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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
Editor in Chief :
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
Effect of Weber Number and Momentum Flux Ratio on Macroscopic Characteristics of Spray from a Coaxial Porous Injector
Kim, Do-Hun ; Seo, Min-Kyo ; Lee, In-Chul ; Koo, Ja-Ye ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 1~9
DOI : 10.6108/KSPE.2012.16.5.001
The gas jet from a coaxial porous injector for two-phase flows is discharged from the porous surface, which encloses the center liquid jet, and the gas and liquid jet interact with each other physically. The wall injected gas jet transfers the radial momentum effectively while the radial gas jet develops to axial jet, and the performance of atomizing and mixing can be improved. In this study, the Weber number and the ratio of momentum flux were controlled by changing the gas injection area and the mass flow rate of the gas jet, and a study on the spray characteristics at the cold-flow test using water and air simulant was performed. It is concluded that the radial momentum transfer concept of a coaxial porous injector gives a positive effect on the atomization and mixing of the two-phase spray.
Study of Flame Structure by Chemiluminescence and Laser Diagnostics in Model Gas Turbine Combustor
Yoon, Ji-Su ; Kim, Min-Ki ; Lee, Min-Chul ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 10~19
DOI : 10.6108/KSPE.2012.16.5.010
To eliminate the onset of combustion instabilities and develop effective approaches for control, flame structure is very important. In this study, we conducted experiments under various operating conditions with a model gas turbine combustor to examine the relation of combustion instability and flame structure by OH chemiluminescence and laser diagnostics of He-Ne laser absorbtion system. The swirling LNG(
)/air flame was investigated with overall equivalence ratio of 1.2 and dump plane fuel-air mixture velocity 25 ~ 70 m/s. We founded that the combustion instability phenomenon occurs at lower mixing velocity and higher mixing velocity conditions. We also concluded that fluid dynamical vortex frequency has major effects on the combustion instability characteristics at lower mixing velocity condition.
Storability and Material Compatibility Test of Blended Hydrogen Peroxide Propellant
Lee, Jeong-Sub ; Jang, Dong-Wuk ; Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 20~28
DOI : 10.6108/KSPE.2012.16.5.020
Blending method was applied to increase the performance of hydrogen peroxide which is called green propellant. 90 wt.% hydrogen peroxide was blended with ethanol which is less toxic fuel, and there was no storability decrease due to fuel addition. Inconel X750 and Tophet A showed good compatibility and high heat resistance, and SUS 316L was compatible.
, were coated on the material to improve heat resistance, and it was proved from endurance test that
coating is not suitable and adhesive strength between coating and material is related with allowable temperature of material. Thruster test was performed to confirm the performance increase by blending method, and chamber temperature was
which is higher than
that is adiabatic chamber temperature of 90 wt.% hydrogen peroxide.
Case Study on Combustion Stabilization in FASTRAC Thrust Chamber Using Acoustic Cavities
Kim, Hong-Jip ; Kim, Seong-Ku ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 29~36
DOI : 10.6108/KSPE.2012.16.5.029
3-D linear acoustic analysis has been performed to elucidate damping characteristics of large Helmholtz acoustic cavities in FASTRAC thrust chamber. Acoustic impedance concept has been introduced to quantify combustion stabilization capacity. For a given acoustic cavity, sonic velocity in the cavity to achieve an optimal tuning has been determined and satisfactory agreement with the previous results has been obtained. Feasible estimation of sonic velocity in the acoustic cavity has been devised. Results show similar trends without significant deviations, which can be used in the procedure of design and verification of acoustic cavity. From the satisfactory results, investigation of other thrust chambers with acoustic cavities which have shown combustion instabilities will be done as future works.
Transient Thermal Analysis on Wall Temperature Change of Rocket Engine Combustion Chamber Considering Film-Cooling
Ha, Seong-Up ; Lee, Seon-Mi ; Moon, Il-Yoon ; Lee, Soo-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 37~46
DOI : 10.6108/KSPE.2012.16.5.037
The calculation model for heat transfer analysis of rocket engine combustion chamber considering film-cooling has been established. Convective, radiative heat transfers and film-cooling effect in combustion chamber were evaluated using empirical equations especially for rocket engine combustors, and for heat transfer outward from chamber wall general convective and radiative equations were applied. Structural grid has been generated inside chamber wall for FVM calculations, and transient thermal analyses were carried out by time-marching techniques. LOx/kerosene rocket engine with chamber pressure of 50 bar has been analysed, and it is shown that, in that case, the film-cooling less than 4% remarkably contributes to reduce wall temperature, but the effect of the effect of film-cooling more than about 4% is not significantly increased.
A Study on Development of Reaction Rate Equation for Reactive Flow Simulation in Energetic Materials
Kim, Bo-Hoon ; Yoh, Jai-Ick ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 47~57
DOI : 10.6108/KSPE.2012.16.5.047
A modified ignition and growth(I&G) model which is necessary to simulate the combustion phenomena of energetic materials and an analytical model determining the unknown parameters of the reaction rate equation are proposed. The modified I&G model sustains important physical implications with overcoming some problems of previous rate equations. This rate model consists of ignition term which represents the formation of the hotspot due to void collapse and growth term which means the shock to detonation transition phenomena. Also, the theoretical model is used to investigate the combustion characteristics of certain energetic materials before running Hydrocode by pre-determination of unknown parameter,
. The analytical model provides efficient and highly accurate results rather than previous method which simulated the unconfined-rate-stick via the numerical means.
