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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 18, Issue 6 - Dec 2014
Volume 18, Issue 5 - Oct 2014
Volume 18, Issue 4 - Aug 2014
Volume 18, Issue 3 - Jun 2014
Volume 18, Issue 2 - Apr 2014
Volume 18, Issue 1 - Feb 2014
Selecting the target year
Turbulent Combustion Characteristics of a Swirl Injector in a Gas Turbine Annular Combustor Using LES and Level-set Flamelet
Kim, Lina ; Hong, Ji-Seok ; Jeong, Won Cheol ; Yoo, Kwang-Hee ; Kim, Jong-Chan ; Sung, Hong-Gye ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 1~9
DOI : 10.6108/KSPE.2014.18.2.001
To investigate the flame dynamics in an annular combustor with single swirl injector, a 3D large-eddy simulation (LES) and a level-set flamelet turbulent combustion model have been implemented. The LM6000 developed by GEAE has been used as the combustor of concern and boundary conditions are based on experimental data. The strong central toroidal recirculation zone induced by the volume expansion of the combustion gas and the vortex breakdown continuously occurred through the procession of the vortex with decreasing strength, are observed.
Heat Sink Measurement of Liquid Fuel for High Speed Aircraft Cooling
Kim, Joongyeon ; Park, Sun Hee ; Hyeon, Dong Hun ; Chun, Byung-Hee ; Kim, Sung Hyun ; Jeong, Byung-Hun ; Han, Jeong-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 10~15
DOI : 10.6108/KSPE.2014.18.2.010
For hypersonic aircraft, increase of flight speeds causes heat loads that are from aerodynamic heat and engine heat. The heat loads could lead structural change of aircraft`s component and malfunctioning. Endothermic fuels are liquid hydrocarbon fuels which are able to absorb the heat loads by undergoing endothermic reactions, such as thermal and catalytic cracking. In this study, methylcyclohexane was selected as a model endothermic fuel and experiments on endothermic properties were implemented. To improve heat of endothermic reaction, we applied zeolites and confirmed that HZSM-5 was the best catalyst for the catalytic performance. The objective is to investigate catalytic effects for heat sink improvement. The catalyst could be applied to system that use kerosene fuel as endothermic fuel.
Measurement of Pressure-coupled Combustion Instability Characteristics : Acoustic Attenuation by Particulate Matter(Al) and Combustion Response of Solid Propellant
Lim, Jihwan ; Lee, Sanghyup ; Yoon, Woongsup ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 16~26
DOI : 10.6108/KSPE.2014.18.2.016
T-Burner tests of an Al/HTPB propellant in conjunction with a Pulsed DB/AB Method were conducted to find an acoustic amplification factor. Aluminum-free and aluminum-heavy propellants were examined. Instant surface ignition was successfully made by the use of a supplementary propellant of fractionally higher reaction rate. With the presence of higher aluminum concentration in the propellants, the pressure perturbations were promptly damped down and the pressure fluctuations were no longer dispersive. Addition of aluminum particles into the propellant was advantageous for stabilizing pressure-coupled unstable waves.
Buzz Margin Control for Supersonic Intake Operating over Wide Range of Mach Number
Park, Iksoo ; Park, Jungwoo ; Lee, Changhyuck ; Hwang, Kiyoung ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 27~34
DOI : 10.6108/KSPE.2014.18.2.027
Buzz margin scheduling and control technique which are suitable to regulate stable and high pressure air in wide range of Mach number are suggested for fixed geometry of a supersonic intake. From the analysis of preceding study, most effective control variable is induced and scheduling law is newly suggested in a real application point of view. The appropriateness of the control law in wide range of Mach number is addressed by numerical simulation of controlled propulsion system. Also, the simulation for stabilization and tracking performances of the controller are studied to investigate the phenomena under flight maneuver and disturbances.
A Study on the Turbopump Rotordynamic Characteristics due to Bearing Housing Structural Flexibility
Jeon, Seong Min ; Yoon, Suk-Hwan ; Kim, Jinhan ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 35~41
DOI : 10.6108/KSPE.2014.18.2.035
A rotordynamic analysis is performed for a turbopump of 7 ton class liquid rocket engine considering bearing housing structural flexibility. Stiffness and damping characteristics of ball bearings and pump noncontact seals are reflected in a rotordynamic model. A dynamic model of bearing housing with lumped mass and stiffness is also applied to the rotordynamic analysis. Rotor critical speed and onset speed of instability are predicted from synchronous rotor mass unbalance response and complex eigenvalue analyses. The bearing housing structural flexibility effect on rotordynamic characteristics is investigated for both of bearing loaded and unloaded conditions respectively. From the numerical analysis, it is found that the effect of the housing structural flexibility significantly reduces the rotor critical speed and onset speed of instability.
