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터보펌프용 Inter-Propellant Seal의 개발 현황
곽현덕(Hyun D. Kwak),전성민(Seong-Min Jeon),김진한(Jinhan Kim) 한국트라이볼로지학회 2004 한국트라이볼로지학회 학술대회 Vol.39 No.-
To avoid an unexpected explosion occurring from a mixture of LOx and fuel, Inter-Propellant Seal (IPS) is used in a Turbopump. This paper presents a brief theoretical backgrounds of IPS and also reports preliminary test results. Tests were performed up to 1.5 MPa and 20,000 rpm and leakage performance of IPS was evaluated. As a result it was verified that leakage flow rate of IPS satisfied its design requirement.
터보펌프 Mechanical Face Seal의 성능 시험
곽현덕(Hyun D. Kwak),전성민(Seong-Min Jeon),김진한(Jinhan Kim) 한국유체기계학회 2006 유체기계 연구개발 발표회 논문집 Vol.- No.-
The mechanical face seal has been tested in Korea Aerospace Research Institute for turbopump applications. In this paper the ongoing performance test results of the mechanical face seal are briefly described. By means of simulating a practical operating environment, the leakage performance of mechanical face seal is monitored. In addition the carbon wear is measured to estimate the service life time of mechanical face seal. Up to now the test results show the acceptable leakage performance and resonable wear tendency as well. Lastly the repeated test has been carrying out to guarantee the endurance performance of mechanical face seal based on the turbopump service life time.
곽현덕(Hyun D. Kwak),김대진(Dae-Jin Kim),김진선(Jin-Sun Kim),김진한(Jinhan Kim),노준구(Jun-Gu Noh),박편구(Pyun-Goo Park),배준환(Jun-Hwan Bae),신주현(Ju-Hyun Shin),윤석환(Suck-Hwan Yoon),이항기(Hanggi Lee),전성민(Seong-Min Jeon),정은환(E 한국추진공학회 2014 한국추진공학회 학술대회논문집 Vol.2014 No.12
한국형발사체 3단에 적용될 액체로켓엔진용 터보펌프 개발 시제에 대한 조립체 성능시험이 성공적으로 수행되었다. LN2와 물이 적용된 상사매질 조립체 시험을 통해 터보펌프 단품 간 출력 매칭 및 조립체 레벨에서의 수력/공력 성능 검증이 이루어졌다. 실매질 시험은 LOX와 케로신의 실제 운용환경에서 터보펌프의 설계성능, 엔진운용영역 탈설계 성능 검증시험이 엔진의 운용시간을 적용하여 이루어졌다. 각 조립체 시험에서는 펌프의 흡입성능 검증도 병행되었다. 개발된 7톤급 액체로켓용 터보펌프는 성능, 운용시간의 엔진 요구규격을 잘 만족시키는 것으로 확인되었다. Performance tests of the turbopump for the 7-tonf liquid rocket were successfully conducted. The performance of sub-components -two pumps and a turbine- and their power matching were measured and examined firstly under the LN2 and water environment.. In the real propellant-LOX and keroseneenvironment 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 the same as engine operating time. Not only the pump performance but also pump suction capability were investigated in the tests by setting the pump inlet pressure lower than nominal operating value. It have been found that developed-turbopump satisfied all of the engine required performances.
곽현덕(Hyun D. Kwak),전성민(Seong Min Jeon),김진한(Jinhan Kim) 한국유체기계학회 2005 유체기계 연구개발 발표회 논문집 Vol.- No.-
To perform a cryogenic development test for Tribo-elements in a turbopump, a cryogenic bearing and seal test facility (BSTF) is designed and currently under construction in KARI. The working fluid is liquid nitrogen operating at a temperature -197 ℃. The maximum operating pressure and volume flow rate of BSTF are 100 bar and 10 liters per second, respectively. The development tests of floating ring seals, inter-propellant seals (IPS) and cryogenic ball bearings in a turbopump will be performed using the BSTF. This paper briefly described design requirements and procedures of BSTF.
터보펌프 터빈 공력성능시험의 회전체 동역학적 진동분석사례
곽현덕(Hyun D. Kwak),윤석환(Suk-Hwan Yoon),전성민(Seong-Min Jeon),김진한(Jin-han Kim) 한국항공우주연구원 2006 항공우주기술 Vol.5 No.1
터보펌프 터빈 공력성능시험 중의 진동 특성을 측정하여, 정상상태 및 비정상상태에서의 진동의 크기, 시험시간 누적에 따른 진동의 변화추이를 분석하였다. 이를 바탕으로 비정상진동의 특성과 원인을 파악하였으며, 시험시간 누적에 따른 진동의 변화추이 분석을 통해 시험에 사용되는 볼 베어링의 수명 및 교체주기를 제시하였다. This report presents the analysis results of vibration characteristics concerning the aerodynamic performance test of turbopump turbine. In the means of measuring the acceleration during aerodynamic test, vibrational condition was carefully monitored. Based on the measured results the trend of vibration was analyzed and the ball bearing service time was suggested as well. In addition the cause of abnormal vibration, which was monitored during tests, was described.
곽현덕(Hyun D. Kwak),전성민(Seong-Min Jeon),김진한(Jinhan Kim) 한국트라이볼로지학회 2008 한국윤활학회지(윤활학회지) Vol.24 No.6
An inter-propellant seal (IPS) for high thrust turbopump is designed. With given operating conditions and requirements, the inter-propellant seal is designed to satisfy the leakage characteristics which is less than 0.1 % of normal flow rate of pumps. A numerical analysis is developed to predict the leakage flow rate. The results show that the maximum leakage of LOX and kerosene are less than 0.1 % of normal flow rate of pumps, respectively. Based on the numerical analysis results, the detail of IPS is performed, Finally a prototype of IPS is manufactured to perform sets of performance tests in the near future.
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.
곽현덕(Hyun D. Kwak),전성민(Seong-Min Jeon),김진한(Jinhan Kim) 한국트라이볼로지학회 2010 한국윤활학회지(윤활학회지) Vol.26 No.6
An inter-propellant seal (IPS) for 75 ton class thrust turbopump was tested. Leakage characteristics were presented with a given range of pressure difference under cryogenic as well as room temperature conditions. For cryogenic tests, liquid nitrogen was used as analogic fluid of liquid oxygen (LOX) while water was used instead of kerosene for room temperature condition. Test results showed that IPS had satisfactory leakage performance. Additionally endurance test was conducted to prove the life time of manufactured IPS and the tested IPS had successfully survived during required life time, 2100 seconds.