• 유체기계공업학회:학술대회논문집
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• 2005.12a
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• pp.348-353
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• 2005

A cryogenic test facility has been developed to perform inducer and pump tests using liquid nitrogen. Performance tests of a turbopump in the maximum 50ton-thrust class can be performed with cryogenic fluid in the facility which operates at a temperature around $-196^{\circ}C$ with the rotational speed up to 30,000rpm. To verify the reliability of the cryogenic pump test facility, hydraulic performance tests of an inducer were accomplished, and their results were compared with the result from a water test The results confirm the reliability of the cryogenic test facility, and it is expected to contribute for on-going development of a turbopump for liquid rocket engines.

• The KSFM Journal of Fluid Machinery
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• v.9 no.4 s.37
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• pp.20-26
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• 2006

A cryogenic test facility has been developed to perform inducer and pump tests using liquid nitrogen. Performance tests of a turbopump in the maximum 50ton-thrust class can be performed with cryogenic fluid in the facility which operates at a temperature around -196oC with the rotational speed up to 30,000rpm To verify the reliability of the cryogenic pump test facility, hydraulic performance tests of an inducer were accomplished, and their results were compared with the result from a water test. The results confirm the reliability of the cryogenic test facility, and it is expected to contribute for on-going development of a turbopump for liquid rocket engines.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.32 no.4
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• pp.249-254
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• 2008

Hydrodynamic performance test of a turbopump for a liquid rocket engine is carried out. The turbopump is composed of an oxidizer pump, a fuel pump and a turbine, and the two pumps are driven by the turbine. In the test, water is used for the pumps as working media and air is used for the turbine. Performance parameters of pumps and a turbine are drawn, and a power balance between the pumps and the turbine are calculated. The calculation shows a good power balance, which implies that the pump component tests, the turbine component test and the assembly test are reliably performed. At the starting period of the test, pressure rise-flow rate curve of a pump gradually approaches the ideal curve which could be obtained by very slow starting.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.34 no.4
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• pp.391-397
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• 2010

Performance tests of a liquid-oxygen pump were carried out using liquid nitrogen (LN2) as a working fluid in a cryogenic turbopump test facility in Korea Aerospace Research Institute (KARI). The tests were performed at 30-55% of the design rotational speed, and the results were compared with those from a water test. The experimental results confirmed the similarity of the hydraulic performance, which allows the prediction of the pump performance at a design rotational speed of 20,000 rpm. The overall cavitation performance of the pump in the cryogenic environment was better than that in the water environment for all ranges of flow rates and rotational speeds. Critical cavitation number at the design flow rate was determined as 0.012 from the cryogenic test, and as 0.024 from the water test. The improved cavitation performance is due to the thermodynamic effect in cryogenic fluids.

• Journal of Energy Engineering
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• v.17 no.2
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• pp.67-76
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• 2008

A thermal-hydraulic integral effect test facility, ATLAS (Advanced Thermal-hydraulic Test Loop for Accident Simulation), has been constructed at KAERI (Korea Atomic Energy Research Institute). Recently several integral effect tests for the reflood period of a LBLOCA (Large Break LOss of Coolant Accident) of the APR1400 have been performed with the ATLAS. In the APR1400 a high flow condition is changed to a low flow condition due to an fluidic device during an operation of the SIT. As the self-controlled fluidic device was not installed in the ATLAS, a set of characterization tests was performed to simulate its injection capability from the SIT for the APR1400 simulation. In the ATLAS the required SIT flow rate in the high flow condition was acquired by installing orifices with an optimized flow area to throttle the SIT discharge line and the low flow condition was achieved by changing the opening of the flow control valve in the SIT injection line. The test results showed that the safety injection systems of the ATLAS could simulate the required high and low flow rates of the SIT for the APR1400 simulation efficiently.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2007.12a
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• pp.357-359
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• 2007

해양에너지원 중에서 파랑은 모든 해역에 폭넓게 분포하므로 가용에너지원이 풍부하고 에너지를 회수하기 위한 장치를 설치할 수 있는 해역 또한 광범위하며 반도의 지형을 지닌 우리나라의 연안 해역에 대규모로 활용이 가능한 에너지 자원중 하나이다. 본 연구는 새로운 방식인 파력발전용 횡류형터빈인 케이슨 내장형 횡류터빈을 개발하기에 앞서 파랑수조의 왕복운동을 CFD해석을 통하여 구현하는 것이다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2003.06a
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• pp.840-843
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• 2003

The Paper presents theoretical and experimental investigation of plunger type water hydraulic pump (plunger pump). An analysis of Crank shaft for plunger pump is carried out. With this results, the optimal dimensions of plunger pump are determined. And performance test results about slide resistance, hydraulic leak test, efficiency-pressure. and flow-speed and flow-pressure are presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.88-93
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• 2017

For the control of pre-burner combustion pressure, the open angle of TTR(Throttle for Thrust Regulation) valve was varied from $143^{\circ}$ to $185^{\circ}$ while testing of cold flow, ignition, combustion. The major performance variables of rocket engine and hydraulic performance of TTR valve regarding the open angle was verified. However the controllability of pre-burner combustion pressure was not verified due to the limitations of test. The comprehensive research will be done after supplementing these problems.

• Proceedings of the KSME Conference
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• 2001.06e
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• pp.619-624
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• 2001

A performance test facility for turbopump inducer cavitation was developed and the inducer cavitation performance tests were performed. Major components of the performance test facility are driving unit, test section, piping, water tank, and data acquisition and control system. The maximum of testing capability of this facility are as follows: flow rate - 30kg/s; pressure - 13 bar; rotational speed 10,000rpm. This cavitation test facility is characterized by the booster pump installed at the outlet of the pump that extends the flow rate range, and by the pressure control system that makes the line pressure down to vapor pressure. The vacuum pump is used for removing the dissolved air in the water as well as the line pressure. Performance tests were carried out and preliminary data of test model inducer were obtained. The cavitation performance test and cavitation bubble flow visualization were also made. This facility is originally designed for turbopump inducer performance test and cavitation test. However it can be applied to the pump impeller performance test in the future with little modification.

• Proceedings of the Korea Society for Simulation Conference
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• 2000.04a
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• pp.168-173
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• 2000

지금까지 국내에서 설치되어 있는 원전 시뮬레이터용 노심 (Neutronics) 모델 프로그램은 주로 전산기 성능이 오늘날 비해 낮은 환경에서 실시간으로 노물리 계산을 위해 중성자 확산(Diffusion)현상을 미리 반영한 곡선을 사용하는 등 빠른 계산을 위해 많은 가정과 간략화가 있었다. 본 논문에서는 중성자 물리 계산을 2 Group 3-D로 계산이 가능한 최신의 노심코드(REMARK)를 이용하여, WH사가 공급한 900Mw의 3 Loop PWR인 영광 1호기 12주기를 기준으로 한 시뮬레이터의 노심모델 개발하기 위한 핵설계 전산체계인 APA(ALPHA-PHOENIX-ANC) 시스템의 출력으로부터 자동으로 REMAR 입력데이타를 생성하기 위한 GUI툴 개발과 개발된 노심모델의 자체 검증 및 원자력발전소 사고해석에 쓰이는 최적평가코드(RETRAN)를 기반으로 하는 최신 실시간 열수력 시뷸레이션(ARTS) 모델과 결합(Integration)되어 원자로 냉각재 펌프 1대 정지 및 터빈정지 시험등 과도시험한 결과를 기술하였으며 개발된 노심 모델은 원자력 교육원 2호기 시뮤레이터에 적용될 예정이다.