• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2001년도 춘계학술대회논문집
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• pp.735-743
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• 2001

This study was performed to evaluate the dynamic behavior of turbo pump unit. The acceptable separate margin of 1st critical speed was obtained by the use of elastic-ring inserted ball bearing, while the poor separate margin of 1$\^$st/ critical speed was appeared in the case without the elastic-ring. In addition, the results show that the stiffness and damping of plain seals gain more separate margin of 2nd critical speed. However the wear or the failure of seals could reduce the 2$\^$nd/ critical speeds near the operating speed.

• 한국유체기계학회 논문집
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• 제4권2호
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• pp.22-28
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• 2001

This study was performed to evaluate the dynamic behavior of turbo pump unit. The acceptable separate margin of $1^{st}$ critical speed was obtained by the use of elastic-ring inserted ball bearing, while the poor separate margin of $1^{\st}$ critical speed was appeared in the case without the elastic-ring. In addition, the results show that the stiffness and damping of plain seals give more separate margin of $2^{nd}$ critical speed. However the wear or the failure of seals could reduce the $2^{nd}$ critical speed near the operating speed.

• 한국유체기계학회 논문집
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• 제5권2호
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• pp.22-28
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• 2002

Steady state flow calculations are conducted for the newly-designed turbo-pump inducers to validate the performance of Tascflow code. Hydrodynamic performance is evaluated, and structures of the passage flow and leading edge recirculation are also investigated. The calculated results show good coincidence with the experimental data of the static pressure performance and velocity profiles near the leading edge. Upstream recirculation, tip leakage and vortex flow at the blade tip and near leading edge are main sources of pressure losses. Amount of pressure losses from the upstream to the leading edge corresponds to that of pressure losses through the whole blade. The total viscous losses are considerably large due to the strong secondary flow.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제31회 추계학술대회논문집
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• pp.15-18
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• 2008

본 연구에서는 터보펌프 조립체-가스발생기 연계시험 중 개회로 시험에 대한 시동 특성을 분석하였고 수치적으로 해석하였다. 시험에서 터빈의 시동 및 구동은 수소 기체로 수행하였고 그에 따른 가스발생기 점화 및 연소압의 발달을 살펴보았고 해석도 동일한 조건으로 수행하여 결과를 비교하였다. 회전수의 발달 특성은 시험과 잘 일치하는 것을 볼 수 있었고 가스발생기 연소압 발달 특성의 경우 정성적인 기울기가 일치하는 것을 볼 수 있었다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제31회 추계학술대회논문집
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• pp.19-22
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• 2008

본 연구에서는 터보펌프 조립체-가스발생기 연계시험 중 폐회로 시험에 대한 시동 특성을 분석하였고 수치적으로 해석하였다. 시험에서 터빈의 시동은 수소 기체로 수행하였고 구동은 가스발생기에서 연소로 발생하는 연소 기체로 작동하였다. 그에 따른 가스발생기 점화 및 연소압의 발달을 살펴보았고 해석도 동일한 조건으로 수행하여 결과를 비교하였다. 회전수의 발달 특성은 시험과 잘 일치하는 것을 볼 수 있었고 가스발생기 연소압 발달 특성의 경우 정성적으로 일치하는 것을 볼 수 있었다.

• 신재생에너지
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• 제1권4호
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• pp.30-37
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• 2005

Cycle simulation of Ground Source Heat Pump[GSHP] system was carried out to determine the design specification of basic components such as turbo compressor and heat exchangers. Part load operation characteristics of the designed GSHP system was estimated using the compressor and heat exchanger performance data. A 50RT class turbo compressor for GSHP system is now under development, in which R134a refrigerant is adopted as working fluid. The compressor with variable cascade diffusers is designed to work both in cooling and heating modes so that it can actively keep up with the climate change with high efficiency. The normal running speeds of the compressor are 59000rpm for heating mode and 70000rpm for tooling mode respectively. It has two identical impellers at both ends of the rotor so as to minimize aero-induced thrust force effectively. GSHP system was coupled with a vortical type heat exchanger, and heat gain and heat loss from ground were evaluated per a bore hole. For the optimal integration of the heat pump system, its header for circulating fluid was combined with the ground heat exchangers in parallel and series configuration.

• 한국유체기계학회 논문집
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• 제4권4호
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• pp.43-52
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• 2001

Pumps arre used extensively for transporting fluid in many ships. However, the present state of pumps used in the large merchant ships has not been studied. In this paper, we have reported the general description of the operating pumps according to the different ship types(Bulk, Container, Car-Carrier, Tanker, LNG). Moreover, the pump total powers are compared with the main engine Normal Continuous Rating power and the pump total weights are also compared with the ship deadweight.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.1142-1148
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• 2006

The floating ring seal which is used in the high pressure turbo pump is frequently used in the oxidizer pump and the fuel pump of the turbo pump of the liquid propulsion rocket, because it is able to minimize clearance to decrease the leakage flow rate. But, floating ring seal has a tendency to increase the force which caused instability of system as the eccentricity ratio increases. In this paper, we devised design of floating ring seal which decrease contact area between floating and supporting ring. Modified floating ring seal has a tendency to decrease the eccentricity ratio compare with original floating ring seal. The whirl frequency ratio which is able to distinguish stability of system decrease compare with original floating ring seal

• 항공우주기술
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• 제2권2호
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• pp.151-156
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• 2003

액체 로켓엔진시스템은 연료공급방식에 따라 가압식과 터보펌프식으로 나눌 수 있으며, KSR-III 과학로켓에서는 가압식 액체 로켓엔진을 사용하였으나, 현 시점에서 우주발사체 1단으로 가압식 액체로켓엔진을 사용하기에는 극복해야할 기술적 과제가 많으며, 가압식 액체로켓 기술의 한계로 인해 터보펌프식 액체 로켓엔진 개발이 요구되고 있다. 본 연구에서는 터보펌프식 액체로켓 엔진시스템의 기본적 특성을 검토하기 위하여 국내 액체로켓 엔진의 차세대 추진제 조합으로 주목받고 있는 케로신(Kerosene)-액체산소(LOX)와 메탄(Methane)-액체산소 추진제에 대한 분석을 수행하였다. 또한 터보펌프식 액체로켓 엔진시스템의 기본적 특성을 검토하기 위해 직접 궤도 및 전이 궤도를 거쳐 위성을 투입하는 발사체 사이징 안을 각각 고려하여 분석하였다.

• Applied Science and Convergence Technology
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• 제24권2호
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• pp.27-32
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• 2015

We analyzed the destruction patterns of a turbo-molecular pump (TMP) resulting from its sudden exposure of a foreline to the atmospheric pressure due to a destruction of the foreline connecting clamp of an ICP dry etcher for 300 mm wafers during high-vacuum operation ($5{\times}10^{-6}$ Torr). Unlike in the case of view port's breakage, the TMP's rotor module was crashed inside the chamber. The primary damage resulted from the collision of the blades and stators, and the secondary damage resulted from the breaking of the rotor - driving shaft assembly. The fixing screws of the rotor and axial shaft were bent and broken when the TMP controller output the maximum current even after the crash event. Electrical power consumption analysis of the TMP power controller confirmed it. The stress distributions were analyzed by a finite element method using CFD-ACE+ multi physics software. Rotating inertia of each parts and kinetic energies were calculated as well. 68% of the rotational kinetic energy is deposited by the rotor - shaft module.