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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 2, Issue 3 - Dec 1998
Volume 2, Issue 2 - Aug 1998
Volume 2, Issue 1 - Apr 1998
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Numerical Study of Two-Dimensional Supersonic Ejector Flows
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 1~12
Industrial ejector system is a facility to transport, to compress or to pump out a low pressure secondary flow by using a high pressure primary flow. An advantage of the ejector system is in its geometrical simplicity, not having any moving part, compared with other fluid machinery. Most of the previous works have been performed experimentally and analytically. The obtained data. are too insufficient to improve our current understanding on the detailed flow field inside the ejector. In order to provide more comprehensive data on this ejector flow field, two-dimensional computations using Reynolds-averaged Navier-Stokes equations were performed for a very wide range of operating pressure ratio of the supersonic ejector with a secondary throat. The current results showed that the supersonic ejector system has an optimum pressure ratio for the secondary flow total pressure to be minimized. The numerical results clearly revealed the shock system, shock/boundary layer interaction, and secondary flow entrainment inside the supersonic ejector.
A Dynamic Simulation for Small Turboshaft Engine with Free Power Turbine Using The CMF Method
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 13~20
A steady-state and dynamic simulation program for a small multi-purpose turboshaft engine with the free power turbine was developed. In order to reduce developing cost, time and risk, a turbojet engine whose performance was well-known was used for the gas generator, and life time was improved by replacing turbine material and by using Larson-Miller curves. The component characteristic of the power turbine was derived from scaling the gas generator turbine. Equilibrium equations of mass flow rate and work were used for the steady-state performance analysis, and the Constant Flow Method(CMF) was used for the dynamic performance simulation. The step fuel scheduling was carried out for acceleration in the dynamic simulation. Through this simulation, it was found that the overshoot of the turbine inlet temperature exceeded over the compressor turbine limit temperature.
Stress Analysis of Pressurization Type Propellant Tank in the Satellite
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 21~30
Design parameters which used to analyze the stress distribution on the tank wall were defined to develop the propellant tank and obtain optimal values. 1/4 modeling of total tank was selected to calculate the stress distribution with respect to the variation of the support lug location and the tank wall thickness and 1/2 modeling was selected for the stress distributions with respect to the variation of fuel outlet location. Actually, 350psi was applied as static load and 12 gravity as a dynamic load during launching on the internal tank wall. The structural analysis was done with respect to attaching condition of the tank in the satellite. Also the effect of the variation of the propellant outlet location from
on the stress distribution was investigated. The equivalent stress distribution and optimal parameters induced from analysis results of the each condition will be used as the fundamental data to design the propellant tank.
Finite Element Analysis of Residual Stress after Quenching and Element Removal of A1 Ring Rolls
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 31~40
To predict residual stresses of aluminum ring rolls after quenching and element removal, 2-D and 3-D thermal elasto-plastic analyses were performed. Strains measured by three step sectioning method were directly compared to those analysed using ABAQUS's element removal. Numerical residual stresses after quenching had similar tendency to measured ones after 2 step aging, but the difference between numerical and measured ones was large. The difference is the reason why there are nonuniform residual stress distributions to ring height direction due to small height of ring, It is judged that the increase of ring height will improve the accuracy of measured ones and decrease the difference. By direct comparison between 3-D numerical strains to simulate three step sectioning method and measured ones, the accuracy of measurement and analysis can be improved. It is concluded that there can be predicted the deformation behavior on machining complex shaped large structures with residual stresses.
Two-Mode Nonlinear Combustion Instability Analysis
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 41~49
A nonlinear mathematical model of longitudinal combustion instability appropriate for ramjets and augmenters was developed based on modal analysis. The model was limited to a two-mode formulation. The associated differential equations were solved both analytically and numerically. The two-mode nonlinear model is capable of predicting the bootstrapping effect which characterizes nonlinear velocity-sensitive combustion response. Also, parametric studies were performed.
Water Vapor Transmission for T800/AD6005 Based Composite Motor Case
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 50~58
Water vapor transmission was tested in water bath controlled by
, 90%RH for T800/AD6005 based composite motor case which made by filament winding method. We detected internal relative humidity of composite motor case by inserting the humidity detector through the head of motor case for the study of humidity transmission through the wall of composite motor case. We found out that this composite material appears the water vapor flux of 2.88
sec and diffusivity of 7.98
, 90%RH water vapor condition.
A Linear Stability Analysis of Unsteady Combustion of Solid Propellants
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 59~66
The combustion instability analysis of solid propellants is generally done by the simplified governing equations for chemically inert condensed phase region with QSHOD assumption. Since the gas phase and surface reaction layer can be more rapidly relaxed to the external perturbations than the condensed phase, these regions are treated as quasi-steady manner in the analysis. In this paper, the classical ZN(Zeldovic-Novozhilov)approach was re-examined with the presence of radiation augmented burning enhancement in the combustion. Also, the surface reaction was assumed to partially absorb the incident radiant heat fluxes and pass the remaining to the chemically inert condensed phase. As a result of the analysis, the burning rate response function was obtained which consists of a pressure response function and a radiation response function. The response function was shown to be able to predict the results of T-burner tests.
A Study on the Thermal Stability of Unidirectionally Solidified Eutectic Composites of Ni-Base Superalloys
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 67~77
Homogeneous liquids of Ni-21.5Nb-2.5Al and Ni-23.3Nb eutectic superalloys were solidified into Ni/
) phase by directional solidification and the effect of interlamellar spacing on microsturctural stability at high temperatures, hardness variation with growth rate was studied. The interlamellar spacing(
) in the eutectics was varied with the growth rate(R), corresponding to "
R ＝Constant" relationship. Isothermal heat treatments of the eutectics used in this study, provided the microstructural stability improvement at hight temperature as the interlamellar spacing increases. It was also seen that the hardness improvement is made with the growth raterowth rate
New Treatment of High-Pressure Exhaust Gas Flows Using Shock-Wave Confinement
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 78~87
In many industrial practices it is an important problem to discharge a high-pressure exhaust gas to the atmosphere without generating a loud noise and much vibration. This may be achieved by confining a shock system inside the exhaust duct with a double orifice. The objective of the current work is to develop a new treatment method for the high-pressure exhaust gases. A theoretical analysis was applied to one-dimensional, steady. viscous, compressible model flowfield, and an experiment was performed using a shock tunnel facility. The results showed that the total pressure drop increases with a decrease of the opening area of the upstream orifice, and the shock confinement to the duct is possible by decreasing the opening area of the downstream orifice.
Propulsion Installation Design on Wing-Mounted-Nacelle Type
Journal of the Korean Society of Propulsion Engineers, volume 2, issue 1, 1998, Pages 88~94
Installation design methods and results of an aircraft engine on the wing-mounted-nacelle type aircraft has been presented in this paper. The design process starts from design requirements and constraints and covers some major aspects of the engine installation design such as wing-nacelle interference drag, roll clearance, ground clearance, nose gear collapse margin, rotor burst and fuel tank capacity. The method was applied to 100-seat class airplane(K100). Results of the design suggest optimum nacelle location and nacelle installation angle(toe-in, incidence, droop angle) which satisfies in stalled engine performance and size/location of wing dry day.