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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 14, Issue 6 - Dec 2010
Volume 14, Issue 5 - Oct 2010
Volume 14, Issue 4 - Aug 2010
Volume 14, Issue 3 - Jun 2010
Volume 14, Issue 2 - Apr 2010
Volume 14, Issue 1 - Feb 2010
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A Study on the Supersonic Flow Characteristics Through a Dual Throat Nozzle
Shin, Choon-Sik ; Kim, Heuy-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 1~7
Dual throat nozzle(DTN) is recently attracting much attention as a new concept of the thrust vectoring technique. This DTN is designed with two throats, an upstream minimum and a downstream minimum at the nozzle exit, with a cavity in between the upstream throat and exit. In the present study, a computational work has been carried out to analyze a fundamental performance of a dual throat nozzle(DTN) at various nozzle pressure ratios(NPR) and throat area ratios. Two-dimensional, axisymmetric, steady, compressible Navier-Stokes equations were solved using a fully implicit finite volume scheme. NPR was varied in the range of NPR from 2.0 to 10.0, at different throat area ratios. The present computational results were validated with some experimental data available. Based upon the present results, the performance of DTN is discussed in terms of the discharge coefficient and thrust efficiency.
Analysis of Pressure Fluctuations in a Thrust Chamber with Chamber Pressure Variation
Ahn, Kyu-Bok ; Lim, Byoung-Jik ; Kim, Jong-Gyu ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 8~14
For the development of a liquid rocket engine, hot-firing tests of a regeneratively cooled thrust chamber were performed at chamber pressures of approximately 30 and 60 bars. In the paper, pressure fluctuation data, which were obtained from the dynamic pressure transducers installed in propellant manifolds and combustion chamber, were analyzed. Compared to the data at chamber pressure of 60 bar, the results at chamber pressure of 30 bar showed low-frequency oscillations around 150 Hz in the combustion chamber. The low-frequency waves in the combustion chamber were coupled with those in the manifolds. However, the RMS values of the chamber pressure fluctuations at chamber pressure of 30 bar were only 0.8% of the chamber pressures. Thus, it can be inferred that the thrust chamber operates in the stability boundary even at low chamber pressure.
Forced Response Analyses of a Bladed Disk with Friction Dampers
Yoo, Jae-Han ; Lee, In ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 15~23
To reduce the vibration levels, additional dissipation elements such as dry friction dampers are sometimes integrated into bladed disk assembly. In this study, forced response analysis systems for a tuned bladed disk with friction dampers were developed and verified. For the efficient nonlinear vibration analysis, multi-harmonic balanced method and cyclic boundary condition were used. Also, mode shapes obtained using fictitious mass method were used to describe the motion of the structures with the concentrated structural nonlinearity, friction damper. The relative convergence of fictitious mass and traditional unconstrained modes were compared.
A Numerical Study on Combustion-Stability Rating of Impinging-Jet Injectors Using Hot-Fire Simulation
Choi, Hyo-Hyun ; Sohn, Chae-Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 24~31
Combustion-stability rating of impinging-jet injector is conducted numerically using hot-fire simulation in a subscale chamber with the five-element injector head. A sample F(fuel)-O(dxidizer)-O-F impinging-jet injector is adopted. In this work, instantaneous chemical reaction is adopted for hot-fire simulation based on the assumption that mixing process of fuel and oxidizer streams is controlling. The model chamber was designed based on the methodologies proposed in the previous work regarding geometrical dimensions and operating conditions. The present stability boundaries are in a good agreement with air-injection and hot-fire experimental data. The proposed numerical method can be applied cost-effectively to stability rating of jet injectors when mixing of fuel and oxidizer jets is the dominant process in instability triggering.
Thermal Decomposition and Ablation Analysis of Solid Rocket Propulsion
Kim, Yun-Chul ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 32~44
A two-dimensional thermal response and ablation analysis code for predicting charring material ablation and shape change on solid rocket nozzle is presented. The thermogravimetric analysis (TGA) techniques have been used to characterize the thermal decomposition constants for Arrhenius parameters. Two heterogeneous reactions involving carbon and the oxidizing species of
are considered and determined by Zvyagin's ablation model and kinetic constants. The moving boundary problem and mesh moving are solved by remeshing-rezoning method in MSC-Marc-ATAS program. The difference between the calculated and experimental value of char and ablation thickness is up to 20%. For the performance prediction of thermal protection systems, this method will be integrated with a three-dimensional finite-element thermal and structure analysis code through the real time sensing of in-depth temperature and heat flux.
Investigation of Characteristics for Cooling Parameters of a Combustor in Liquid Rocket Combustors
Kim, Hong-Jip ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 45~50
Thermal analyses have been performed to study the effect of location of fuel ring and thermal barrier coatings in regenerative cooling channels in a full-scale combustor. For the effective cooling, the fuel ring has better be installed near axial location of the low expansion ratio and low heat flux, and branching of cooling channels is preferable. Also, the radiative cooled nozzle extension is thought to be reasonable for the cooling of combustor walls. Among the possible coatings,
coating and Ni/Cr coating have been adopted. Compared with Ni/Cr coating which has high oxidation resistance,
coating, one of ceramic coatings is found to be much effective to sustain the thermal survivability of combustion walls.
