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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
Effects of Axial Flow Compressor Surge on the Performance of Turbofan Engine
Oh, Chang-Yong ; Koo, Ja-Ye ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 3, 2009, Pages 1~8
This thesis has analyzed the effect of the surge happening in flight on the engine performance, especially on the PW4000 turbofan engine. It is to be judged that the flight surge can occur more often at the time of takeoff than it does en route due to the fact that the engine parameters are prone to fluctuate. EPR is judged to be the most highly sensitive parameter responding when surge occurs. Both Engine rpm and Wf decrease almost simultaneously just like an EPR. During the take-off rolling, N1 vibration is more sensitive than the N2 vibration. Consequently, the surge can be detected by EGT increase, while the other parameters (EPR, rpm, Wf, etc) decrease.
The Study on the Development of Thrust Measurement System and Reliability Appraisal Technique for Low-Thrust Liquid Rocket Engine
Lee, Dong-Hyeong ; Lee, Yang-Suk ; Ko, Young-Sung ; Kim, Yoo ; Kim, Sun-Jin ; Moon, Il-Yoon ; Lee, Hyung-Sool ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 3, 2009, Pages 9~19
Accurate thrust measurement is very important when developing an engine of propulsion system. Especially for a low thrust liquid rocket engine(LRE), accuracy of thrust is seriously affected by thrust measurement errors and thurst losses which are caused by propellant supply system. In this study, a new thrust measurement system is developed for accurate thrust measurement of a low thurst LRE by minimizing these effects. Its thrust measurement range is 150~1500N and the maximum error is below 10N. Also, a reliability appraisal technique is investigated to improve reliability and accuracy of the thrust measurement system.
Real-Propellant Test of a Turbopump for a 30-Ton Thrust Level of Liquid Rocket Engine
Hong, Soon-Sam ; Kim, Dae-Jin ; Kim, Jin-Sun ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 3, 2009, Pages 20~26
Turbopump test for a 30-ton-thrust liquid rocket engine was carried out using real-propellant. Liquid oxygen, kerosene, cold hydrogen gas were used for the oxidizer pump, the fuel pump, and the turbine, respectively. The turbopump was reliably operated at the design and off-design conditions and the performance requirements were satisfied, which implies that the turbopump development at the engine subsystem level is successfully accomplished in the point of performance validation. This paper presents the results of a test where the turbopump was run for 75 seconds at three operating modes. In terms of performance characteristics of pumps and turbine, the results of turbopump assembly test using real-propellant showed a good agreement with those of the turbopump component tests using simulant working fluid.
Passive Control of the Supersonic Cavity Pressure Oscillations Using Porous Vertical Barrier
Kang, Min-Sung ; Kwon, Joon-Kyeong ; Kim, Heuy-Dong ; Setoguchi, Toshiaki ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 3, 2009, Pages 27~33
A computational study has been performed out to evaluate the effect of a vertical porous barrier on the pressure oscillations in a supersonic cavity. The porous barriers with different perforations were vertically installed into a rectangular cavity at Mach numbers 1.50, 1.83 and 2.50. TVD finite difference MUSCL scheme was employed to solve the two-dimensional, unsteady, compressible Navier-Stokes equations. The present vertical porous barrier considerably altered the characteristics of the time-dependent shear layers that occur at the upstream edge of cavity and remarkably reduced the pressure oscillations inside the supersonic cavity. The present results showed that the effectiveness of passive control using the present porous vertical barrier is dependent on Mach number and the perforation of the porous barrier.
Research on the Dispersion Stability and Scale up of Carbon Slurry Fuel
Cho, Min-Ho ; Yang, Mun-Kyu ; Lee, Ik-Mo ; Cho, Joon-Hyun ; Kwon, Tae-Soo ; Jeong, Byung-Hun ; Han, Jeong-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 3, 2009, Pages 34~40
For the preparation of carbon-slurry fuel, the effects of process parameters on the carbon dispersion stability in the liquid fuel have been investigated. The dispersion stability of carbon-slurry fuels could be monitored by measurements of particle size and carbon contents in the different positions, and observation of dispersion states after centrifuging. Through the application of various additives, it was found that NB463S84 based on polyolefin succinimde showed the best dispersion and longest stability life of carbon-slurry fuel. Also, PIBSI (polyisobutenyl succimide) with the similar functional groups to NB463S84 was effectively synthesized and same dispersion stability was verified by application to carbon-slurry fuel. Finally, the possibility of practical use of carbon-slurry fuels was confirmed by application of the mixing conditions obtained from g scale to kg scale preparation.
Analysis of Rocket Booster Separation from Air-Breathing Engine with Kane's Method
Choi, Jong-Ho ; Lim, Jin-Shik ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 3, 2009, Pages 41~49
The present paper describes a mathematical modeling and simulation of the separation of a solid rocket booster from an air breathing engine vehicle. The vehicle and booster are considered as a multi-connected body and the booster is assumed to move only along the axial direction of the vehicle. The dynamic motion of the vehicle and the booster were modeled by using Kane's method. The aerodynamic forces on the whole system along various positions of booster were calculated by using DATCOM software and the internal pressure force acting on the effective surface during separation was simply calculated with gas dynamics and Taylor MacColl equation. Numerical simulation was done by using Mathworks-Matlab. From the result, the variation of Mach number and angle of attack are not large during the separation, so the variation of pitch angle and the characteristics of inlet flow for varying the Mach number and angle of attack during the separation test can be identified as neglectable values.
A Development of A Gas Mechanical Pulsator
Kim, Tae-Woan ; Hwang, Oh-Sik ; Ko, Young-Sung ; Jung, Se-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 3, 2009, Pages 50~57
A gas mechanical pulsator is developed for the study of combustion instabilities in various combustors such as LRE combustor. First, it shows that the mass flow rates and the perturbation frequencies can be successively controlled by the inlet pressure and the rotating speed of a rotating disk with many holes. Second, the device is used as an acoustic amplification source as a substitute for the speaker in the previous acoustic tests and its results show almost the same resonant frequency and damping characteristics compared with the previous results. In conclusion, the result shows that it can be used as a substitute for a speaker in the studies of LRE combustion instabilities, which has a flow and no limitation of amplification, and a device for making a perturbation source in gas flow.
The Outlook of Future Aeropropulsion System
Lee, Chang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 3, 2009, Pages 58~63
The global restriction on pollutant emissions and the soaring of crude oil price are expected to result in the change of future transportation system. Hydrogen is considered to be the leading candidate as an alternative energy source before other new alternative energy sources emerge. Scientists anticipate that hydrogen fuel gas turbine engine and fuel cell will be the power plant of the aircraft in the near future. To realize the aircraft powered by fuel cell system in the future, the technologies such as fuel cell with higher energy density, compressed gas or liquid storage system of hydrogen fuel, and efficient and lightweight electric motor have to be developed first.