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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society of Propulsion Engineers
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Journal DOI :
The Korean Society of Propulsion Engineers
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Volume & Issues
Volume 12, Issue 6 - Dec 2008
Volume 12, Issue 5 - Oct 2008
Volume 12, Issue 4 - Aug 2008
Volume 12, Issue 3 - Jun 2008
Volume 12, Issue 2 - Apr 2008
Volume 12, Issue 1 - Feb 2008
Selecting the target year
An Experimental Study on Effect of Half-Wave Resonator Position on Acoustic Damping in a Combustion Chamber
Sohn, Chae-Hoon ; Kim, Chul-Hee ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 1~7
Effect of radial position of half-wave resonator is investigated experimentally for acoustic damping in a combustion chamber by adopting acoustic cold test. Acoustic damping is quantified by damping factor. When resonator with optimal tuning length is installed, damping is enhanced as its radial location is away from the center of the faceplate. And, spatial profile of damping factor is similar to that of the amplitude of the acoustic mode to be damped. As the location is close to the center, acoustic damping is mitigated and independent of the resonator length. On the other hand, the resonator with non-optimal length dose not show any effects of its radial position. Acoustic-damping capacity can be evaluated as functions of resonator length and position.
A Study on Steady State Performance of Variable Thrust Nozzle by Cold-Flow Test
Kim, Joung-Keun ; Lee, Ji-Hyung ; Oh, Jong-Yun ; Chang, Hong-Been ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 8~14
Solid Rocket Motor(SRM) has advantages such as - high specific impulse, operational safety and simplicity in design and manufacturing process but thrust magnitude can't be controlled. For studying of pintle nozzle that can control the thrust magnitude of SRM, cold flow test and numerical analysis about needle type pintle shape were performed and results were presented in this paper. As the results of this study, pintle tip's shape and nozzle contour were important design parameters because thrust performance and variable thrust range of pintle nozzle depend on them. Especially, the thrust of needle typed pintle nozzle adopted in this test was predicted 13% higher than normal nozzle without pintle.
A Study on Windmilling Start Performance of Micro Turbo-jet Engine
Kim, Wan-Jo ; Park, Hwi-Seob ; Roh, Tae-Seong ; Choi, Dong-Whan ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 15~23
A numerical method based on the prediction of total pressure loss of major components of the engine has been developed for prediction of the windmilling start performance of micro-turbojet engine. The start performance in on/off design region has been analysed by applying this method to predict windmilling start-able regions of the centrifugal-type engine. The results of this analysis have been validated by comparing with the test data. The effect of each design parameters on windmilling start performance has been analysed for the enlargement of start-able regions.
Mixing and Penetration Studies of Transverse Jet into a Supersonic Crossflow
Kim, Chae-Hyoung ; Jeong, Eun-Ju ; Jeung, In-Seuck ; Kang, Sang-Hun ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 24~32
A non-reacting experimental study on a normal injection into a Mach 1.92 crossflow which flows over various geometries(flat plate, small cavity, large cavity) was carried out to investigate the effect of the momentum flux ratio(J). The aft ramp of the cavity advances the increase of the penetration height and the strong two-dimensional shock from recompression region mainly affects the shock structure and mixing layer at the downstream flow. As flow runs downward, the transverse penetration height increases with increasing J(J = 0.9, 1.7, 3.4). However, above some critical ratio, jet penetration height growth with increasing J is not appeared in flow-field. Large scale cavity has a good mixing efficiency but it increases the drag loss in the combustor.
A Computational Study of Flowfield for a Vent Mixer in Supersonic Flow
Kim, Chae-Hyoung ; Jeung, In-Seuck ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 33~39
To improve the mixing efficiency and to reduce the pressure loss, it is needed to develope a new mixing device for supersonic combustion. The vent mixer is introduced as the new supersonic fuel-air mixer. Computational analyses, that include pressure profile, density contour, and streamline tracing, have been carried out. The expansion wave generates at the end of the extended upper wall of the mixer. And it reduces the shock wave from the hole. Incoming air flow through the hole makes several recirculation regions which increase the mixing efficiency, and the separation region at the downward wall expends the boundary layer which reduces the pressure loss.
