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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 13, Issue 6 - Dec 2009
Volume 13, Issue 5 - Oct 2009
Volume 13, Issue 4 - Aug 2009
Volume 13, Issue 3 - Jun 2009
Volume 13, Issue 2 - Apr 2009
Volume 13, Issue 1 - Feb 2009
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Spray Structure and Cross-section Characteristics of Pulsed Liquid Jet Injected into a Cross-flow
Lee, In-Chul ; Koo, Ja-Ye ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 2, 2009, Pages 1~8
Present studies of these experiments was conducted to using water, over a range of cross-flow velocities from 42 to 136 m/s, with injection frequencies from 35.7 to 166.2 Hz. In cross-flow field, main parameters of liquid jet for secondary breakup were cross-flow drag rather than pressure pulse frequency. As oscillation of the periodic pressure, liquid jet was moved up and down. Also, a bulk of liquid jet puff was detected at upper field of liquid surface. Because of pressure pulsation frequency, an inclination of SMD for the structured layer was evanescent. Cross-sectional characteristics of SMD at downstream area were non-structured distributions. The tendency of volume flux value for various frequency of pressure pulse was same distribution. And volume flux was decreased when the frequency of pressure pulse increasing.
A Debonding Detection Technique for FRP/Rubber Interface by Ultrasonic Phase Reversal
Kim, Dong-Ryun ; Lim, Soo-Yong ; Chung, Sang-Ki ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 2, 2009, Pages 9~16
The object of this study is to develop new examination technique for detecting debond in adhesive interface of different kinds of materials. Ultrasonic signal was modeled by theoretically analyzing ultrasonic propagation phenomenon of the adhesive interface and debonding interface. The test method using the phase reversal of the debonding interface applied to the FRP/Rubber test block. Aluminum/Rubber test block with the flat bottom hole was manufactured to evaluate quantitatively the minimum detection ability of defects. The pulse echo reflection method and the phase reversal method were mutually compared and it was estimated that the phase reversal method could detect the debond on the basis of the theoretically predicted ultrasonic signal and ultrasonic test data.
Unsteady Internal Ballistic Analysis for Solid Rocket Motors with Erosive Burning
Cho, Min-Gyung ; Heo, Jun-Young ; Sung, Hong-Gye ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 2, 2009, Pages 17~25
A typical unsteady internal ballistic analysis model was proposed to take account of the erosive burning with the variance of local velocity and pressure along the grain surface of a solid rocket combustor. To validate the model of concern in the study, both cases of non-erosive and erosive burning were compared with the previous researches with marginal accuracy. It was quantitatively investigated that the combustion pressure, grain length, initial temperature, and vaporization temperature of propellant affect the erosive burning characteristics.
Controlling the Horseshoe Vortex by Leading-Edge Chamfer at a Generic Wing-Body Junction
Cho, Jong-Jae ; Kim, Kui-Soon ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 2, 2009, Pages 26~34
Secondary flow losses can be as high as 30~50% of the total aerodynamic losses for a turbo-machinery blade or stator row. These are important part for improving a turbine efficiency. Therefore, many studies have been performed to decrease the secondary flow losses. The present study deals with the chamfered leading-edge at a generic wing-body junction to decrease the horseshoe vortex, one of factors to generate the secondary flow losses, and investigates the vortex generation and the characteristics of the horseshoe vortex with the chamfered height, and depth of the chamfer by using
. It was found that the total pressure loss for the best case can be decreased about 1.55% compare to the baseline case.
Computational Investigation of Pintle Nozzle Flow
Kim, Joung-Keun ; Lee, Ji-Hyung ; Chang, Hong-Been ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 2, 2009, Pages 35~41
Both the nozzle expansion ratio and the chamber pressure are simultaneously and continuously changed according to pintle movement, resulting in a different internal flow structure and flow separation characteristics. In this paper, the pintle position effect on nozzle flow structure and separation phenomena is analyzed by experimental-aided Computational Fluid Dynamic(CFD). Among the turbulent models for RANS(Reynold Averaged Navier Stokes) in Fluent, Spalart-Allmaras model is better agreement with the nozzle wall pressure distribution attained by cold-flow test than other models. And even if a conical nozzle is used, there is a shock structure similar to cap-shock pattern mainly occurred in contoured or shaped optimized nozzle because of internal shock generated from pintle tip flow separation.
Development of Gas Turbine Engine Simulation Program Based on CFD
Jin, Sang-Wook ; Kim, Kui-Soon ; Choi, Jeong-Yeol ; Ahn, Iee-Ki ; Yang, Soo-Seok ; Kim, Jae-Hwan ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 2, 2009, Pages 42~53
Gas turbine engine simulation program has been developed. In compressor and turbine, 2-D NS implicit code is used with k-
SST turbulent model. In combustor, 0-D lumped method chemical equilibrium code is adopted under the limitations, the products are only 10 species of molecular and air-fuel is perfectly mixed state with 100% combustion efficiency at constant pressure. Fluid properties are shared on interfaces between engine components. The outlet conditions of compressor have been used as the inlet condition of combustor. The inlet condition of turbine comes from the compressor The back pressure in compressor outlet is transferred by the inlet pressure of turbine. Unsteady phenomena at rotor-stator in compressor and turbine is covered by mixing-plane method. The state of engine can be determined only by given inlet condition of compressor, outlet condition of turbine, equivalence ratio and rotating speed.
Analysis on Turbulent Scalar Field in a Channel with Wall Injection using LES Technique
Na, Yang ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 2, 2009, Pages 54~63
Large eddy simulation was conducted for flow development in a chamber with wall injection which simulates the cold flow in an idealized hybrid rocket motor. It was found that a peculiar timescale, roughly corresponding to St~0.5, resides in the flowfield resulting from the interaction between the main oxidizer and wall injected flows. However, the fact that this time characteristics is absent in the temperature field in the vicinity of the wall indicates that even a small regression rate renders the passive scalar, such as temperature, dissimilar to the velocity field. This implies that a classical approach, which assumes that constant turbulent Prandtl number, should be replaced by a more sophisticated turbulence models to accurately predict the temperature field in the hybrid motor.
A Study on Flame Extinction and Edge Flame Oscillation in Counterflow Diffusion Flame
Park, Dae-Geun ; Yun, Jin-Han ; Park, Jeong ; Keel, Sang-In ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 2, 2009, Pages 64~76
Experimental and numerical studies are conducted on the characteristics of flame extinction and edge flame oscillation in counterflow diffusion flames. The characteristics of flame extinction and edge flame oscillation are well described varying burner diameter, separation distance between two burners, global strain rate, and velocity ratio. It is verified numerically and experimentally that radial conduction heat loss significantly contributes to flame extinction and edge flame oscillation at low strain rate flames in zero- and micro-gravity. It is also shown that for appropriately small burner diameters flame extinction modes are grouped into four and these are significantly attributed to excessive radial conduction heat loss. The edge flame oscillation can be characterized well by one curve with Strouhal number and Peclet number.