, Hong-Jip ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 5, 2007, Pages 78~84
In the regeneratively cooled combustion chambers of liquid rocket engine using hydrocarbon fuels, coking occurs as the wall temperature increases which results in compounds deposition on the wall of cooling channels. This phenomenon reduces cooling capability of the coolant which finally causes damage to the combustor by overheating of the chamber wall. In this paper, experiment results using an electrical heating equipment to simulate the regeneratively cooled channel are introduced and based on the results the compatibility of copper alloy with hydrocarbon fuel Jet A-1 is investigated.