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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 19, Issue 6 - Dec 2015
Volume 19, Issue 5 - Oct 2015
Volume 19, Issue 4 - Aug 2015
Volume 19, Issue 3 - Jun 2015
Volume 19, Issue 2 - Apr 2015
Volume 19, Issue 1 - Feb 2015
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Study on Variable Systems for Compressor and Turbine and its Control Scheme
Kim, Sangjo ; Kim, Donghyun ; Bae, Kyoungwook ; Kim, Dae-il ; Son, Changmin ; Kim, Kuisoon ; Lee, Daewoo ; Go, Jeungsang ; Choi, Dong-Whan ; Kim, Myungho ; Min, Seongki ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 1~14
DOI : 10.6108/KSPE.2015.19.5.001
In case of a gas turbine engine for supersonic operation, the engine have a wide range of operating inlet mass flow rate and required high performance such as thrust and fuel consumption. Therefore, variable system and its optimal control logic are essentially needed. In this work, a method for performance prediction of a gas turbine engine with variable system compressor and its control scheme were developed. Conceptual design of compact acuation system for the operation of the variable system was also conducted. The performance of a low-bypass ratio mixed flow turbofan engine was analyzed, and it was observed that the surge margin of the engine is improved at off-design condition by applying the control scheme.
Thermal Decomposition Kinetics of ZPP as a Primary Charge of Initiators
Kim, Junhyung ; Seo, Taeseok ; Ko, Seungwon ; Ryu, Byungtae ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 15~21
DOI : 10.6108/KSPE.2015.19.5.015
The thermal decomposition characteristics of the ZPP(Zirconium/Potassium perchlorate), widely used as a primary charge of initiators, were investigated by differential scanning calorimetry(DSC). The DSC results with different heating rates were elaborated with AKTS-Thermokinetics software for the determination of the kinetic parameters of the thermal decomposition of ZPP. There was good agreement between the experimental and the simulation curves, based on the determined kinetic parameters, which indicates the validity of the kinetic description of the thermal decomposition process of ZPP.
Hot Firing Tests of a Gas Generator for Liquid Rocket Engine using a Turbine Manifold Simulator
Lim, Byoungjik ; Kim, Munki ; Kim, Jonggyu ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 22~30
DOI : 10.6108/KSPE.2015.19.5.022
A gas generator which generates turbine driving gas by burning a part of propellants is used in an open cycle liquid rocket engine and as a main component of an open cycle liquid rocket engine autonomous hot firing tests are required to investigate the combustion performance and characteristics of the gas generator. However, since the combustion gas generated by a gas generator is choked at the turbine nozzle in the turbine manifold, it is necessary to consider the internal volume of turbine manifold as well as that of the gas generator for correct investigation of the combustion performance, characteristics, and acoustic characteristics of the gas generator. Therefore, in the paper hot firing test results of a gas generator with a turbine manifold simulator are described and characteristic prediction using the autonomous test of a gas generator is explained.
Numerical Study on the Characteristics of Dual-Mode Scramjet Isolator
Deng, Ruoyu ; Kim, Heuy Dong ; Jin, Yingzi ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 31~36
DOI : 10.6108/KSPE.2015.19.5.031
As one of the most promising propulsive systems in the future, the dual-mode scramjet engine has drawn the attention of many researches. Detailed flow features concerned with the isolator play an important role in the dual-mode scramjet system. The 2D numerical method has been used for the dual-mode scramjet with wind tunnel. To validate the ability of the numerical model, numerical results have been compared with the experimental results. Overall pressure distributions show quite good match with the experimental results. Back pressure has been studied for maximum pressure rising. According to the results, pressure distribution of supersonic inlet section is not influenced by back pressure. The shock train is pushed towards upstream as the back pressure increases. The maximum value of back pressure without inlet unstart goes up rapidly and then keeps constant when the isolator length increases. The optimal length of isolator section (
) is 8.7 in this model.
Effect of Particle Size Distribution on the Sensitivity of Combustion Instability for Solid Rocket Motors
Joo, Seongmin ; Kim, Junseong ; Moon, Heejang ; Ohm, Wonsuk ; Lee, Dohyung ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 37~45
DOI : 10.6108/KSPE.2015.19.5.037
Prediction of combustion instability within a solid-propellant rocket motor has been conducted with the classical acoustic analysis. The effect of particle size distribution on the instability has been analyzed by comparing the log-normal distribution to the fixed mono-sized particle followed by a survey of motor length scale effect between the baseline model and small scale model. Particle damping effect was more efficient for the small scale motor which has a relatively high unstable mode frequencies. It was also revealed that the prediction results by considering the particle size distribution show an overall attenuation of fluctuating pressure amplitude with respect to the mono-sized case.
Development of Multi-channel Simultaneous Laser Shock Sensing System for Linear Explosive-induced Pyroshock Propagation Prediction
Jang, Jae Kyeong ; Abbas, Haider ; Lee, Jung Ruyl ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 46~51
DOI : 10.6108/KSPE.2015.19.5.046
Multi-channel DAQ system was developed to predict propagation characteristic of the shock wave generated by linear explosive. The system can generate shock wave from 1000 points per second using a pulsed laser and simultaneously obtain the shock wave signals using 15 chanel contact sensor. The system is expected to pridict the propagation characteristics of various linear explosive-induced pyroshock because it can be used with a user-defined time delay that corresponds to detonation speed of the linear explosive.
