• Transactions of the Korean Society of Mechanical Engineers B
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• v.34 no.5
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• pp.563-568
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• 2010

Turbopump-gas generator open-loop coupled tests are performed during the development of a 30tonf-LOx/Kerosene rocket engine. In the turbopump-gas generator open-loop tests, the propellants to gas generator are supplied from the outlets of turbopump, while the gas exhausted from the gas generator is vented out to the atmosphere, instead of being used to turbine driving. This paper presents the objectives, procedure, and results of the open-loop coupled test, in addition to a schematic representation of the test apparatus and the operating conditions for the test facility system and control system. The results of turbopump-gas generator open-loop coupled test confirm chill-down procedure, startup characteristics, nominal operability and smooth shutdown of the open-loop coupled Test Plant in test conditions simulating engine system operation environment.

• The KSFM Journal of Fluid Machinery
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• v.4 no.1 s.10
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• pp.63-68
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• 2001

• The KSFM Journal of Fluid Machinery
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• v.12 no.3
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• pp.79-83
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• 2009

• The KSFM Journal of Fluid Machinery
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• v.4 no.3 s.12
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• pp.78-89
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• 2001

• 유체기계공업학회:학술대회논문집
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• 1998.02a
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• pp.55-62
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• 1998

• 유체기계공업학회:학술대회논문집
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• 1997.02a
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• pp.74-82
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• 1997

• 유체기계공업학회:학술대회논문집
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• 1997.02a
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• pp.196-205
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• 1997

• Transactions of the Korean Society of Mechanical Engineers B
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• v.35 no.3
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• pp.301-307
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• 2011

Turbo blowers are mainly used in refuse collection systems. We discuss blower performance in relation to the angle of the inlet vane installed at the upstream of the blower. The flow characteristics of the components are analyzed by three-dimensional Navier-Stokes analysis and compared to experimental results. A two-stage serially connected turbo blower is introduced to analyze the performance experimentally. Throughout the experimental measurements and the numerical simulation, the distorted inlet velocity generated in the small vane angle reduces the performance of the blower, because of the local leading-edge separation and the resulting non-uniform blade loading. We also perform a detailed flow analysis using the results obtained in the numerical simulation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.253-256
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• 2003

The engine core of a 65hp-turboshaft engine for UAV is developed and modified into a 55lbf-turbojet engine. Since the core engine is installed with a propelling nozzle, which has the same mass flow characteristics as the power generator of the turboshaft engine its mechanical and aerodynamic characteristics are basically the same as those of the complete engine. Engine output is not shaft power but thrust force that is easier to measure. The core engine is very useful for core test purpose. Besides, the core engine itself can be directly used for propulsion of small air vehicles.

• Proceedings of the KSME Conference
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• 2001.06e
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• pp.637-642
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• 2001

Performance and cavitation characteristics of a turbo pump inducer which is designed for oxygen pump is experimentally investigated. It is found that the static performance of inducer is dependent on the location of inlet pressure measurement and that enough distance from inducer is ensured for accurate evaluation of performance. With the increase of flow rate. NPSH tends to decrease as opposed to pump characteristics, which seems to be due to the cavitation region.