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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 11, Issue 6 - Dec 2007
Volume 11, Issue 5 - Oct 2007
Volume 11, Issue 4 - Aug 2007
Volume 11, Issue 3 - Jun 2007
Volume 11, Issue 2 - Apr 2007
Volume 11, Issue 1 - Feb 2007
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The Design and Hot-firing tests of a Water-cooled High Pressure Sub-scale Combustor
Lee, Kwang-Jin ; Kim, Jong-Gyu ; Lim, Byoung-Jik ; Ahn, Kyu-Bok ; Seo, Seong-Hyeon ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 1~6
A 3-tonf-class high pressure sub-scale combustor was designed and manufactured to study the performance improvement of combustor. The combustor consists of a combustion chamber with film cooling, thermal barrier coating and water cooling channels to prevent thermal demage of the hardware and an injector head with 37 coaxial swirl injectors. Hot-firing tests were carried out at the design point with varying flow rate for film cooling. The test result revealed that the increase of film cooling flow rate decreases the combustion performance, but in the cases of similar film cooling flow rates, the combustion performance is dependent on the mixture ratio of main injector excluding the film cooling flow rate.
Friction Welding Analysis of Welding Part Shape with Flow Gallery Considered Fluid Flow
Yeom, Sung-Ho ; Kim, Bum-Nyun ; Hong, Sung-In ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 7~12
Friction welding is a welding method to use frictional heat of a couple of materials. In this paper object is that design the welding part shape with the flow gallery part which there is no effect in flow. Decided the welding part design parameter and doing the friction welding analysis used the rigid-plastic FEM program DEFORM-2D. To do friction welding analysis must input necessary flow stress data, friction coefficient by temperature change, upset pressure and Revolution per minute etc. According to analysis result, it decided the optimal shape of welding part with no effect in flow.
Design Technique for Minimizing the Crosstalk Effect in Multiaxis Thrust Measurement Stand
Kim, Joung-Keun ; Yoon, Il-Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 13~19
This paper described design method to minimize the crosstalk effect of multiaxis thrust measurement stand which can measure the thrust vector control performance of Solid Rocket Motor. This paper presents a theoretical solution for predicting the magnitude of crosstalk and calculates design sensitivity. The results indicate that the most important parameter of crosstalk is the displacement of flexure-loadcell-flexure assembly. And shape, dimension and mechanical properties of flexure and loadcell can also influence the magnitude of crosstalk.
Investigation of Transient Performance of An Auxiliary Power Unit Microturbine Engine
Son, Ho-Jae ; Kim, Soo-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 20~28
The easiest way to see the phenomena of compressor surge is to show the static and dynamic operation characteristic on the map. Its operation zone will be restricted by the surge limit and, static and transient process must have some margin for it. Effect of rotor moment of inertia, air/gas volumes and heat transfer are factors to cause the transition from the static line. In case a large volume such as heat exchanger exists in the system it will exert a substantial influence to dynamic characteristics. In the present paper, influence of air volume bled from the compressor exit on transient process is investigated with an example of an auxiliary power unit micro-turbine engine. Turbine mass, pressure ratio, rotation speed, power and moment are calculated based on mass and work conservation. Result from the present study can give guidance to design the control system. A computer program is developed to calculate the dynamic process using the MathCAD commercial software.
A Study on fault Detection of Off-design Performance for Smart UAV Propulsion System
Kong, Chang-Duk ; Kho, Seong-Hee ; Ki, Ja-Young ; Lee, Chang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 29~34
In this study a model-based diagnostic method using the Neural Network was proposed for PW206C turbo shaft engine and performance model was developed by SIMULINK. Fault and test database to build the NN was obtained at various off-design operating range such as flight altitude, flight Mach number and gas generator rotational speed variation. According to the fault detection analysis results, it was confirmed that the proposed fault detection method could find well the fault of compressor, compressor turbine and power turbine at on-design point as well as off-design point conditions.
A Numerical Study on Acoustic Damping Induced by Gap between Baffled Injectors in a Model Rocket Combustor
Sohn, Chae-Hoon ; Lee, Jung-Yun ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 35~42
Acoustic damping induced by gap width between baffled injectors is investigated numerically, which are installed to suppress pressure oscillations in a model rocket combustor. The previous work reported that the baffled injectors show larger acoustic damping with the gap width between injectors. It is simulated numerically and its mechanism is examined. Damping factors are calculated as a function of gap width and it is found that the optimum gap is 0.1 mm or so. For understanding of the improved damping induced by the gap, dissipation rate of turbulent kinetic energy and vorticity are calculated as a function of the gap. Both parameters have their maximum values at the specific gap and especially, the dissipation rate has the same profile as that of damping factor. It verifies that the improved damping made by the gap is attributed to the increased acoustic-energy dissipation.
Operation and Maintenance Techniques for Liquid Rocket Combustor Ground Firing Test Facility
Kang, Dong-Hyuk ; Lim, Byoung-Jik ; Moon, Il-Yoon ; Seo, Seong-Hyeon ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 43~49
A ground firing test facility for Liquid Rocket Engine(LRE) combustor was built in Korea Aerospace Research Institute(KARI) in 2001 to support the development of the first Korean LRE for the KSR-III. About 170 tests were conducted up to date since its establishment and in the meantime a considerable improvements were made in the facility capability. This paper describes the outline, conducted tests and operation techniques which have been acquired through the operation of the test facility.
Effects of Fuel-Injection Pressure on the Spray Breakup Characteristics in Small LRE Injector
Jung, Hun ; Kim, Sung-Cho ; Park, Jeong ; Kim, Jeong-Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 50~57
Spray characteristics of an injector in a small liquid rocket engine (LRE) is characterized by Particle Image Velocimetry (PIV) and Dual-mode Phase Doppler Anemometry (DPDA). Instantaneous plane images captured by PIV are examined for the qualitative prediction of spray breakup with the setup of evaluation technique for effect of spray angles on injector performance. DPDA is also applied in order to quantify the average velocity, turbulent intensity, SMD, and number density of spray droplets along the spray stream distance leading to precise observation of spray atomization behavior. An objective of the study is the derivation of design parameters of new injectors and the establishment of performance criteria through the clear understanding of spray characteristics.
Impact Structural Behavior by Bird Strike on Engine Inlet Nacelle
Kong, Chang-Duk ; Lee, Seung-Hyeon ; Park, Hyun-Bum ; Yoon, Jae-Huy ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 58~64
It is well known that the aircraft engine inlet should be safely designed against the bird strike at the aircraft development stage. The aircraft accident is increasing for FOD(Foreign Object Damage), especially bird of runway circumference. The aircraft accident due to bird strike brings about economic loss which is connected with the life of passengers. In this study, MSC/DYTRAN has been utilized to analyze the aircraft engine inlet against the bird strike. In order to validate the proposed method for the bird strike analysis, this study was performed with comparison of precedence study results.
Survey on a Research for Fire Safety in Space with the Understanding of Combustion Characteristics in Microgravity based on NASA's Space Research Program
Sohn, Chae-Hoon ; Son, Young-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 11, issue 3, 2007, Pages 65~72
Fire is one of important checkpoints in crewed exploration systems, where men inhabit in space. In space, astronaut can't escape from fire out of a spacecraft and not expect any help of fire fighters, either. Accordingly, the best way to stand against fire is to prevent it. But, when fire occurs in space, flame behaviors are quite different from those observed on earth because of micro- or zero-gravity in space. The present paper introduces major research results on flame behaviors under microgravity and fire prevention, detection, and suppression in crewed exploration spacecrafts and international space station based on NASA's FPDS research program.