A Study on the Effect of Fuel Boiling Point on Injection Characteristics at High Fuel Temperature Conditions
Lee, Hyung Ju ; Choi, Hojin ; Kim, Ildoo ; Jeong, Byung-Hoon ; Han, Jeong-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 42~51
DOI : 10.6108/KSPE.2014.18.2.042
An experiment was conducted to study fuel injection characteristics of high boiling point test fuels (HBPTF), which are newly developed with higher boiling points than conventional aviation fuels, for various injection pressures when the fuel was heated to the temperature higher than their boiling points. The injection characteristics with elevating fuel temperature were quantified by the flow coefficient (
) and the cavitation number (
), and it was found that the trends between
for various fuels were very similar with each other. In addition, compared with a conventional fuel, HBPTFs not only have higher fuel temperatures at which the effect of fuel boiling on the injection initiates, but also are less affected by the fuel boiling inside the injectors at temperatures over the boiling point.
Effect of Thermal Barrier Coating and Film Cooling Condition on the Cooling Performance of Liquid-propellant Rocket Engine Combustor
Joh, Miok ; Kim, Seong-Ku ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 52~59
DOI : 10.6108/KSPE.2014.18.2.052
The effect of ceramic thermal barrier coating thickness on the cooling performance of a liquid-propellant rocket engine combustor has been investigated through combustion/cooling performance analysis whose results verified against measured data from hot-firing tests. Also have been confirmed the effects of film cooling amount near the face plate on the coolant temperature and on the thermal barrier coating surface temperature. Some important points to be considered for designing cooling schemes for regeneratively cooled rocket engine combustor have been drawn and reviewed from present study and further verification of the analysis tool should be performed in the future.
Combustion Stability Rating Test of Liquid Rocket Engine Thrust Chamber
Ahn, Kyubok ; Kim, Jong-Gyu ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 60~66
DOI : 10.6108/KSPE.2014.18.2.060
As a evaluation method of combustion stability in a liquid rocket engine thrust chamber, external disturbance devices are used. In the paper, the study on pulse-gun ignition tests for a combustion stability rating test of a thrust chamber was performed. Charging volume of pulse-guns was determined by confirming the intensities of the pressure waves from the ignition tests in the cold-flow conditions. While using same injector head, combustion instabilities were not encountered during 14 hot-firing tests without pulse-guns but combustion instabilities were triggered by pulse-gun ignition during 2 hot-firing tests. The results showed that the pulse-gun ignition test could be the evaluation method and could reduce the hot-firing test number for the stability rating of a thrust chamber.
Characterization of Carbon Black-filled Liner
Kim, Jeongeun ; Ryu, Taeha ; Hong, Myungpyo ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 67~72
DOI : 10.6108/KSPE.2014.18.2.067
In this study, the viscosity of carbon black filled HTPB liner, mechanical properties and bonding force between propellant and liner were investigated. It is difficult to apply carbon black filled HTPB liner to the motor case in using a horizontal centrifugal casting because of its high viscosity. This problem is solved as a ageing premix at
. The viscosity of premix is drastically decreased from 464 to 200 poise after 6days ageing.
Analytical Study on Equivalent Shear Modulus according to Shape of Egg-box Core
Lee, SangYoun ; Yun, Su-Jin ; Park, DongChang ; Hwang, Kiyoung ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 73~79
DOI : 10.6108/KSPE.2014.18.2.073
The sandwich shell with Egg-box core has been used for the combustion chamber case of air breathing propulsion system. The alteration on pitch length and thickness of Egg-box core was required to be lighter and save manufacturing time and cost of combustion chamber case. In this paper, the finite element analysis method which simulated bending test was used to predict the equivalent shear modulus which affect structural stability of sandwich shell in short time. The result of FE calculation on sandwich panel with homogeneous material, H130-foam core, showed a good agreement with the values available in the reference. The equivalent shear modulus of Egg-box core according to the variation of pitch length and thickness can be obtained.
Development of Side Jet Thruster with Nozzle Closure Separation Device
Han, Houkseop ; Park, Euiyong ; Kim, Dongjin ; Son, Youngil ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 80~85
DOI : 10.6108/KSPE.2014.18.2.080
Side jet thruster using nozzle closure separation device provides a solid rocket with a trajectory shift function. Side jet thruster consists of low combustion temperature propellant, neutral type propellant grain and nozzle closure separation device. If a trajectory shift is required, side jet thrust is generated on the rocket by separating some nozzle closures located in the opposite direction to thrust. After completing trajectory shift, the other nozzle closures located in the thrust direction are separated to cease side jet thrust. The operation process is verified through ground static test. The result in this study can be applied to changing rocket trajectory by controlling side jet thrust through nozzle closure separation.
Modeling and Simulation of O
Gas Supply System of Afterburner for Fuel-rich Gas of Gas Generator
Wang, Seungwon ; Lee, Kwangjin ; Chung, Yonggahp ; Han, Yeoungmin ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 2, 2014, Pages 86~92
DOI : 10.6108/KSPE.2014.18.2.086
Combustion Chamber Test Facility (CCTF) to be constructed in Naro Space Center for re-burning the fuel-rich gas of gas generator have afterburner system. The afterburner system is supplied the Oxygon (
) gas and Methane (
) gas to reduced the harmful exhaust gas. The detailed design for the planned CCTF afterburner system is simulated and analysed by AMESim program through the all of gas supply system components. Afterburner system is performed to verify the pipe size, orifice diameter, and gas supply conditions according to the total gas consumption from analysis of gas supply system.