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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 8, Issue 4 - Dec 2004
Volume 8, Issue 3 - Sep 2004
Volume 8, Issue 2 - Jun 2004
Volume 8, Issue 1 - Mar 2004
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Modeling of Injector Orifice for the Flow Analysis in LOX Manifold of Liquid Rocket
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 1~9
The flow in the LOX manifold of liquid rocket (KSR-III) has been analyzed using a CAE technique with an objective of modeling injector orifices in order to reduce the computational cost for the flow analysis without much losing the accuracy of capturing the flow physics. The numerical result shows that the flow just above the injector orifices is not uniformly distributed in terms of pressure and mass flow rate in case pre-distributors are not equipped inside the manifold. This non-uniformity of mass flux is attributed to the presence of large-scale flow patterns. Several boundary conditions which were designed to effectively replace the presence of injector orifices have been tested and it was found that a simple modeling can be possible by mimicking the actual shape of the orifices.
Combustion Performance Tests of Fuel-Rich Gas Generator for Liquid Rocket Engine Using an Impinging Injector
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 10~17
The results of the combustion performance tests of gas generator which supplies hot gas into the turbine of turbo-pump for liquid rocket engine and uses LOx and kerosene as propellant are described. The gas generator consists of a injector head with F-O-F impinging injector, a water cooled combustion chamber, a gas torch igniter, a turbulence ring and an instrument ring. The effect of turbulence ring and combustion chamber length on performance of gas generator are investigated. The ignition and combustion at design point are stable and the pressure and gas temperature at gas generator exit meets the target. The turbulence ring installed at middle of chamber effectively mixes hot gas with cold gas and the effect of residence time of hot gas in gas generator on combustion efficiency is small. Test results show that the main parameter controlling the gas temperature at gas generator exit is overall O/F ratio.
Fuel Spiking Test for the Surge Margin Measurement in a Gas Turbine Engine
Lee, Jin-Kun ; Lee, Kyung-Jae ; Ha, Man-Ho ; Kim, Chun-Taek ; Yang, Soo-Seok ; Lee, Dae-Sung ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 18~24
A fuel spiking test was performed to measure the surge margin of the compressor in a gas turbine engine. During the test, fuel spiking signal is superposed on the engine controller demand signals and the combined signals are used to control a fuel control valve. For the superposition, a subsystem composed of a fuel controller and a function generator is used. The real engine test was performed at the Altitude Engine Test Facility (AETF) in Korea Aerospace Research Institute (KARI). In the preliminary test, the fuel spiking signals are in good agreement with the dynamic pressure at the fuel line and at the compressor discharge point. After the preliminary test, a fuel spiking test to measure the surge point at a specific engine speed was performed. The test results show that the fuel spiking test is very effective in the measurement of surge.
Vibration Control of Flexible Structures by using Conveying Fluid Pipe
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 25~31
This paper describes a new vibration-suppression technique for flexible cantilevered structures by using a pipe containing an internal flow. The stability and dynamic response are analyzed based on the finite element method. The flutter limit and optimum stabilizing fluid velocity are determined in root locus diagrams. The impulse responses of the system are studied by the mode superposition method to observe the damping rate of the motion. The stabilizing effect of an internal flow is demonstrated by impulse responses of the structures with and without an material damping. It is found that the response of the pipe with flow of liquid has a larger effect of, stabilizing than that with flow of gas.
Thrust Performance of 1-lbf Class of Liquid-Monopropellant Rocket Engine
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 32~38
A comprehensive understanding is given for the hot-firing test results, which were obtained throughout the verification program of mono-propellant hydrazine rocket engines (thrusters) producing 0.95 lbf (4.2 N) of nominal steady-state thrust at an inlet pressure of 350 psia (2.41 Mpa). A scrutiny for the engine performance is made in terms of thrust and temperature behavior of steady state firing mode at the given propellant injection pressures: Pinj = 400, 250, 100, and 50 psi. The thrust and specific impulse are compared with a reference performance of 1-lbf standard rocket engines and their normalization procedure is introduced. A practical engineering approach to the data measurement and reduction is addressed, too.
Feature of Spray Transport and Atomization from Two-Phase Swirling Jet with Air-to-Liquid Mass Ratio
Lee, Sam-Goo ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 39~45
Experiments were performed in a two-phase swirling spray facility that has been described elsewhere. Measurements of spray transport and drop size distribution are analyzed over wide ranges of air to liquid mass flow ratios, utilizing four different internal mixing pneumatic nozzles. The spatial distributions of mean velocities. fluctuating velocities, and velocity-diameter correlation were quantitatively analyzed. Also, the exponential correlation curves were obtained with ALR along the spray centerline, which indicated an approximately identical formulation regardless of ALR. It indicated that the atomization characteristics were remarkably superior in the case of 30o of swirl angle with higher ALR. Among other things. nozzle configuration is one of the significant parameters affecting spray phenomena from an internal mixing nozzle. Turbulence intensities are increasingly degenerated with an increase of nozzle configuration, allowing a rapid increment of drop size distribution.
