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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 Numerical Study on Quarter-Wave Resonator Tuning for Suppression of Combustion Instability in a Model Combustion Chamber
Park, Ju-Hyun ; Park, I-Sun ; Sohn, Chae-Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 1~8
Acoustic tuning of quarter-wave resonator is investigated numerically to suppress combustion instability in liquid rocket engines. A model combustion chamber is adopted. First, basic acoustic characteristics are examined and acoustic damping is pursued by quarter-wave resonators. Next, for frequency tuning of the resonators, thermodynamic properties inside the acoustic resonators are estimated based on the numerical data. Maximum damping capacity is obtained when the resonators are designed to have the optimum length calculated with the properties. But, damping capacity induced by the resonators with the same length is comparable with it.
A Study on the Transitional Shock Separation Patterns in an Over-Expanded Nozzle
Lee, Jong-Sung ; Lijo, Vincent ; Kim, Heuy-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 9~15
Numerical investigation was carried out on axisymmetric over-expanded rocket nozzle to predict flow fields of transitional shock separation patterns. The unsteady, compressible N-S equations with k-
SST for turbulence model closure were solved using a fully implicit finite volume scheme. Computed results were in good agreement with previous experimental works. It was found that strong side-loads were generated during the transition of RSS to FSS due to the development of a vortex ring in the inviscid jet core region. Hysteresis phenomenon exhibited by the shock-separation patterns was also found during the start-up and shut-down processes.
Study on Inverse Modeling of a Turboprop in High Altitude Operation using Engine Performance Data
Kong, Chang-Duk ; Lim, Se-Myeong ; Kim, Ji-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 16~22
The gas turbine engine performance relies greatly on its component performance characteristics. Generally, engine manufacturers do not provide engine purchasers the component performance characteristics which can be obtained by lots of experimental tests at various operating conditions and big amount of expenses. In previous works the component maps have mostly been generated by scaling from a similar component map. However this scaling method has large error at off design points, specially in high altitude operation. Therefore this work proposes an inverse modeling method that can generate components maps of PT6A-67A turboprop engine using performance data provided by the engine manufacturer. In addition, evaluation can be made through comparison between performance analysis results using the performance simulation program including the generated compressor map and performance data.
Numerical Analysis of the Effect of Nozzle Shapes on the Performance of a Partial Admission Supersonic Turbine
Cho, Jong-Jae ; Kwon, Tae-Un ; Kim, Kui-Soon ; Jeong, Eun-Hwan ; Park, Pyun-Goo ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 23~29
A supersonic nozzle specially is one of the important part in a supersonic turbine usually adapted the impulse type, because the flow acceleration in the turbine theoretically is done only in the nozzle. The present study deals with numerical flow analysis to investigate the effect of nozzle shapes on the performance characteristics of a partial admission supersonic turbine. The flow analysis was performed for four different nozzle shapes. The shapes of the nozzles are circular, square, straight rectangular and bent rectangular nozzles. The results of the flow analysis showed that the aerodynamic loss of turbine is highly affected by the nozzle shapes, and the partial admission loss is also highly depended on nozzle shapes. Specially, bent rectangular nozzle had the best performance among the nozzle shapes
Experimental Study to Investigate the Flow Characteristics of a Supersonic Turbine Depending on the Relative Positions of Nozzle and Cascade
Cho, Jong-Jae ; Kim, Kui-Soon ; Jeong, Eun-Hwan ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 30~38
Experiments were performed to investigate the flow characteristics of a partial admission supersonic turbine depending on the relative positions of nozzle and cascade. The flow was visualized by a Schlieren system. The static pressures at the turbine cascade inlet, passage and outlet were measured by pressure transducers. Highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions of the supersonic turbine were observed by the experiments. And the flow characteristics in the supersonic turbine as the relative positions were observed.
A Comparative Study of Single Component Thermophysical Properties using the Real Gas Equation of State at Supercritical Conditions
Kim, Kuk-Jin ; Heo, Jun-Young ; Kim, Jong-Chan ; Koo, Ja-Ye ; Sung, Hong-Gye ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 39~51
Theoritical principles about the real gas equation of state are investigated and comparisons for the thermophysical properties of oxygen, hydrogen, and methane as the propellants of liquid rocket engine are carried out for the various conditions of pressure and temperature including supercritical conditions. The properties obtained using the real gas equation of state(Soave modification of Redlich-Kwong, Peng-Robinson equation of state, and extended corresponding states principle) have been compared with the results of applying the ideal gas equation of state. Differences of thermophysical properties among the models specifically at the liquid phase regime and their error ranges are addressed.
Combustion Stability Test of LRE Thrust Chamber using Artificial Perturbation Method
Lee, Kwang-Jin ; Seo, Seong-Hyeon ; Han, Yeoung-Min ; Choi, Hwan-Seok ; Ko, Young-Sung ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 52~60
Combustion stability tests of 30
-class LRE thrust chamber with double swirl coaxial injector were carried out in domestic ground combustion test facility by means of artificial perturbation method. In these tests, thrust chambers with varying design factors like recess number of injector, baffle length, types of film cooling and chamber diameter were used and test results showed that these design factors are closely related with high frequency combustion stability. By using the oscillation decrement instead of the decay time in the combustion stability analysis of artificially perturbed LRE thrust chamber, it was confirmed that increment of damping factor results in the improvement of high frequency combustion stability of LRE thrust chamber.
Construction of a High-Altitude Ignition Test Facility for a Small Gas-turbine Combustor
Kim, Tae-Woan ; Lee, Yang-Suk ; Kim, Ki-Woo ; Kim, Bo-Yean ; Ko, Young-Sung ; Kim, Sun-Jin ; Kim, Hyung-Mo ; Jung, Yong-Wun ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 61~68
A small high altitude test facility has been developed to investigate ignition performance of a small gas-turbine combustor under high altitude conditions. Supersonic diffusers and a heat exchanger were used to perform a low pressure and a low temperature condition, respectively. Experimental results showed that the low pressure environment could be controlled by upstream pressure of primary nozzle flow and low temperature environment by mixture ratio of cooled air and ambient air. Ignition performance tests were performed to verify the performance of the facility under simulated high altitude conditions. Conclusively, it was proven that the test facility could be used for ignition performance test of a small gas-turbine combustor under high altitude condition of approximately 6,100m.
Development of the Scramjet engine Test Facility(SeTF) in Korea Aerospace Research Institute
Lee, Yang-Ji ; Kang, Sang-Hun ; Oh, Joong-Hwan ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 69~78
Korea Aerospace Research Institute started on design and development of a hypersonic air-breathing engine test facility from 2000 and completed the test facility installation in July 2009. This facility, designated as Scramjet engine test facility(SeTF), is a blow-down type high enthalpy wind tunnel which has a pressurized air supply system, air heater system, free-jet test chamber, fuel supply system, facility control/measurement system and exhaust system. In this paper, details of the specifications, and configuration of the SeTF are described. For verifying characteristics of the SeTF, wind tunnel tests are now on progress and some of the data are also described.
Technical Survey on the Classification and Characteristics of UAV's Power Plant
Lee, Dong-Hun ; Paeng, Ki-Suk ; Kim, Yu-Il ; Park, Boo-Min ; Choi, Seong-Man ; Huh, Hwan-Il ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 3, 2010, Pages 79~86
The characteristics and classification of UAV power plants were studied. The energy source for electric generation and power source for internal combustion engine for UAVs were compared. The advantage and drawbacks of power plants were analyzed respectively and the performance demand condition was suggested for next generation UAV power plant finally.