Effects of Flight Conditions on IR Signature from Aircraft Exhaust Plume
Go, Gun-Yung ; Kim, Man-Young ; Baek, Seung-Wook ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 58~66
DOI : 10.6108/KSPE.2012.16.5.058
The IR signature and radiative base heating from an aircraft plume have been important factors for aircraft survivability in modern battle fields. In order to enhance the aircraft survivability and reduce the base heating, infrared signatures emitted from an aircraft exhaust plume should be determined. In this work, therefore, IR signatures and radiative base heating characteristics are examined in the plume exhausted from the aircraft with operating at altitude of 5 km in M
A Study on Failure Assessment Diagrams for a Solid Propellant
Ha, Jae-Seok ; Kim, Jae-Hoon ; Yang, Ho-Young ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 67~73
DOI : 10.6108/KSPE.2012.16.5.067
Failure mechanisms for a solid propellant were discussed, and the stip-yield and the inherent flaw models were applied to them. Then, failure assessment diagram methods were investigated by means of modified two models. Fracture toughness tests using CCT(center-cracked tension) specimens made of a solid propellant were conducted to generate the failure assessment diagrams. The failure assessment diagram of the inherent flaw model was normalized in order to compare with that of the modified strip-yield model. From the comparison of two failure assessment diagrams, it was found that the failure assessment diagram of the modified inherent flaw model more conservatively assesses the failure than that of the modified strip-yield model.
An Experimental Study on Micro Shock Tube Flow
Park, Jin-Ouk ; Kim, Gyu-Wan ; Kim, Heuy-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 74~80
DOI : 10.6108/KSPE.2012.16.5.074
Past few years have seen the growing importance of micro shock tubes in various engineering applications like micro combution, micro propulsion, particle delivery systems. But in order to efficiently apply Micro Shock Tube to such areas require the detailed knowledge of shock characteristics and flow field inside a micro shock tube. Due to many factors such as boundary layer, low Reynolds number and high Knudsen number shock propagation inside micro shock tubes will be quite different from that of the well established macro shock tubes. In the present study, experimental studies were carried out on micro shock tubes of two diameters to investigate flow characteristics and shock propagation. Pressure values were measured at different locations inside the driven section. From the experimental values other parameters like shock velocity, shock strength were found and shock wave diagram was constructed.
Burst Test of Cast Al-Alloy Casing for Liquid Rocket Engine Turbopump
Yoon, Suk-Hwan ; Jeon, Seong-Min ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 81~88
DOI : 10.6108/KSPE.2012.16.5.081
Turbopump is a key component in liquid rocket engines, and reducing weight while maintaining structural safety is one of the major concerns of turbopump designers. To reduce the weight aluminium alloy castings instead of steel casings are introduced. The casting process is especially useful for enhancement of productivity and for reduction of product costs. But, since castings are used in space vehicle engines, reliability cannot be compromised. Therefore, proper design, production process and thorough investigation should be performed to ensure structural integrity. In this study inlet casings for a fuel pump were casted with A356.0-T6 alloy and using one of them a burst test was conducted to ensure structural integrity. Structural analysis is performed for simulation, and with multiple strain gages strains are measured and compared with predictions.
Study on Thickness Measurement about Insulation Rubber of Steel Motor Case Using Ultrasonic Resonance
Kim, Dong-Ryun ; Kim, Jae-Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 89~96
DOI : 10.6108/KSPE.2012.16.5.089
The rubber side could be contaminated using the existing pulse echo method because the ultrasonic wave was incident on the rubber side from the interior of the steel motor case, which could lead to the critical disbond defect. To develop the test method which can be replaced the existing method, the ultrasonic wave was incident on steel face of the steel/rubber adhesive test block. Rubber resonance frequencies measured from the steel/rubber adhesive test block were in good agreement with theoretically predicted rubber resonance frequencies. This paper was described about the ultrasonic resonance method to convert the rubber resonance frequency into the rubber thickness.
Review of the Solid Propulsion Trend in the Launch Vehicle(1)
Lee, Tae-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 97~107
DOI : 10.6108/KSPE.2012.16.5.097
In general, solid propulsion offers cost effective, large thrust capabilities comparing to the liquid propulsion which offers high specific impulse and restart capabilities. Therefore, solid propulsion is well fitted for the first stage and boosters. Building Block Launcher(BBL) approach has been studied for the launch vehicle because of cost effectiveness, limited development time and low risk. Using of the carbon fiber epoxy resin in the solid rocket motor case is expanded, and specially high strength fibers are more attracted since its inert mass reduction.
A Numerical Study on Thermal Analysis of Fuel Shut-off Valve
Baek, Nak-Gon ; Lee, Jae-Yun ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 5, 2012, Pages 108~114
DOI : 10.6108/KSPE.2012.16.5.108
Thermal and fluid flow characteristics in a fuel shut-off valve under operating conditions are studied numerically. The disk size of the valve has 15 mm diameters and maximum mass flow rate is 600 kg/h. The Analysis was performed in the commercial code, STAR-CCM+. This paper shows that results from the numerical analysis has a good agreement compared to experimental results.