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 15, Issue 6 - Dec 2011
Volume 15, Issue 5 - Oct 2011
Volume 15, Issue 4 - Aug 2011
Volume 15, Issue 3 - Jun 2011
Volume 15, Issue 2 - Apr 2011
Volume 15, Issue 1 - Feb 2011
Selecting the target year
Improvement of the Aerothermal Environment for a 90° Turning Duct by the Nonaxisymmetric Endwall
Cho, Jong-Jae ; Kim, Kui-Soon ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 1~10
This paper presents the shape optimization of the endwall which improve the aerothermal environment of a gas turbine passage. A nonaxisymmetric endwall technique was adapted as the improving method. The turbine passage was simulated by a
turning duct (
=360,000). The main purpose of the present investigation was to focus on finding a nonaxisymmetric endwall with minimum total pressure loss in the passage and heat transfer coefficient on the endwall of the duct. An approximate optimization method was used for the investigation to secure the computational efficiency. Results indicated that a significant improvement in aerothermal environment can be achieved through the application of a nonaxisymmetric endwall.
A Study of Flame Visualization of the APU Gas Turbine Engine Sector Combustor
Kim, Bo-Ra-Mi ; Choi, Chea-Hong ; Choi, Seong-Man ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 11~17
In order to see flame behavior in the annular reverse gas turbine combustor, sector combustion test was performed. Ignition test by using torch ignition system was carried out at various combustor inlet velocity and air fuel ratio. Also, flame blow out limit was measured by changing fuel flow rate with constant air mass flow rate. In test results, stable ignition is possible at air excess ratio of 6 and this limit is gradually increased with combustor inlet velocity. The minimum blow out limit is about 4 at 40 m/s of combustor inlet velocity. This blow out limit is also increased up to about 10 with increasing combustor inlet velocity. Test result shows that lean blow out limits are increased with air velocity. The highest blow out limit was found at the combustor inlet velocity of 65 m/s.
Control of Pressure and Thrust for a Variable Thrust Solid Propulsion System Using Linearization
Kim, Young-Seok ; Cha, Ji-Hyeong ; Ko, Sang-Ho ; Kim, Dae-Seung ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 18~25
Solid propulsion systems have simple structures compared to other propulsion systems and are suitable for long-term storage. However the systems generally have limits on control of thrust levels. In this paper we suggest control algorithms for combustion chamber pressure of variable thrust solid propulsion systems using special nozzles such as pintle valve. For the pressure control within the chamber, we use a simple pressure change model by considering only mass conservation within the combustion chamber, design a classical algorithm and also a nonlinear controller using the feedback linearization technique. Also we derive the equation of the thrust for an under-expanded one-dimensional nozzle and then design a proportional-intergral controller after linearizing the thrust model for an operating point. Finally, we demonstrate the performance of the controller through a numerical simulation.
An Experimental Study on Flame Structure and Combustion Instability Characteristics in Model Gas Turbine Combustor
Park, Sung-Soon ; Kim, Min-Ki ; Yoon, Ji-Su ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 26~34
The present work addresses structural characteristics of natural gas flames in a lean premixed swirl-stabilized combustor with an attention focused on the effect of the formation of recirculation zones on the combustion instability. It is known that the recirculation zone plays an important role in stabilizing a turbulent, premixed natural gas flames by providing a source of heat or radicals to the incoming premixed fuel and air. To improve our understanding of the role of recirculation zones, the flame structure was investigated for various mixture velocities, equivalence ratios and swirl numbers. The optically accessible combustor allowed for the application of laser diagnostics, and Particle Image Velocimetry(PIV) measurements was used to characterize the flame structure under both cold flow conditions and hot flow conditions. Dynamic pressures were also measured to investigate characteristics of combustion at the same time. The results indicates that the formation of recirculation zone is strongly related to the occurrence of thermo-acoustic instabilities.
Effects of Changes in Equivalence Ratio and Modulation Condition on Flame Transfer Function
Kim, Dae-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 35~40
An experimental study of the flame response in a turbulent premixed combustor has been conducted in order to investigate mechanisms for combustion instabilities in a lean premixed gas turbine combustor. A lab-scale combustor and mixing section system were fabricated to measure the flame transfer function. Measurements are made of the velocity fluctuation in the nozzle using hot wire anemometry and of the heat release fluctuation in the combustor using chemiluminescence emission. The results show that the flame transfer functions are greatly dependent on the modulation frequency as well as operating conditions such as equivalence ratio. Flame dynamics can be generalized as a function of Strouhal number which is a ratio of flame length to modulation wave length.
Rotor Leading Edge Thickness Effect on Supersonic Impulse Turbine Performance
Lee, Hang-Gi ; Jung, Eun-Hwan ; Park, Pyun-Gu ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 41~47
Turbopump, which is a part of 75 ton open cycle liquid rocket engine has a super sonic impulse turbine. This paper investigated the leading edge thickness effect on the turbine performance experimently. Two rotors were tested with the different leading edge thickness. The ratios (rotor thickness to Pitch) are 1.9 and 1.4 times to 30 ton turbine rotor. As a result, a rotor with 1.4 times ratio had a 1.5% higher efficiency gain than a rotor with 1.9 times ratio. The pressure ratio with the maximum efficiency on the same rotational speed was increased to the full expansion ratio of nozzle.
