Go to the main menu
Skip to content
Go to bottom
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
A Study on Fuzzy Trend Monitoring Method for Fault Detection of Gas Turbine Engine
Kong, Chang-Duk ; Kho, Seong-Hee ; Ki, Ja-Young ; Oh, Sung-Hwan ; Kim, Ji-Hyun ; Ko, Han-Young ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 6, 2008, Pages 1~6
This work proposes a fuzzy trend monitoring method for the fault detection of a gas turbine engine through analyzing measured performance data trend. The proposed trend monitoring technique can diagnose the engine status by monitoring major engine measured parameters such as fuel flow rate, exhaust gas temperature, rotor rotational speed and vibration, and then analyzing their time deppendent changes. In order to perform this, firstly the measured engine performance data variation is formulated using Linear Regression, and then faults are isolated and identified using fuzzy logic.
A Study on Development of On-line Condition Monitoring Program of a Turboshaft Engine
Kong, Chang-Duk ; Kho, Seong-Hee ; Ki, Ja-Young ; Gu, Young-Joo ; Jun, Yong-Min ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 6, 2008, Pages 7~11
The helicopter flies at low level flight mode in its own operational range comparing to other aircraft categories. The low level flight means that the engine operates at variable atmospheric condition such as hot and cold temperature, snow, heavy rain, etc. Furthermore it may increase the entering possibility of engine foreign object damage particles like sand, dust, etc., i.e. this operating condition gives rise to damages of engine gas path components. An on-line condition monitoring program was developed by using SIMULINK, where measurement signals were simulated as an input module. The reliability and capability of the developed on-line condition monitoring were confirmed through application to a real helicopter engine health monitoring.
Study on Fundamental Technique for Numerical Analysis of Interior Ballistics
Sung, Hyung-Gun ; Park, Sol ; Hong, Gi-Cheol ; Roh, Tae-Seong ; Choi, Dong-Whan ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 6, 2008, Pages 12~20
The efficient plan and numerical methods for development of the interior ballistics code have been investigated. The schemes of the numerical code for the moving boundary with the projectile movement have been compared and verified through the free piston motion problem. The combustion of solid propellants and the pressure gradient in the chamber by the porosity effect have been predicted based on the numerical calculation of the initial combustion of the interior ballistics. Computerization techniques of the fundamental schemes and plans for development of the numerical analysis code for the interior ballistics have been obtained.
Effect of Flow Angles at Nozzle and Solidities on a Partial Admitted Small Axial-Type Turbine
Cho, Chong-Hyun ; Ahn, Kook-Young ; Cho, Soo-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 6, 2008, Pages 21~29
Performance characteristics on a partially admitted small axial-type turbine are experimentally studied with changing design parameters, such as exit flow angles at the nozzle and solidities at the rotor. The tested turbine consists of a single-stage and its mean radius is 35 mm. In this experiment, three different solidities and four different nozzle flow angles are applied to find the optimal design parameter. For a comparison of the turbine performance, the net specific output powers are evaluated. For a 3.4% partial admission rate, the best performance is obtained when the rotor solidity is at 2.18, which is increased to 74% compared to the solidity at full admission.
Internal Flow Stability for Tangential Entry Conditions in a Swirl Injector
Kim, Sung-Hyuk ; Khil, Tae-Ock ; Cho, Seong-Ho ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 6, 2008, Pages 30~37
Many theoretical and experimental studies have been conducted to investigate elements of swirl injector hydrodynamics, such as variations in liquid film thickness or air core diameter. From these studies, some theoretical relationships have been established through an approximate analytical solution of flow hydrodynamics in a swirl nozzle. However, experimental studies on elements such as the stability of internal flow have not produced conclusive results. In this study, the stability of the internal flow under tangential entry conditions was examined by visualizing the formation of the air core in the swirl chamber and measuring the liquid film thickness in the orifice.
An Experimental Study on the Trajectory Characteristics of Liquid Jet with Canted Injection Angles in Crossflow
Kim, Min-Ki ; Song, Jin-Kwan ; Hwang, Jeong-Jae ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 6, 2008, Pages 38~47
The liquid column and spray trajectory have been experimentally studied in liquid jets injected into subsonic crossflow. With water as fuel injection velocity, injection angle were varied to provide of jet operation conditions. The Pulsed Shadowgraph Photography and Planar Liquid Laser Induced Fluorescence technique was used to determine the injection characteristics in a subsonic crossflow of air. And the mainly objectives of this research was to get a empirical formula of liquid column and spray region trajectory with forward and reversed injection of air stream. As the result, This research has been shown that each trajectories were spatially dependent on air-stream velocity, fuel injection velocity, various injection angle, and normalized injector exit diameter. Furthermore, the empirical formula of liquid column trajectories has been some different of drag coefficient results between forward and reversed angled injection.
The Effect of Turbine Blade Pitch on the Gas Turbine Engine Performance
Kim, Jae-Min ; Kim, Kui-Soon ; Choi, Jeong-Yeol ; Jung, Yong-Wun ; Hwang, In-Hee ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 6, 2008, Pages 48~55
We have simulated the performance of a simple engine model with a gas turbine engine simulation program based on CFD. 2-dimensional Navier-Stokes code for the viscous flow was applied to simulate a compressor and a turbine, and the chemical equilibrium code with the lumped method was applied to simulate the combustor. Unsteady-flow phenomenon between rotor and stator of the compressor and the turbine was analyzed by steady mixing-plane method. In this way, the influence of the turbine blade pitch on the engine was investigated. It was shown that the compressor is operated at more higher pressure conditions as narrower the pitch distance of the turbine.
The Aeropropulsion Research and Development of the Korea Aerospace Research Institute
Lee, Yang-Ji ; Lee, Kyung-Jae ; Kang, Sang-Hun ; Kang, Young-Seok ; Kim, Hyung-Mo ; Park, Poo-Min ; Jeon, Yong-Min ; Yang, Soo-Seok ; Lee, Dae-Sung ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 6, 2008, Pages 56~65