Study on the Debonding Detection Techniques of Liner/Propellant Interface of Rocket Motor
Kim, Dong-Ryun ; Ryoo, Baek-Neung ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 40~47
It is known that the adhesive interface testing of the rocket motor using the ultrasonic wave is superior to the other testing methods about the ability to economical detect the defects. But, the signal analysis of the ultrasonic wave takes a lot of time and efforts because the time interval of the transmitted pulse and the received pulse is too short to separate the reflected signals due to the multi-layers of the rocket motor. The ultrasonic testing of rocket motor have only applied to the automatic system about extremely limited areas like the debond in adhesive interface between the motor case and the insulator. In this study the new technique to detect the debond between the liner and the propellant using the property of the resonance and the lamb waves instead of the existing ultrasonic testing was described.
Spray Characteristics of the Oxidizer-rich Preburner Injector in High Pressure Environments
Yang, Joon-Ho ; Choi, Seong-Man ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 48~56
In the rocket preburner, oxidizer-rich combustion with liquid oxygen and kerosene is very challenging work. The key factor of stable flame is good mixing and that is controlled by the injector performance. We have studied spray characteristics of the oxidizer-rich rocket preburner injector in high pressure environments. The injector is composed of fuel orifices, oxidizer orifices and cooling skirt with liquid oxygen. By using this apparatus, we have taken photographs and measured Sauter mean diameter with changing ambient pressure from 0 to 30 kgf/cm2[g]. Droplet diameter is measured by the image processing technique. From the test results, we could understand spray characteristics of the oxidizer-rich preburner injector and this result could be applied to the development of the oxidizer rich preburner system.
The Atomization Mechanism and Spray Characteristics of Drum Type Rotary Atomizer
Lee, Dong-Hun ; Choi, Hyun-Kyung ; Choi, Seong-Man ; You, Gyung-Won ; Huh, Hwan-Il ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 57~65
The atomization phenomena and spray characteristics of drum type rotary atomizer using centrifugal force from high rotational speed of gas turbine engine shaft were studied through rotary atomizer modeling analysis and experimental method. A test rig for rotary atomization that has range of
was used to make similarity for high speed rotating shaft. Spray visualization methodology and Phase Doppler Anemometry were also used to investigate the atomization mechanism and spray characteristics. We found that the rotating fuel spray has unique breakup process and we have to make breakup point earlier through increasing rotating speed to improve atomization performance.
Numerical Analysis of Detonation Wave Propagation Characteristics in Annular Channels
Lee, Su-Han ; Cho, Deok-Rae ; Choi, Jeong-Yeol ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 66~73
Present study examines the detonation wave propagation characteristics in annular channels. Numerical approaches used in the previous studies were extended with marching windows technique. Parametric study has been carried out using a radius of curvature normalized by the channel width considered as unique geometric parameter. In the channels of small radius of curvature, detonation wave is unstable and the regular cell structure is not observed. There is a critical radius of curvature where cell structure can be sustained. The effect of curvature makes the pressure difference on inner and outer surfaces where the detonation wave is overdriven. The results converge to that of straight channel as the radius of curvature gets larger, as expected.
Preliminary Study of a Turbopump Pyro Starter
Hong, Moon-Geun ; Lee, Soo-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 2, 2008, Pages 74~80
The feasibility study into the development of turbine spinners, which start up the turbo-pump, has been carried out and the design requirements and parameters ranges have been presented. Turbine spinners use the solid propellant as such composite propellant based AN compound with high energy plasticizers, coolants, and phase stabilizer which relieves a sensible volume change due to the phase transformation of AN near room temperature. Propellants which have a homing rate of
and pressure exponent ranged from 0.3 to 0.6, showed stable burn-out in the standard motor tests. Both the magnitude of ignition energy and its thermal transfer mechanism have been proved to have a tangible effect on the ignition of the pyre starter, and the results of this study showed that a flame temperature of 1400K would be quite adequate to get a stable ignition for the AN composite propellant.