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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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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 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
Selecting the target year
A Study of Inverse Modeling from Micro Gas Turbine Experimental Test Data
Kong, Chang-Duk ; Lim, Se-Myeong ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 6, 2009, Pages 1~7
The gas turbine engine performance is greatly relied on its component performance characteristics. Generally, acquisition of component maps is not easy for engine purchasers because it is an expensive intellectual property of gas turbine engine supplier. In the previous work, the maps were inversely generated from engine performance deck data, but this method is limited to obtain the realistic maps due to calculated performance deck data. Therefore this work proposes newly to generate more realistic compressor map from experimental performance test data. And then a realistic compressor map can be generated form those processed data using the proposed extended scaling method at each rotational speed. Evaluation can be made through comparison between performance analysis results using the performance simulation program including the generated compressor map and on-condition monitoring performance data.
Development of High Pressure Sub-scale Regeneratively Cooled Combustion Chambers
Kim, Jong-Gyu ; Lee, Kwang-Jin ; Seo, Seong-Hyeon ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 6, 2009, Pages 8~16
The development of high-pressure sub-scale combustion chambers is described. A total of four high-pressure sub-scale combustion chambers having either a detachable structure of the mixing head and the chamber or a single welded regenerative cooling structure have been developed. The sub-scale combustion chambers have a chamber pressure of 70 bar and propellant mass flow rate of 5.1~9.1 kg/s. The propellant mass flow rate and the recess number of the injector were changed for the improvement of combustion performance and they were validated through hot firing tests. The design and manufacturing techniques of regenerative cooling channel and film cooling to be applied to the full-scale combustion chamber were adopted through the present development and verified.
Thermo-Structural Survivability Evaluation of a Thrust-Measuring Nozzle Extension in a Full-scale Combustor
Kim, Hong-Jip ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 6, 2009, Pages 17~23
The survivability of the temporary nozzle extension for an accurate thrust measurement in a full-scaled combustor has been investigated through thermal analyses. The effects of nozzle extension materials and the thickness of thermal barrier coating (TBC) have been elucidated. It has been found that thermal survivability cannot be guaranteed without TBC. The maximum temperature of the nozzle extension decreased with increasing TBC thickness. For hot firing tests, the TBC is thought to be indispensable to the thermo-structural survivability of the nozzle extension made of steel.
Improvement of the Flow Characteristics by Optimizing the Leading-Edge Shape Around Airfoil/Flat-Plate Junction
Cho, Jong-Jae ; Kim, Kui-Soon ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 6, 2009, Pages 24~33
The present study deals with the optimization of the leading edge shape around a wing-body junction to minimize the strength of the horseshoe vortex, which is one of the main factor generating the secondary flow losses. For this purpose, approximate optimization method is used for the optimization. The study is performed by using
. The total pressure coefficient for the optimized model was decreased about 9.79% compared with the baseline model.
Study on Standards of Combustion Stability Assessment of Liquid Rocket Engine Combustion Devices
Seo, Seong-Hyeon ; Lee, Kwang-Jin ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 6, 2009, Pages 34~40
The present study describes the methods and standards for the combustion stability assessment of a thrust chamber and a gas generator as parts of a liquid rocket engine. The first method uses a statistical approach through typical static combustion tests and the second one a dynamic assessment identifying decaying characteristics of pressure fluctuations excited by a pulse generating device. Based on accumulated test results, it is concluded that the maximal values for combustion stability are 3% of a chamber static pressure with a Root-Mean-Square value of pressure fluctuations, and 10 msec with a decay time.
Spray Characteristics of the Simplex Atomizer with Working Fluids
Choi, Chea-Hong ; Lim, Byeong-Jun ; Choi, Seong-Man ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 6, 2009, Pages 41~47
This paper presents the spray characteristics of the simplex fuel nozzle with different working fluids for the gas turbine engine. Spray characteristics can be changed with viscosity, surface tension and density. In this research, water and test fluid type 2 which has similar characteristics of the kerosene are used as a working fluid. Spray visualization was performed by using ND-Yag laser and droplet size was measured by using PDPA(Phase doppler particle analyzer) system. The test results show that spray shapes and SMD distributions of two working fluids are similar at main spray region.
Study on Flow Property and Structural Analysis of Gas Generator Oxidizer On/Off Valve
Lee, Jongl-Yul ; Huh, Hwan-Il ; Ahn, Yang-Woo ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 6, 2009, Pages 48~55
The purpose of using Gas Generator Oxidizer On/Off Valve(GOV) is to control opening and closing of oxidizer mass flow. This paper describes analytical results of flow and structural properties for four different GOV models, using commercial software such as Fluent(Ver. 6.3.26) and NASTRAN(2005 r.2), PATRAN(2005 r.2). Analytical results show that GOVs could generate 2.3~3.8 kg/s of oxidizer mass flow rate and come up with 1.09~1.42 of safety factor.
Technical Survey on Propulsion Systems for Personal Air Vehicles
Yun, Dong-Ik ; Huh, Hwan-Il ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 6, 2009, Pages 56~63
In this paper, we present technical survey results on propulsion systems for Personal Air Vehicles (PAV). Reciprocating engines are suitable for current PAVs because of their superior efficiency and price advantages, except they produce noise problems. Turbo-Shaft engines are suitable for VTOL PAVs because of high specific power and wide operating range even though they are expensive. However, fuel cells and batteries may replace conventional engines in the near future.