A Numerical Study on Transient Performance Behavior of a Turbofan Engine with Variable Inlet Guide Vane and Bleed Air Schedules
Kim, Sangjo ; Son, Changmin ; Kim, Kuisoon ; Kim, Myungho ; Min, Seongki ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 52~61
DOI : 10.6108/KSPE.2015.19.5.052
This paper performed a numerical study to analyse the transient performance behavior of a turbofan engine with variable inlet guide vane (IGV) and bleed air schedules. The low bypass ratio mixed flow turbofan engine was considered in this study. For modeling the compressor performance with IGV, the performance maps were generated by using a one-dimensional meanline analysis and feed to the engine simulation program. The IGV and bleed air according to the rotating speed were scheduled to satisfy 10% of surge margin at steady-state condition. The transient engine performance analysis was conducted with the schedules. The engine with IGV schedule showed a higher surge margin and lower turbine inlet temperature than the engine with bleed air schedule during the transient period.
Simulator Development for Startup Analysis of Staged Combustion Cycle Engine Powerpack
Lee, Suji ; Moon, Insang ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 62~70
DOI : 10.6108/KSPE.2015.19.5.062
A liquid rocket engine system can cause rapid pressure and temperature variations during the startup period. Thus the startup analysis is required to reduce time and expense for successful development of liquid rocket engine through the startup prediction. In this study, a startup analysis simulator is developed for a staged combustion cycle engine powerpack. This simulator calculates propellant flow rates using pressure and flow rate balances. In addition, a rotational speed of turbopump is obtained as a function of time by mathematical modeling. A startup analysis result shows that the time to reach a steady-state and a rotational speed at the steady-state are 1.3 sec and 27,500 rpm, respectively. Moreover it can indicate proper startup sequences for stable operation.
Study of Multi Perforated Propellant Performance Analysis and Design using Configuration Variables
Oh, Seok-Hwan ; Jang, Jin-sung ; Park, Min-Su ; Roh, Tae-Seong ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 71~77
DOI : 10.6108/KSPE.2015.19.5.071
Internal ballistics is a phenomenon happened in tens of milliseconds during the gun firing. The configuration variables of the solid propellant are important factors which have influences on the performance of the gun system. In this study, the performance analysis of the 7-perforated propellant has been conducted using the numerical program for the interior ballistics. The effect of the configuration variables on the gun system performance has been analyzed. The propellant design has been conducted for the satisfaction of the performance requirements. As results, the relationship between the configuration variables and the performance has been obtained and the basic design concept of the multi-perforated propellant has been provided.
Burst Prediction of Hoop Winding Composite Case with Metal Liner
Han, Houkseop ; Kim, Hyung-kun ; Lee, Young-won ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 78~83
DOI : 10.6108/KSPE.2015.19.5.078
In the composite case, the first ply failure is considered total failure of the case. When the case is constructed by filament winding over a metal liner, the first ply failure does not necessarily mean total failure of the case. In this study, we compared the results through finite element analysis and burst test to predict the burst pressure of the hybrid case (filament-wound composite case with metal liner). Through it predicts the burst pressure of the hybrid case, we can determine the thickness of the metal liner and composite.
Dynamic Oxidation Behaviors of Aluminide Coated Titanium Alloys
Son, Youngil ; Park, Jinsoo ; Park, Joonsik ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 84~90
DOI : 10.6108/KSPE.2015.19.5.084
Titanium alloys has been received an attention due to their excellent specific strength and many other superior properties in the application of components of flying subjects. In this study, Ti-6Al-4V (Ti64 alloy) has been selected in order to evaluate oxidation and degradation behaviors under the exposure of high temperature flame. The alloy has been coated with Al diffusion coating routes. The coated alloys showed an improved oxidation and degradation behaviors. The oxidation and degradation mechanism for the coated and uncoated alloys has been discussed in terms of microstructural observations.
Certification Test Result of After-burner Test Facility for Gas-generator of 75 tonf Class Liquid Rocket Engine
Kim, Chae-Hyoung ; Lee, Kwang-Jin ; Han, Yeoungmin ; Chung, Yonggahp ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 91~97
DOI : 10.6108/KSPE.2015.19.5.091
After-burner test facility for gas generators of 75 tonf class liquid rocket engines was designed, which was verified by the facility certification test of the Combustion Chamber Test Facility(CCTF). The purpose of the certification test of the after-burner test facility is to verify the combustion stability of gas torches equipped in the gas generator and the after-burner test facility by using methane and oxygen gases. In the case of the autonomous test, the supply system provided steadily methane and oxygen gases to the after-burner system without pressure drop. The combustion pressure of the gas torch approached the design requirement. In the case of the coupled test, the gas generator ignition and the fuel-rich exhaust gas combustion were successfully carried out, leading to the verification of the test facility.
Dynamic Analysis of a Flow Passage Opening Device in Flight Profile of a High-speed Vehicle
Jung, Sungmin ; Park, Jeong-Bae ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 5, 2015, Pages 98~103
DOI : 10.6108/KSPE.2015.19.5.098
A flow passage opening device utilizing an acceleration follow-up technique allows fuel to flow continuously through a pressurized fuel tank system. It is very difficult to test the device in a real flight situation because of severe test condition and a cost problem. In this paper, therefore, the results of a basic negative g test conducted by low-speed airplane are compared with RecurDyn simulation. Dynamic behavior of the device in total flight profile of a high-speed vehicle is also analyzed by using RecurDyn to predict its performance.