Development of Ultrasonic Testing Method for Evaluation of Adhesive Layer of Blaster Tube
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 46~53
Ultrasonic testing method has been developed to evaluate flaw of adhesive layers in blast tube for the reliability of the rocket nozzle. The ultrasonic reflection from the interface between the steel sheet and the epoxy adhesive is measured with a high-frequency Pulse-echo setup in order to identify contact debonding and missing adhesive in epoxy layer between steel and FRP layers. The steel sheet is resonated by low-frequency ultrasound, and the gap size underneath the measuring location is estimated from the resonance responses. For practical application in industry an automated testing system has been developed where the proposed approach is implemented. The performance of the proposed approach has been verified by actual measurement of gap sizes from the cross-sections of cut specimens using an optical microscope.
Preliminary Study of Micro Cold Gas Thruster
Seonghwan Moon ; Hwayoung Oh ; Hwanil Huh ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 54~61
Miniaturization of subsystems including propulsion systems is recent trends in spacecraft technology. Small space vehicle propulsion is not only a technological challenge of a scaling system down, but also a combination of fundamental flow/combustion constraints. In this paper, physical constraints of micronozzle for cold gas micro-thruster are reviewed and discussed. Method to measure small thrust are also described.
Numerical Analysis of Flow Characteristics within Blades for Design Parameters of Impulse Supersonic Turbine Blade
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 62~72
In this paper. firstly, numerical results were compared with experimental results to verify accuracy of the results. It is found that the numerical results show good agreements with experimental result. Next, computations about flow within blades for design parameters such as radius of the pressure and suction side's curvature and pitch-chord ratio have been performed. It is found that the flow and performance characteristics mainly depend on shocks occurred at the leading edge of blades and the end of nozzle and separations occurred inside the flow passage. And shock of nozzle and separations depend upon area of flow passage and shocks of blade are affected by the number of blades occupied by a nozzle.
A Theoretical Study on the Estimation of Distorted Thrust of Solid Rocket Motor
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 73~84
In general, static firing test is conducted before flight in order to obtain data such as thrust. pressure, temperature and strain, which show the characteristics of rocket motors. But the measured thrust of the obtained data is especially distorted by the effects of dynamic characteristics of thrust stand so that it is difficult for us to determine the exact value of peak thrust and rising time etc., which represent the performance of rocket motor. This paper, therefore. verified the causes of distortion of measured thrust, and proposed the theoretical method to estimate the true thrust from the distorted thrust. And also the proposed method was applied to virtual thrust stand using computer simulation, and showed good result. As a result of that, the proposed method was proven to be valid and applicable to estimate distorted thrust.
Study on Combustion Characteristics of Unielement Thrust Chambers with Various Injectors
Seonghyeon Seo ; Lee, Kwang-Jin ; Han, Yeoung-Min ; Kim, Seung-Han ; Kim, Jong-Gyu ; Moon, Il-Yoon ; Seol, Woo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 85~94
Experimental study on combustion characteristics of double swirl coaxial injectors has been conducted for the assessment of critical injector design parameters. A reusable, unielement thrust chamber has been fabricated with a water-cooled copper nozzle. Two principal design parameters. a swirl angle and a recess length, have been investigated through hot firing tests for the understanding of their effects on high pressure combustion. Clearly, both parameters considerably affect the combustion efficiency, dynamics and hydraulic characteristics of an injector. Internal mixing of propellants in a recess region increases combustion efficiency along with the increase of a pressure drop required for flowing the same amount of mass flow rates. It is concluded that pressure buildup due to flame can be released by the increase of LOx flow axial momentum or the reduction of a recess length. Dynamic pressure measurements of the thrust chamber show varied dynamic behaviors depending on injector configurations.
Combustion and Performance Efficiency of Boron Carbide Fuel in Solid Fuel Ramjet
Lee, Tae-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 95~101
An experimental investigation was conducted to investigate the effects of the equivalence ratio and air mass flux on the combustion efficiency in a solid fuel ramjet used fuel grains which were highly loaded with boron carbide. Combustion efficiency increased with increasing equivalence ratio (grain length), and decreasing air mass flux. Higher inlet air temperature produced higher combustion efficiencies, apparently the result of enhanced combustion of the larger boron particles those burn in a diffusion controlled regime. Short grains which considered primarily of the recirculation region produced larger particles and lower combustion efficiencies. The result of the normalized combustion efficiency increased with inlet air temperatures coincident with the result of the Brayton cycle thermal and the total efficiency relating to the heat input.
The Interpretation of Separation Mechanism of Ridge-Cut Explosive Bolt Using Simulation Programs
Lee, Yeung-Jo ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 102~114
The present work has been developed the interpretation processor including the behavior of material failure and the separation phenomena under transient dynamic loading (the operation of explosive bolt) using AUTODYN V4.3, SoildWork 2003 and TrueGrid V2.1 programs. It has been demonstrated that the interpretation in ridge-cut explosive bolt under dynamic loading condition should be necessary to the appropriate failure model and the basic stress of bolt failure is the principal stress. The use of this interpretation processor developing the present work could be extensively helped to design the shape and the amount of explosives in the explosive bolt having a complex geometry. It is also proved that the interpretation processor approach is an accurate and effective analysis technique to evaluate the separation mechanism in explosive bolts.
Development Scheme For A Supersonic Turbo Jet Engine
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 2, 2004, Pages 115~121
This paper suggests the development scheme for a supersonic turbo jet engine in order to increase the performance and to reduce the weight based on the characteristics of components as well as the current technology trends.