http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
왕승원(Seung-Won Wang),정용갑(Yonggahp Chung),김성룡(Seong-Lyong Kim),한영민(Yeoung-Min Han) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.12
추진기관 시스템 시험설비의 유공압시스템에는 발사체 각 단별 엔진상부와 추진제 저장탱크의 공간, 산화제 저장탱크 제어밸브의 내부공간 퍼지에 필요한 고온기체 공급시스템이 있다. 고온기체 공급시스템은 고온기체 생산을 위한 압축기와 압축기의 냉각을 위한 냉각장비, 온도 및 노점을 낮추기 위한 드라이어, 유분제거 및 청정도 유지를 위한 필터 등으로 구성되어 있다. 본 논문에서는 추진기관 시스템 시험설비를 구축하는데 있어 고온기체 공급시스템의 설계내용에 대해 소개하였다. Thermo-starting system is a sub-system of hydraulic/pneumatic system in Propulsion System Test Complex(PSTC), supply gas to purge propellant tanks, upper space of the engines(1st, 2nd, 3rd) and control valves on oxidizer tank. Thermo-starting system designed compressor for the production of high temperature gas, the cooling equipment for compressor, the dryer for dew point and filters. In this paper, the design results of thermo-starting system is introduced.
김성룡(Seong-Lyong Kim),왕승원(Seung-Won Wang),한영민(Young-Min Han) 한국추진공학회 2017 한국추진공학회지 Vol.21 No.4
TPTF (Turbopump Real Propellant Test Facility) at Naro Space Center has used alcohol burner system to simulate the gas flow of gas generator of liquid rocket engine. During the test at TPTF, the temperature and pressure at turbine inlet were smoothly increased while those of the gas generator of engine were constant. Present research developed a simulation code for the burner and the piping system and applied to the system. The calculation results were in good agreement with the test, and confirmed quantitatively that the non-steadiness is due to the heat transfer of the pipe. While the insulation of the pipe is ineffective, the length has a large impact on the turbine inlet condition. The present research clarified the empirically estimation of test condition, and can be applied to determination of the following test conditions.
김진선(Jin-Sun Kim),왕승원(Seung-Won Wang),우성필(Seongphil Woo),김성룡(Seong-Lyong Kim),한영민(Yeoung-Min Han),고영성(Youngsung Ko) 한국추진공학회 2014 한국추진공학회 학술대회논문집 Vol.2014 No.12
고성능의 액체로켓엔진을 확보하기 위해서는 터보펌프개발과 그 검증시험이 필수적인 항목이라고 볼 수 있다. 터보펌프의 실험적 검증을 위해 액체산소와 케로신을 토대로 한 실매질 시험설비의 구축을 완료하였다. 주요 서브시스템에 대한 검증시험이 이루어 졌고, 터보펌프 개발모델을 연계한 종합시험을 수행함으로써 시험설비의 인증이 이루어 졌다. 앞으로 제작되는 모든 터보펌프의 실매질 개발시험과 인증시험이 본 시험설비에서 수행될 예정이다. The development and verification test of a turbopump are fundamental to have an high-performance LRE(liquid rocket engine). A turbopump real-propellant test facility based on liquid oxygen and kerosene has been constructed for the experimental validation of the turbopump. The verification tests of sub-system were performed and the performance of the total system was tested with the development model of the turbopump. Development and validation tests of all turbopumps to be manufactured will be performed at the turbopump real-propellant test facility.
정은환(Eunhwan Jeong),곽현덕(Hyun-Duck Kwak),김대진(Dae-Jin Kim),김진선(Jin-Sun Kim),노준구(Jun-Gu Noh),박민주(Min-Ju Park),박편구(Pyun-Goo Park),배준환(Jun-Hwan Bae),신주현(Ju-Hyun Shin),왕승원(Seong-Won Wang),윤석환(Suck-Hwan Yoon) 한국추진공학회 2016 한국추진공학회지 Vol.20 No.2
Performance tests of a 75-tonf liquid rocket engine turbopump were conducted. The performance of sub-components - two pumps and a turbine - and their power matching were measured and examined firstly near the design speed under the LN2 and kerosene environment. In the real propellant - LOX and kerosene - environment tests, design and off-design performance of turbopump were fully verified in regime of the rocket engine operation. During the off-design performance tests, turbopump running time was set longer than the engine operating time to verify the pump operability and set the pump inlet pressure close to design NPSHr to investigate pump suction capability in parallel. It has been found that developed-turbopump satisfied all of the engine required performances.
곽현덕(Hyun D. Kwak),김대진(Dae-Jin Kim),김진선(Jin-Sun Kim),노준구(Jun-Gu Noh),박민주(Min-Ju Park),박편구(Pyun-Goo Park),배준환(Jun-Hwan Bae),신주현(Ju-Hyun Shin),왕승원(Seong-Won Wang),윤석환(Suck-Hwan Yoon),이항기(Hanggi Lee),전성민( 한국추진공학회 2015 한국추진공학회 학술대회논문집 Vol.2015 No.11
75톤급 액체로켓엔진용 터보펌프 개발 시제에 대한 조립체 성능시험이 터보펌프 실매질 시험설비에서 수행되었다. LN2와 케로신을 적용한 첫 시험에서는 터보펌프 단품들의 조립체 레벨, 설계회전수 근방에서의 수력/공력 성능 및 출력 매칭 점검이 이루어 졌으며 LOX와 케로신을 적용한 실매질 시험에서는 터보펌프의 설계성능 및 엔진운용영역 탈설계 성능 검증시험이 이루어졌다. 탈설계시험의 경우, 엔진의 운용시간을 초과하여 터보펌프가 운용되었으며 펌프입구압력을 설계 요구유효흡입 양정(NPSHr)에 가깝게 설정하여 흡입성능 검증을 병행하였다. 개발된 75톤급 액체로켓용 터보펌프는 성능, 운용시간의 엔진 요구규격을 잘 만족시키는 것으로 확인되었다. Performance tests of the developing 75-tonf liquid rocket engine turbopump were conducted. The performance of sub-components - two pumps and a turbine - and their power matching were measured and examined firstly near the design speed under the LN2 and kerosene environment. In the real propellant - LOX and kerosene - environment tests, design and off-design performance of turbopump were fully verified in regime of the rocket engine operation. During the off-design performance tests, turbopump running time was set longer than the engine operating time and pump suction capability were investigated in parallel by setting the pump inlet pressure close to design NPSHr. It have been found that developed-turbopump satisfied all of the engine required performances.