A Study of Spray Characteristics of the Rotating Fuel Nozzle with Orifice Diameters
Lee, Mae-Hoon ; Jang, Seong-Ho ; Lee, Dong-Hun ; Choi, Seong-Man ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 51~56
An experimental study was performed to understand spray characteristics of the V type rotating fuel nozzle with orifice diameters by using high speed rotational system. The experimental apparatus consist of a high speed rotational system, fuel injection system and acrylic case. The droplet size and velocity were measured by PDPA(Phase Doppler Particle Analyzer) and spray was visualized by using Nd-Yag laser-based flash photography. From the test results, droplet size is reduced with increasing orifice diameter up to the critical value. When increasing orifice diameter over than this critical value, droplet size is not decreased with increasing the orifice diameter. This is due to the irregular distribution of the liquid sheet around the inner surface of injection orifice.
Inter Propellant Seal Performance test for 75 ton Class Turbopump
Jeon, Seong-Min ; Kwak, Hyun-Duck ; Park, Min-Joo ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 57~64
A performance test of inter propellant seal for a 75 ton class turbopump is conducted using water to evaluate leakage and endurance performance. Each part of fuel pump side and oxidizer pump side for a prototype inter propellant seal has been tested for verifying endurance performance during total accumulated test time 2,100 sec in water. The fuel pump side part with one-stage seal of carbon floating ring shows average leakage rate 13.7 gram/sec under average seal differential pressure 9.4 bar. On the other hand, the oxidizer pump side part with two-stage seal assembly of carbon floating rings shows average leakage rate 7.3 gram/sec under average seal differential pressure 9.5 bar. After the endurance performance test, the inter propellant seal shows good physical condition. A leakage performance test of the inter propellant seal for cryogenic environment will be performed using LN2 in the near future.
Investigation on the Performance Characteristics of the 75ton Class Turbopump Turbine
Jeong, Eun-Hwan ; Lee, Hang-Gee ; Park, Pyun-Goo ; Kwak, Hyun-D. ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 65~71
Performance test of the 75ton class turbopump turbine was performed. Using the measured turbine power characteristics in the wide-range operational conditions, variations of nozzle velocity ratio, total pressure loss, and relative flow angle to the pressure ratios and rotational speeds are quantified. Efficiency and nozzle exit pressure behavior was also investigated and compared with 30ton turbopump turbine data. A rotor blade was redesigned based on the test results and CFD analysis.
Experimental Study on Cellular Instabilities in Diluted Syngas-Air Premixed Flames
Vu, Tran Manh ; Song, Won-Sik ; Park, Jeong ; Kim, Jeong-Soo ; Yun, Jin-Han ; Keel, Sang-In ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 72~83
Experiments were conducted to investigate the effects of added diluents (carbon dioxide, nitrogen, and helium) on cellular instabilities in outwardly propagating spherical syngas-air premixed flames. Laminar burning velocities and Markstein lengths were measured by analyzing high-speed schlieren images at various diluent concentrations and equivalence ratios. Experimental results showed substantial reduction of the laminar burning velocities and of the Markstein lengths with the diluent additions in the fuel blends. Effective Lewis numbers of helium-diluted syngas-air flames increased but those of carbon dioxide- and nitrogen-diluted syngas-air flames decreased in increase of diluents in the reactant mixtures. With helium diluent, the propensity for cells formation was significantly diminished, whereas the cellular instabilities for carbon dioxide- and nitrogen-diluted syngas-air flames were not suppressed.
Preliminary Design of Test Facility for 75-tonf-Class Liquid Rocket Engine Combustor
Lim, Byoung-Jik ; Seo, Seong-Hyeon ; Kim, Mun-Ki ; Kang, Dong-Hyuk ; Han, Yeong-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 84~91
For the successful development of 75-tonf-class liquid rocket engine, a plenty of tests on each engine component have to be performed and this is equally true for a combustor. However the test facility which is in operation at Korea Aerospace Research Institute lacks its capacity to perform fire tests of a 75 tonf class combustor at its nominal thrust. Since the test facility has to be ready prior to the start of development tests, it is very urgent to establish the test facility. The preliminary design of a test facility for a 75 tonf class combustor which was performed according to such a necessity is described in the paper.
Combustion Stability Rating Test under Low Pressure Condition of a 75-tonf-class LRE Thrust Chamber
Lee, Kwang-Jin ; Kang, Dong-Hyuk ; Kim, Mun-Ki ; Ahn, Kyu-Bok ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 92~100
Combustion stability rating tests of 75-tonf-class thrust chamber for technology demonstration were carried out at a low pressure. Two kinds of mixing heads were used in this study. One of them has injectors of 631 and the other has injectors of 721. Mixing head with injectors of 631 showed a self-oscillation instability at the chamber pressure of 30 bar. Mixing head with injectors of 721 showed that a high frequency combustion stability was maintained under the same pressure and the same mass flow rate. But mixing head with injectors of 721 generated a self-oscillation instability at the chamber pressure of 20 bar and it was found that stability boundary region was changed due to the configuration of a mixing head from these results.
A Parametric Study on Double-Slit-Type Rupture Disc of Pulse Separation Device
Han, Houk-Seop ; Cho, Won-Man ; Lee, Won-Bok ; Koo, Song-Hoe ; Lee, Bang-Eop ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 5, 2010, Pages 101~110
Dual pulse rocket motor is a solid motor with two grains separated by a bulkhead and rupture disc. The elasto-plastic explicit dynamic analysis for the rupture disc was conducted by finite element method. The effect of the slit geometry of a rupture disc was parametrically analyzed in terms of rupture time and shape. The results can be used to control the rupture pressure by changing the slit geometry of rupture disc.