An Analysis on Combustion Instability in Solid Rocket Motor of 4 Slotted Tube Grain
Cho, Ki-Hong ; Kim, Eui-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 48~56
A Possibility of combustion instability on longitudinal mode has a high level at large scale of L/D. Solid propellant has a metal particle and a grain of control to pressure oscillation. Solid rocket motor in slotted-tube grain controls pressure oscillation of longitudinal mode. Slotted-tube grain restrains longitudinal 1st pressure oscillation. But cavity volume of aft. insulation ablation amplifies 2nd pressure o scillation by vortext shedding. A study has suppressed combustion instability and vortex shedding by modified 4 slotted tube solid rocket motor design.
Numerical Analysis of a Highly Unstable Detonation Considering Viscosity and Turbulence Effects
Kang, Ki-Ha ; Shin, Jae-Ryul ; Cho, Deok-Rae ; Choi, Jeong-Yeol ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 57~64
It has been suggested that turbulent effect should be considered for the study of highly unstable detonation of hydrocarbon fuels, as in the case of pulse detonation engine (PDE). A series of numerical study are carried out to understand the characteristics of the highly unstable detonation by considering viscosity, turbulence model and turbulence-combustion interaction model. Through studies of the different levels of modeling, it is understood that the viscosity and turbulence have negligible effects on low frequency characteristics, but tend to enhance the high frequency characteristics. It is also considered that the turbulence-chemistry interaction model should be taken the influence of the activation energy into account for detonation studies.
Bubble-driven Convective Flow in the Liquid with Temperature Gradient
Bae, Dae-Seok ; Kim, Jeong-Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 65~72
Numerical simulation has been performed to investigate the bubbly flow in the liquid with vertical temperature gradient. The objective of this study is to establish an accurate numerical prediction program of gas-liquid two-phase flows in a vertical temperature gradient condition, whose mathematical model is formulated by the Eulerian-Lagrangian model. The present numerical results reveal the temperature mixing mechanism and the fluid dynamical characteristics induced by the bubbly flow in the liquid with stratified temperature. The effects of bubble radius, void fraction, and gas flow rate on bubble-driven convective flow are considered, too.
Evaluation of the Inherent Flow Coefficient of the Control Valve in the Liquid Propellant Rocket Engine
Park, Soon-Young ; Cho, Won-Kook ; Seol, Woo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 73~78
When a liquid rocket engine - specifically for the gas-generator cycle engine has throttle valves to control the thrust level and mixture ratio of the engine, it is possible to adjust the inherent flow characteristics of the control valves in order to secure a linearized correlation between the control-process-parameters like the thrust or mixture ratio of an engine and the throttle angle of valve. These linearities can reduce the complexity of the control process and make the process more explicit by ensuring the intuitive control. In this point, we proposed an algorithm within the frame of the in-house-developed program to obtain the control valves' inherent flow characteristics which satisfy the linearity, and calculated the sensitivities of control valves with respect to the throttle angle. Also, we compared the obtained inherent flow characteristics with the existed data and concluded the results are satisfactory.
Development of T700/701K Engine for KUH
Kim, Jae-Hwan ; Ahn, Iee-Ki ; Lee, Dae-Sung ; Sung, Ok-Suck ; Sung, In-Kyung ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 79~84
This paper presents development activities of the T700/701K turbo-shaft engine for Korean Utility Helicopter(KUH). The T700/701K is the first rear-drive variant of the GE's T700 engine which is proven for military applications in the world. The main workscope of the development includes a modification from a front-drive engine to a rear-drive one, an performance enhancement of the power turbine and an incorporation of two channel FADEC(Full Authority Digital Engine Control) system for more reliable operation. The first engine run for development and qualification test was successfully completed in 2008. Since the PFRT(Preliminary Flight Rating Test) has been completed, the first flight of the engine installed in the first prototype of KUH has been successfully demonstrated in March, 2010 and the engine installation compatibility tests are being carried out during KUH flight test. The test and evaluation for qualification has been done except for the low cycle fatigue test up to date.
Analytical Analysis of Segmented Arc Plasma Torch for Plasma Wind Tunnel Facility
Seo, Jun-Ho ; Choi, Soo-Seok ; Choi, Seong-Man ; Hong, Bong-Guen ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 85~93
A parametric study is conducted for the design of segmented arc plasma torch with the input power and current of 0.4 MW and 300 A, respectively. For this purpose, we use the analytical relationship between input power, current condition, plasma temperature, inner diameter (R) and length (L) of the torch constrictor based on arc channel model. The results reveal that arc plasma temperatures increase monotonically as ��L increases or R decreases for the ranges of R
7.5 mm and L
1.25 m. For larger valuse of ��R and L than 7.5 mm and 1.25 m, respectively, however, they show non-linear behavior corresponding to the variations of ��L, which stands for the generation of unstable arc plasma. From this parametric study, optimum ranges of R and L are suggested as 5.5 mm
7.5 mm and 0.25 m
0.5 m for 0.4 MW class segmented arc plasma torch, under which stable arc plasma can be achieved at the input currents of ~300 A.
Sub-System Requirements of a Pressure-fed Hot-firing Test Facility for the Performance Assessment of a LRE Thrust Chamber
Lee, Kwang-Jin ; Lim, Byoung-Jik ; Seo, Seong-Hyeon ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 4, 2011, Pages 94~102
Sub-system requirements of a pressure-fed hot-firing test facility for performance assessment of a Liquid Rocket Engine(LRE) thrust chamber using Liquid oxygen and kerosene were described. These requirements were based on the experience of construction and operation of the ground hot-firing test facility which was used for the development of the KSR-III and a 30 tonf-class LRE thrust chamber. So it is expected that this paper is used as a basic material and an itemized previous review statement for the design and construction of a large hot-firing test facility.