• Proceedings of the KSRS Conference
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• 2005.10a
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• pp.656-658
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• 2005

KAERI (Korea Atomic Energy Research Institute) has been performing the project named PEFP (proton engineering frontier project). PEFP has been performing the project of a high power proton accelerator. Control system for 20 MeV proton accelerating structure has developed. We use the EPICS(Experimental Physics and Industrial Control System) tool kit as a foundation of the control system. EPICS is adopted for control systems which have OPI(OPerator Interface) and IOqlnput Output Controller). We have performed the PEPF control system on SUN workstation host computer. In this paper, we present the vacuum monitor, RFQ, and DTL Turbo pump control system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.167-170
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• 2006

For a short time a pyre-starter should turn the blades of a turbine to the adequate rotational speed by a single operation. Through this process the pressures of the components of a propellant rise rapidly up to the operating point, and the components enter into a gas-generator. Combustion in the gas-generator occurs to keep the turbopumps working. In this research characteristic parameters of a pyre-starter which correspond to the required performance of the turbopump before the gas-generator starts to work were selected

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.623-626
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• 2009

Hanwha Corporation Daejeon Plant have developed apogee Kick Motor of KSLV-I that is the first among nation space launch vehicle for five years from 2003. Now, we are joining in KSLV-II(Korea Space Launch Vehicle-II) project and developing Pyro starter which is turbo pump for the first start-up of liquid propulsion supply.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.221-224
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• 2009

Since the coupling of cavitation modeling with turbulent flow is the difficulty topic, a numerical simulation for two phase flow remains as one of the challenging issues in the society. This research focuses on the development of numerical code to deal with incompressible two phase flow around conical body combined with cavitation model suggested by Kunz et al. with k-e turbulent model. The simulation results are compared to experimental data to verify the validity of the developed code. The calculation results show very good agreement with experimental observations. Also, the calculation of cavitation in cryogenic fluid is being done by implementing the temperature sensitivity in government equations and it is still in the progress. This code have been being further extended to 3D compressible two phase flow for the study on the fluid dynamics around inducers and impellers in turbo pump system.

• 유체기계공업학회:학술대회논문집
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• 2006.08a
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• pp.551-554
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• 2006

Inhibition of propellant temperature rising in liquid propulsion rocket using cryogenic fluid as a propellant is very important. Especially propellant temperature rising during stand-by after filling and pre-pressurization can bring into cavitation in turbo-pump. One of the method preventing propellant temperature rising in cryogenic feeding system is recirculating propellant through the loop composed of propellant tank, feed pipe, and recirculation pipe. The circulation of propellant is promoted through gas-lift effect by gas injection to lower position of recirculation pipe. In this experiment liquid oxygen and gas helium is used as propellant and injection gas. Under atmospheric and pressurized tank ullage condition, helium injection flow-rate is varied to observe the variation of recirculating flow-rate and propellant temperature in the feed pipe. There is appropriate helium injection flow-rate for gas-lift recirculation system.

• Proceedings of the KIEE Conference
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• 1997.11a
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• pp.285-287
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• 1997

We have deposited hydrogen-free diamond-like carbon (DLC) films by pulsed laser deposition of graphite. Pulsed laser deposition (PLD) can be utilized to generate films with desired properties quite different from those of the starting material. Since DLC films grown by PLD using turbo pump are perpared without hydrogen, they have a higher density and a higher index of refraction than the hydrogenated DLC films. In this study, effects of the substrate temperature and laser energy density on the properties of DLC films were systematically investigated. The structure and properties of the films have been studied by scanning electron microscopy (SEM), Fourier Transform Infrared (FT-IR), X-ray diffraction (XRD), and Raman spectroscopy.

• Journal of computational fluids engineering
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• v.11 no.1 s.32
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• pp.16-20
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• 2006

The present study focuses on the flow analysis of a turbo pump inducer by performing both numerical and experimental methods. The head rise, efficiency and detailed flow fields such as outlet flow angles, pressure and velocity vectors are measured and compared with the computational data. Generally a good agreement is obtained between numerical and experimental results. However, some discrepancies are observed due to complex flow structures inside the inducer. Future calculations with an advanced turbulence model and a dense computational grid needs to be performed to obtain accurate numerical solution for the detailed flow fields.

• Transactions of the Korean Society of Automotive Engineers
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• v.18 no.4
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• pp.74-78
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• 2010

Turbocharger in the application to a diesel engine was widely used in automobile industries for the improvement of engine performance. To comply with stringent emission standards, ball bearing turbocharger has been developed by applying new emission reduction technology. Up to date turbocharger has been proved as an essential part of diesel engines by demonstrating its improved engine performance, fuel efficiency and reduced emission as well. In this research, the performance of the ball bearing turbocharger was compared by the conventional journal bearing type turbocharger. The results shows that ball baring turbocharger was proved to be 10~13% higher fuel efficiency and 30% less average emission than journal bearing turbocharger.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.35-44
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• 2004

In this study, one dimensional aerodynamic and structural study of a partial admission turbo pump turbine was performed. A turbine consists of a nozzle, rotor, outlet guide vanes. The aerodynamic characteristics of each component was derived from the governing equation and validated from the CFD calculations. One-dimensional basic design such as velocity triangles was conducted from the mean line analysis and modified from the 2-D and 3-D CFD analysis. The blade profile was determined by the CFD optimization. The thermal stress analysis and structural analysis are needed to be studied in the next design stage.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2001.11a
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• pp.15-18
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• 2001

In this paper, we investigate the rotordynamic characteristics of turbopump system for 9.5ton thrust liquid rocket engine. A finite element method is used to analyze the vibratior characteristics of a rotor-bearing system. The turbopump rotating system is modeled by shaft with sixty elements, nine rigid disks, four ball bearings and four floating ring seals. The calculation results show that the margin of 1st critical speed is increased from 12% to 68% by use of elastic damping ring. In addition, the margin of the 2nd critical speed near the operating speed is increased from 30% to 63% by the stiffness and damping of floating ring seals.