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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
Editor in Chief :
Volume & Issues
Volume 12, Issue 6 - Dec 2008
Volume 12, Issue 5 - Oct 2008
Volume 12, Issue 4 - Aug 2008
Volume 12, Issue 3 - Jun 2008
Volume 12, Issue 2 - Apr 2008
Volume 12, Issue 1 - Feb 2008
Selecting the target year
Performance Test of the 30-ton Class Liquid Rocket Engine Turbopump Turbine
Jeong, Eun-Hwan ; Park, Pyun-Goo ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 1~6
Performance test of the 30-ton class liquid rocket engine turbopump turbine has been conducted using high pressure cold air. Overall performance of the two kinds of turbine rotors - rotor with knife-edged L.E blades and with rounded L.E blades - has been measured for various rotational speed and turbine pressure ratio. The effect of rotational speed and turbine pressure ratio on the turbine axial force behavior also has been measured in parallel. Test results have revealed that the efficiency of knife edged L.E. turbine is a little bit higher than that of rounded L.E. turbine. The axial force of the turbine varied linearly with respect to rotational speed and its magnitude largely depended on turbine pressure ratio.
Construction of the Pressure Sensitive Paint System
Jeon, Young-Jin ; Kim, Ki-Su ; Seo, Hyung-Seok ; Byun, Yung-Hwan ; Lee, Jae-Woo ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 7~15
Pressure Sensitive Paint(PSP) means a reacting paint in pressure. The calibration of PSP and the wind tunnel test of PSP painted model are required to measure pressure by using PSP. Therefore, the post processing from these results shows the information and image of the pressure distribution. PSP can show the information of total pressure from the wind tunnel test and the calibration. In this study, equipments of PSP are composed, and experiment is accomplished by using PSP. The surface pressure distribution around the wall of nozzle is measured by PSP. The measured pressure has similar results to those of the CFD and pressure tap measurement.
Effect of Gas-liquid Ratio on Characterization of Two-Phase Spray Injected into a Cross-flow
Cho, Woo-Jin ; Lee, In-Chul ; Lee, Bong-Su ; Koo, Ja-Ye ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 16~22
The effect of two-phase spray injected into subsonic cross-flow was studied experimentally. External-mixing of two-phase spray from orifice nozzle with L/d of 3 was tested with various air-liquid ratio that ranges from 0 to 59.4%. Trajectory of spray and breakup phenomena were investigated by shadowgraph photography. Detailed spray structure was characterized in terms of SMD, droplet velocity, and volume flux using PDPA. Experimental results indicate that penetration length was increased and collision point of liquid jets approached to nozzle exit and distributions of mist-like spray were obtained by increasing air-liquid ratio.
Compressibility correction of the Panel Method in Flow Analysis of a High Subsonic Turbine Cascade
Kim, Hark-Bong ; Kim, Jin-Kon ; Kwak, Jae-Su ; Kang, Jeong-Seek ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 23~28
Flow analysis in a turbine cascade by Euler or Navier-Stokes equation gives relatively accurate solution, however, those method require large computer memory or computing time. On contrast, the panel method, which is applied to incompressible and inviscid flow, provides fast and reasonal solution but the compressibility correction is required for a high air velocity case. In this paper, the compressibility corrected panel method was applied in order to find velocity distribution on turbine blades. Results showed that the calculated velocity in a turbine cascade by the compressibility corrected panel method gave good agreement with the solution by finite volume method for compressible flow.
Spray Characteristics of the Injector for the APU Gas Tubine Engine at Airplane Operating Conditions
Choi, Chea-Hong ; Choi, Seong-Man ; Lim, Byeong-Jun ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 29~36
Spray characteristics for APU gas turbine engine are investigated. In the test, four flight conditions such as sea level idle, sea level max power, 20,000 feet idle, 20,000 feet max power are used as spray experimental conditions. Spray visualization was performed by using ND-YAG laser bean PDPA(Phase Doppler Particle Analyzer) was used for measuring the particle diameter and velocity from 20 mm to 100 mm from discharge orifice. From the test result, SMD is
맛 20,000 ft idle condition and SMD is
at sea level idle condition. Also SMD is
at 20,000 ft max power condition and SMD is
at sea level max power condition. In the case of 20,000 ft idle condition, combustion instability could be occurred due to the higher drop diameter. Therefore it is necessary to decrease the droplet diameter in the high altitude condition.
