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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
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Volume & Issues
Volume 8, Issue 4 - Dec 2004
Volume 8, Issue 3 - Sep 2004
Volume 8, Issue 2 - Jun 2004
Volume 8, Issue 1 - Mar 2004
Selecting the target year
Experimental Investigation of the LRE Thrust Chamber Regenerative Cooling(II)
Kim Jung-Hun ; Jeong Hae-Seung ; Park Hee-Ho ; Chung Yong-Gab ; Kim Sun-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 1~9
We conducted the firing test with the regenerative cooling LRE and calculated the heat flux from measured coolant temperature, that was compared with the heat flux predicted by previously developed numerical analysis method. The difference between the measured heat flux and the numerical calculation value was within nine percents. Therefore, developed numerical analysis method can be applied to the design/fabrication of a real LRE system. and, it was investigated that combustion pressure and mixture ratio have an Influence on the heat flux with a constant relation.
Experimental Study on the Suppression of low Frequency Unstable Burning Occurred in a Gas Generator Using Bundle Cylindrical Grain
Sung Hong-Gye ; Byun Jong-Ryul ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 10~16
Untypical unstable burning with very low frequency was observed at firing test of a gas generator using bundle cylindrical grain. The pressure unbalance between inside and outside of cylindrical grain brought such a low unstable burning. The grains were radially holed so that the high pressure gas inside of grain could quickly moved outward of gain, resulting dissipation of the pressure unbalance However too many holes were required to let the burning be stable for all operation regime from low to high temperature of grain and resultantly deteriorate the Progressive increase of gas amount produced by a gas generator. So another idea using grids located both sides of a bundle grain was applied to dissipate actively large vorticities enhanced by unbalance pressure distribution in a combustor. Finally stable burning with progressively increase of gas was established by application of 5
5 grid slightly away bundle grain to move bundle gain freely in case pressure unbalance were occurred inside of combustor.
A Study on Power loading Experiment & Performance Analysis for Dynamic Transient Effect of a Turbo-shaft Engine with Free Power Turbine
Kim Gyoung-du ; Yang Soo-seok ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 17~26
In this paper, power transmission systems converts the shaft power of a Turbo-shaft Engine with Free Power Turbine into the generator power and be composed of a method being supplied in the thrust motor driving a propellers. Being used this, Gas turbine engine works to flat rating about 110 kw (147 shp) that the thrust motor be extremely supplied from the engine of 317shp. In this test equipment, the engine is installed with the flywheel being able to the damping function when happen to the varying load between gas turbine engine output-shaft and generator. Then if the flywheel of inertial moment be not considered, the generator and motor not get the required power from the engine for raising the load. Also it is certified that the engine works the abnormal operation. Hence the flywheel of inertial moment is determined the required range to do the performance analysis with the dynamic transient from the given and tested engine data. This system is able to get the required power after a mounting test with the redesigned flywheel.
Studies on Characteristics of Pressure Regulation System for Simulating Turbo Pump Unit
Lee Joong-Youp ; Jung Tae-Kyu ; Chung Yong-Gahp ; Kim Young-Mog ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 27~36
This paper has been conducted to design for pressure regulation system. to simulate for performance of turbo pump unit using AMESim(Advanced Modeling Environment for Simulation of Engineering Systems). With optimized of system, pressure regulation system has been confirmed dynamic characteristics of transient and steady states range based on static modeling of open type turbo pump fed engine system. These results can be utilized to verify for performance test facility of propulsion control system for analysis on control valves, review of the fundamental principle on the control logic and certificating engine feeding system.
Characteristics for Sludge Removal Nozzle in Steam Generator
Lee Sam-Goo ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 37~43
Water-jet trajectory visualization and velocity deficits from a high pressurized steam-generator nozzles were experimentally observed. In order to find an optimal nozzle configuration. several parameters affecting plugging and erosion onto the steam generator tube were quantitatively analyzed. For the experiments, a high-pressurized pump (pressure in use: 200 kg/
, 15 HP, 11 kW, output flow Q : 301/min) was utilized. Visualization, velocity distribution, and spray growth rate with different nozzle configurations have been mainly focused using a 2-D PDPA system. The results indicated that trajectories along the centerline regardless of their configurations has its potential core region. However, the phenomena from the peripheral part need to be meticulously considered. Accordingly, it is evident that quantitative velocity deficits at the outer region are outstanding due to the aerodynamical drag and entrainment.
