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PALW을 이용한 소경 스테인리스강 튜브의 용입특성 개선
황재련,윤석환,나석주,Hwang Jae-Ryeon,Yoon Suk-Hwan,Na Suck-Joo 대한용접접합학회 2004 대한용접·접합학회지 Vol.22 No.6
Laser welding is obviously an attractive method to join small, thin parts such as small stainless steel tubes, but it is very sensitive to the joint clearance and tolerance, and this makes laser welding difficult to obtain consistent welding qualities over time. Recently, Plasma Augmented Laser Welding(PALW) is being developed to solve these problems. In this study, plasma arc welding(PAW) was introduced to join conventional V-grooved butt joint of thin stainless steel strips using single laser heat source in manufacturing small stainless steel tubes. The effect of the welding speed enhancement is investigated by the experiments. Effects of welding directions, distance between the heat sources and intensity of arc heat source on the optimal welding speed was investigated. Through this research, it was confirmed that PALW process has higher welding speed and robustness than laser welding process.
폴리머의 레이저 투과접합 시 접합부의 기계적 성질에 관한 연구
차상우,김진범,윤석환,나석주,Cha, Sang-Woo,Kim, Jin-Beom,Yoon, Suk-Hwan,Na, Suck-Joo 대한용접접합학회 2007 대한용접·접합학회지 Vol.25 No.2
Laser Transmission Joining (LTJ) of plastics is a process in which light of suitable wavelength is transmitted through a transparent substrate that is in contact with an absorbing one. In this paper, LTJ is investigated by preliminary experiments from the viewpoint of mechanical engineering. To understand transmitting characteristics of each polymer substrate, transmission rate, reflection rate and absorption coefficient of polymer are measured by using a laser power-meter. Characteristics of joining in the spot welding and seam welding are investigated by measuring the fracture load. Fracture load increases in accordance to the laser power and irradiation time. However, when the laser power is over 60W and irradiation time over 4seconds, fracture load decreases. This phenomenon is probably due to heat-softening of materials. Besides, cavities are generated at a joint by evaporation of water molecules, which can be suppressed by introduction of a gap between two substrates.
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),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.
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 Duck 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 한국추진공학회 2015 한국추진공학회지 Vol.19 No.2
Performance tests of a turbopump for the developing 7-tonf liquid rocket engine were conducted. The performance of turbopump components and their power matching were measured and examined firstly under the LN2 and water environment.. In the real propellant(LOX and kerosene) environment tests, design and off-design performances of turbopump were fully verified. During the off-design tests, turbopump running time was set the same as engine operating time and pump inlet pressure were set lower than nominal operating value in order to investigate pump suction capability. It have been verified that subject turbopump satisfies required performance - flow rate, head, suction performance and operational time - in the operating regime of developing liquid rocket engine.