High Altitude Simulation Test Facility for the KSLV-I Kick Motor Development
Kim, Yong-Wook ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 37~43
In order to verify the performance of upper stage propulsion system designed to operate in the upper atmosphere, test facility which can simulate high altitude is needed. Cylindrical supersonic exhaust diffuser, which utilizes the momentum of exhaust gas, provides a simple means for providing a low pressure around the propulsion system. This paper describes sub-systems and specification of high altitude test facility developed for the test of KSLV-I kick motor. Performance of the facility has been successfully verified through five times of hot firing tests.
A Study on Performance Analysis of a Helicopter Propulsion System Using SIMULINK
Kong, Chang-Duk ; Ki, Ja-Young ; Kho, Seong-Hee ; Kim, Jae-Hwan ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 44~50
In this study a turboshaft engine for a helicopter propulsion system was modeled using SIMULINK and the components' maps were generated from the limited performance deck data provided by engine supplier using a hybrid method with the genetic algorithms and the system identification method. In order to verify the SIMULINK performance model and the component maps generated by the hybrid method, the steady-state performance analysis results were compared with the performance data provided by engine manufacturer. In this investigation, it was confirmed that the analysis results by the proposed model are closely met with those by engine manufacturer's data.
A Study on Installed Performance Analysis Modelling for a Helicopter Propulsion System Considering Intake Loss
Kong, Chang-Duk ; Kho, Seong-Hee ; Ki, Ja-Young ; Jun, Yong-Min ; Ahn, Lee-Ki ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 51~56
In this work the realistic install performance analysis of a helicopter was performed together with power extraction enabling to operate auxiliary system as well as intake pressure loss, loss due to bleed air, etc. which must be considered in practical propulsion system's performance modelling to be installed to the airframe. The pressure loss occurring in intake was estimated from the intake performance map with relationships of Mach Number and pressure loss. In order to evaluate the proposed installed performance model, the experimental data for comparison must be needed when mounted in propulsion system. However because of lack of accessibility to such real data at the moment, the alternative way was made through comparison that the analysis results by the proposed model were compared with a wellknown commercial program GASTURB's analysis results. The validity of the proposed installed performance model was consequently confirmed because its average deferences from the GASTURB's results were within 0.5%.
Mixing Characteristics of Various Cavity Shapes in SCRamjet Engine
Oh, Ju-Young ; Seo, Hyung-Seok ; Byun, Yung-Hwan ; Lee, Jae-Woo ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 57~63
In combustor of SCRamjet of air-breathing engine type, the flow duration time is very short because of the supersonic air flow. In this short duration, the whole process of combustion should be done, so it is very important to study supersonic combustion technologies. In this study, we focus fuel-air mixing enhancement method using cavity and conducted 3-dimensional Navier-Stokes computational analysis. Cavity height is fixed by 10mm, length is changed from 0 to 40mm. There is a supersonic jet injection downstream of the cavity and the hole size is 1mm. As a result, the higher ratio of cavity length/height is, the higher value of vorticity gets. The increased area of vorticity expands to upper and sidewise combustor. However, the stagnation pressure loss which generates thrust loss becomes higher when the vorticity is higher. Considering these result, we can conclude that optimized design which considers the highest mixing performance and the least stagnation pressure loss is needed.
MEMS Power Device
Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 1, 2008, Pages 64~70
Thanks to the breakthroughs in micro fabrication technology, numerous concepts of micro aerospace systems including micro aerial vehicle, nano satellite and micro robot have been proposed. In order to activate these mobile micro systems, high density power in a small scale power source is required. However, we still do not have micro power source that has energy density that can support these systems. In the present article, status of micro power sources are described and alternatives that have been derived from the past experience are proposed.