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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
The Measurement Technique of Burning Rate in Solid Proplellant at High Pressure
Yoo, Ji-Chqang ; Jung, Jung-Young ; Yim, Yoo-Jin ; Ko, Seung-Won ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 4, 2008, Pages 1~6
The burning characteristics of HTPB/AP solid propellants were measured by closed bomb of internal volume of 200 cc and 700 cc up to 30,000 psia. The burning rates of closed bomb method showed good agreement with those of strand burner method between 1,000 psia and 5,000 psia, and the sharp increment of pressure exponent(n) around 6,000 psia as a result of testing in accordance with loading densities. The burning rate measured in 200 cc and 700 cc of internal volume of closed bomb agreed well without the relation of internal volume size.
A Study on the Autofrettage Analysis in Single and Compound Cylinders
Shim, Woo-Sung ; Kim, Jae-Hoon ; Lee, Young-Shin ; Cha, Ki-Up ; Hong, Suk-Kyun ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 4, 2008, Pages 7~15
In manufacturing aircraft, safety and lightness of structure are important factors. Utilizing autofrettage technique, these benefits can be obtained. This technique is most frequently applied to a single cylinder. However, the Bauschinger effect reduces the benefits of autofrettage process Therefore, there is increasing interest in the use of compound cylinder that combine shrink fit and autofrettage. In this paper, single and compound cylinders that has same geometry were considered. It was found that compound cylinder which was autofrettaged has lower tangential hoop stress and plastic strain than single cylinder at bore. This means a reduction in the impact of the Bauschinger effect after shrink-fitting which produces the beneficial bore hoop stress.
Study on Starting Pressure of Supersonic Exhaust Diffusers to Simulate high Altitude Environment
Yoon, Sang-Kyu ; Yeom, Hyo-Won ; Kim, Jin-Kon ; Sung, Hong-Gye ; Kim, Yong-Wook ; Oh, Seung-Hyup ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 4, 2008, Pages 16~23
Theoretical and numerical approaches were conducted in order to study supersonic exhaust diffusers to simulate high altitude performance of rockets on the ground. A physical model of concern includes a rocket motor, vacuum chamber, and diffuser, which have axisymmetric configurations. An analysis was conducted to investigate operation characteristics of supersonic exhaust diffusers from a flow-development point of view. Emphasis was placed on theoretical formulation to predict the starting pressure of diffusers, the effect of the vacuum chamber size, and the minimum starting pressure of the rocket motor to start the diffuser.
Research on the formulation and Process of Base Bleed Unit for reducing of Curing Time
Choi, Young-Ki ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 4, 2008, Pages 24~32
We made a new propellant formulation to improve the productivity of Base Bleed Unit(aka BBU) by reducing of the curing time. We made an experiment with new propellant formulation such as binder characteristics and manufacturing process. In addition, we already tested several basic characteristics and the final performance of the new propellant. According to the test report, it was not only satisfied with all requirements in the specification, but it also contributed to improve productivity and reduced 53% of the curing time.
Thermal Analysis of Prelaunch Transients in Cryogenic Oxidizer Tank of Liquid Propulsion Rocket
Kim, Kyoung-Hoon ; Ko, Hyung-Jong ; Kim, Kyoung-Jin ; Cho, Kie-Joo ; Oh, Seung-Hyub ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 4, 2008, Pages 33~41
The prelaunch thermal transients in the cryogenic oxidizer tank of liquid propulsion rocket subjected to uniform heat flux from outside are numerically analyzed through thermodynamic equations and heat and mass transfer relations. The prelaunch stage is assumed to be composed of five idealized sub-stages including pressurization process by helium gas injection. The Peng-Robinson equation of state is utilized in the lumped analysis of ullage gas. The liquid region is divided into a number of horizontal layers of uniform properties to account for the thermal stratification. The computational result for the typical case shows that the temperature rise of liquid oxidizer is less than 1K and the adsorbed helium into the liquid is approximately 10g.
Operation limits analysis of PW206C turboshaft engine in manual mode
Lee, Chang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 4, 2008, Pages 42~47
The power control system of Smart UAV is similar to the propeller pitch governing concept of turboprop aircraft. The pilot adjusts the engine power directly and the pitch governor controls the propeller pitch to maintain the propeller rotational speed. The electronic engine controller(EEC) of PW206C engine developed for helicopter is not fit for the power control concept of Smart UAV, and therefore the manual back-up system of PW206C engine is used for the engine power control of Smart UAV. Engine performance estimation program is used to predict the control range of power lever angle(PLA) according to the variation of engine output shaft speed, flight altitude and flight speed. These data provide a guide for the PLA control in manual mode operation.
Effect of Leading Edge Shape on the Blade Surface Temperature of a Partial Admission Supersonic Turbine
Lee, Sang-Do ; Kim, Kui-Soon ; Lee, In-Chul ; Koo, Ja-Yae ; Mun, In-Sang ; Lee, Su-Young ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 4, 2008, Pages 48~55
In this paper, numerical analysis of the surface gas temperature on turbine blades has been performed to investigate the temperature profiles characteristics of a partial admission supersonic turbine driven by high temperature and pressure gas of pyro-starter with two different types of turbine blade edge shape. In order to examine the surface gas temperature on turbine blades at initial starting, computations tlave been carried out at several turbine rotational speeds in the range of
rpm for each type of turbine edge shape. "Sharp" edge and "Round" edge types were taken as the turbine edge shape factor. As turbine rotational speed increased, the average temperature of turbine blades was further decreased. It was also found that the surface temperature of turbine blades with a sharp edge was lower than round-type edge turbine blades.
Aerodynamic Design and Numerical Analysis on a Transonic Centrifugal Compressor
Choi, Jae-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 4, 2008, Pages 56~62
This study presents the aerodynamic design and numerical analysis results on a transonic centrifugal compressor which is used for gas turbine systems. Mean-line analysis and quasi-3D analysis are used for the aerodynamic design, and Reynolds-averaged Navier-Stokes analysis is applied to flow analysis of the compressor. The aerodynamic parameters for a transonic compressor, such as pressure coefficient, swirl parameter, blade loading, are discussed, and flow characteristics in the impeller and diffuser are discussed.
Combustion Instability in Gas Turbine Engines
Oh, Jeong-Seog ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 12, issue 4, 2008, Pages 63~77
This paper described the general concept of combustion instability and its mechanism in gas turbine engines. The approaching method to study this phenomenon was introduced including the up-to-date research activity in tile world. Combustion instability is one of critical problems, still now, affecting engine performance, durability and operation. In addition it is known that this problem is caused by coupling between fuel or air flow fluctuation and heat release rate in gas turbine engines, which is related with NOx reduction strategies. Therefore, in order to understand the current status of combustion instability we reviewed the combustion instability phenomenon in gas turbine engines.