A Study on Component Map Generation of a Gas Turbine Engine Using Genetic Algorithms
Kong Chang-Duk ; Kho Seong-Hee ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 44~52
In this study, a component map generation method using experimental data and the genetic algorithms are newly proposed. In order to generate the performance map for components of this engine, after obtaining engine performance data through many experimental tests, and then the third order equations which have relationships the mass flow function the pressure ratio and the isentropic efficiency as to the engine rotational speed were derived by using the genetic algorithms. A steady-state performance analysis was performed with the generated maps of the compressor by the commercial gas turbine performance analysis program GASTURB. In comparison, it was found that the component maps can be generated from the experimental test data by using the genetic algorithms, and it was confirmed that the analysis results using the generated maps were very similar to those using the scaled maps from the GASTURB.
A Study on the Nozzle-Rotor Interactions of Partial Admission Supersonic Turbines
Seong Young-Sik ; Han Seong-Hoon ; Kim Kui-Soon ; Park Chang-Kyoo ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 53~60
In order to investigate the nozzle - rotor interactions and the effect of partial admission, the flows in supersonic turbine rotor cascades with a nozzle have been computed. Extensive computations of partial admission supersonic turbines provide the shock structures and flow patterns in the nozzle and rotor. The governing equations were discretized with Euler implicit method in time and 2nd-order upwind scheme of FVM in space. The
turbulence model was utilized to describe the turbulent flow field. It is clearly shown that the nozzle flow is highly affected by the shocks or expansion waves propagated from the rotor leading edge. And the rotor flow is also affected by the shocks or wakes originated from the nozzle.
Experimental Study on the Extinction Characteristics of the Solid Properllant
Hwang Yong Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 61~67
The extinction characteristics of the solid propellant were studied experimentally in this paper. These characteristics are required for designing TCO (thrust cut off) system of the solid rocket motor Parameters to characterize solid propellant extinction were defined by physical observation. A device was designed (or acquiring these parameters and the firing tests were implemented to get the preliminary data for the extinction characteristics of HTBP propellant.
Effect of Inflow Fluctuation of LOX Manifold of Liquid Rocket on the Flow
Lee Gunho ; Byun Yung-Hwan ; Na Yang ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 68~74
Effect of fluctuation imposed on the inflow to LOX manifold of liquid rocket has been analyzed numerically. Time-varying fluctuation was idealized by the sinusoidal signal and three different representative frequencies were considered. It was found that all the frequencies tested produced the consistent flow reactions in the manifold in that the place close to the region of infection showed oscillatory flow rate through injector orifices in phase with the inflow fluctuation whereas the other side exhibits characteristics which are out of phase.
Development of Liquid Propellant Rocket Engine for KSR-III
Choi Hwan-Seok ; Seol Woo-Seok ; Lee Soo-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 3, 2004, Pages 75~86
KSR-III is the first Korean sounding rocket propelled by a liquid propellant propulsion system and it has been developed over 5 years using purely domestic technologies. The propulsion system of KSR-III is a 13-ton class see-level thrust liquid rocket engine(LRE) which utilizes liquid oxygen and kerosene for its propellants and employed pressurized propellant feeding and ablative cooling system. The problem of combustion instabilities which has brought the most difficulty in the development was resolved by implementation of a baffle. Through the development of KSR-III LRE, meaningful achievements have been made in the core technologies of LRE such as design of injectors and combustion chambers and test, evaluation, and control of combustion instabilities. The acquired technologies will be applied to the development of higher performance LREs necessary for future space development programs such as Korean Small Launch Vehicles(KSLV) In this paper, the development of KRE-III LRE system is described including its design, analyses. performance tests and evaluation.