• The KSFM Journal of Fluid Machinery
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• v.6 no.3 s.20
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• pp.58-63
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• 2003

The performance of turbo pump drops rapidly and it gets into break-down when the void fraction reaches above the threshold value because the impeller flow passage is choked up with air bubbles. Phenomenological understanding of break-down and pumping recovery mechanisms under air-water two-phase flow conditions are therefore important for pump designers and essential assignment for researchers. In this paper, we investigated the characteristics of break-down and pumping recovery due to entrained air occurring inside a screw-type centrifugal pump which has a wide flow passage mainly through the findings of suction and discharge pressures, rotational speed, flow rate measurements and visualization.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2002.11a
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• pp.379.1-379
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• 2002

In this paper the leakage prediction and rotordynamic analysis of an annular seal with a smooth rotor and spiral-grooved stator are performed. For developing a theoretical model, the three-control-volume analysis of the circumferentially-grooved seal is expanded by considering pressure reduction due to the pumping effect of spiral groove and pressure flow through the spiral groove. Validation to the present analysis is achieved by comparisons with available experimental data. (omitted)

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.5
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• pp.65-71
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• 2010

Performance test of the 75ton class turbopump turbine was performed. Using the measured turbine power characteristics in the wide-range operational conditions, variations of nozzle velocity ratio, total pressure loss, and relative flow angle to the pressure ratios and rotational speeds are quantified. Efficiency and nozzle exit pressure behavior was also investigated and compared with 30ton turbopump turbine data. A rotor blade was redesigned based on the test results and CFD analysis.

• Proceedings of the KIEE Conference
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• 2008.07a
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• pp.1458-1459
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• 2008

미세 유체 제어 시스템 (마이크로 펌프, 마이크로 밸브, 마이크로 채널, 마이크로 믹서 등)의 집적은 화학 및 바이오 유체를 제어하는 Lab-on-a-chip 의 일부분으로서 사용되며 이러한 시스템의 집적은 Lab-on-a-chip 개발을 위해 필수적으로 요구된다. 본 논문에서는 이러한 microchip을 구현하기 위해서 초미세 유체 제어 소자인 마이크로 펌프와 마이크로 밸브를 같은 기판 위에 Polydimethylsiloxane (PDMS)와 indium tin oxade (ITO)를 사용하여 집적하였다. 그리고 밸브의 반복 작동 시 계속적인 유량의 감소를 줄이기 위해 PDMS 의 혼합비를 달리하여 PDMS membrane 의 기계적 특성을 강화시켰다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.21 no.8
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• pp.1034-1045
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• 1997

For the improvement of the pump characteristics in the partial capacity range, it must be verified that the influence of the impeller design factor on the internal flows and the influence of the impeller internal flows on the pump characteristics. In this paper, in order to understand the influence of inlet angles on flow conditions and characteristics of a mixed flow pump, experiments were carried out for three kinds of impeller, which have the same outlet angle distributions and meridional section shapes. Results show that separation and stall in the partial capacity range can be controlled by the inlet angles. The relationship between the separation - stall at the impeller leading edge and the discharge flow conditions is clarified.

• The KSFM Journal of Fluid Machinery
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• v.15 no.5
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• pp.5-10
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• 2012

An experimental test facility for the complete characteristics of pumps is constructed at KIMM(Korea Institute of Machinery and Materials). All sensors instrumented in test facility for measuring flow rate, pressure, force and moment are in-situ calibrated by primary method. This paper describes the test facility and test technique of the complete characteristics of pumps, together with an experimental test results for a reactor coolant pump which is designed at KIMM for the first time in Korea. The test results for the mixed-flow type pump of $n_s$=1.425 are presented by three curves: constant head, torque, and speed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.38-44
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• 2010

Performance test of the 75ton class turbopump turbine was performed. Through the turbine power measurement in the wide-range operational conditions, velocity ratio, total pressure loss, and relative flow angle characteristics was quantified. Efficiency and nozzle exit pressure behavior was also investigated and compared with 30ton turbopump turbine data. A rotor blade was redesigned based on the test results and CFD analysis.

• Proceedings of the Korea Water Resources Association Conference
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• 2006.05a
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• pp.1323-1327
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• 2006

일반적으로 화력발전소는 원활한 원료 및 냉각수의 공급과 환경적인 요인으로 인해 내륙보다는 해안에 위치하고 있다. 발전소의 안정성을 확보하기 위해서는 고열의 발전기를 냉각하는 냉각설비들이 반드시 필요하며 이를 위해 취수로를 통한 냉각수의 원활한 공급이 이루어져야 한다. 이러한 냉각수 공급은 대용량 펌프에 의해 이루어지며, 취수로 구조물의 형상 및 냉각수의 흐름조건에 따라 성능과 수명이 좌우된다. 특히 해안에 위치하는 지리적 여건상 직접취수가 많으며 이러한 경우 유사가 취수로에 유입되어 펌프 흡입 시 균열과 임펠러 마모 등을 유발시켜 펌프의 안전에 악영향을 미치게 된다. 따라서 취수로에 유사의 퇴적을 유도하는 침사지를 설계하게 되며 Hydraulic Institute Standards(1998)에서는 허용설계유속을 0.2 m/s 이하로 정하고 있다. B 발전소는 직경 3 m의 대형 취수관로 3개를 통해 매우 빠른 유속으로 취수로에 유입되는 냉각수 계통 구조물을 가지고 있어 침사지 내 유속이 허용기준을 초과하였다. 본 연구에서는 침사지내 유속을 만족시키기 위해 다양한 에너지 소산 구조물 설계방안을 제시하였다. 각 설계방안에 따른 흐름 특성 및 유속 분포를 파악하고 common bay 내에서의 난류특성을 분석하여 비교.검토하였다. 수리모형실험 결과를 통해 각각의 설계방안에 따른 침사지의 효율을 평가하였으며 최적의 에너지 소산 구조물에 대한 설계방안을 제안하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.8
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• pp.77-84
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• 2003

Structural analyses of a turbine bladed-disk for a liquid rocket turbopump are peformed to investigate the safety level of strength and vibration at design point. Due to the high rotational speed of the turbopump, effects of centrifugal forces are carefully considered in the structural analysis. Thermal load caused by extreme temperature distribution is also considered as an external force applied to turbine bladed-disk. A three dimensional finite element method (FEM) is used for cyclic symmetry structural analyses with the MSC/NASTRAN DMAP Alter. Interblade phase angles are considered to investigate structural dynamic characteristics as a function of rotational speed. Through the numerical analysis, effects of centrifugal and thermal loads on the turbine bladed-disk are examined.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.220-223
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• 2005

System design parameters of gas generator cycle liquid rocket engines were investigated and compared in the present study. Characteristic velocity of combustor, pressure drop of combustor injector, exit pressure of pump, pump efficiency and specific power of turbine were considered as a system design parameter. The result shows the characteristic velocity is in the range of 1700-1770 m/s, pressure drop of combustor injector, 4-10 bar, pump exit pressure ratio to combustion pressure, 120-230%, pump efficiency, 60-80%, specific power of turbine, $0.28-0.58MW{\cdot}s/kg$.