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이장환,한용운,Lee, Jang-Hwan,Han,Yong-Un 대한기계학회 1997 大韓機械學會論文集B Vol.21 No.4
The change of the structure of homogeneous turbulence subject to irrotational strains has been studied in an anti-Morel type diffuser (center matched cubic contour) using the hot wire anemometry. It was observed that the profiles of mean velocities and turbulence velocities along the center line were stable at the entrance region but rapidly changed near the matching point. The wall induced turbulence at the entrance region grows fast and was diffused toward the center at downstream. It was also observed that the axial turbulence grows faster than the radial one in the middle region of the diffusing flow and that the diffusing process has the vortex compression mechanism due to the conservation of angular momentum. These phenomena are frequently observed at the initial flow region of the free jet.
이장환(JW Lee),김철수(CS Kim),이승호(SH Lee),안종호(JH Ahn),이태호(TH Lee) 대한산부인과학회 1980 Obstetrics & Gynecology Science Vol.23 No.6
희귀한 난소임신 1예를 보고하였고 아울러 이의 문헌고찰을 겸하였다. A ovarian pregnancy, which is extremely rare type of ectopic pregnancy was presented, and a brief review of literature was added.
Canted slit 형상의 핀틀 인젝터 로켓엔진에서 특성길이 변화에 따른 연소성능
이장환(Janghwan Lee),김완찬(Wanchan Kim),김민석(Minseok Kim),김선훈(Sunhoon Kim),고영성(Youngsung Ko),김형모(Hyungmo Kim) 한국추진공학회 2015 한국추진공학회 학술대회논문집 Vol.2015 No.11
본 연구에서는 케로신과 액체산소를 추진제로 사용하는 핀틀 인젝터의 기초설계자료를 확보하고 설계절차를 확립하여 고정형 핀틀 인젝터를 제작하였다. 이를 적용한 액체로켓엔진의 연소실 특성길이에 따른 연소시험을 통해 연소성능에 관한 연구를 수행하였다. 연소실 특성길이 0.41 m에서 1.07 m까지의 연소시험을 통해 연소성능이 약 90∼95%까지 측정되었으며 추진제 조합에 따른 특성길이 추천치는 1.02~1.27 m이나 특성길이 0.76 m이상에서 최적의 성능을 가짐을 확인하였다. In this study, a fixed pintle injector which uses kerosene and liquid oxygen as propellants was made by collecting basic design data and establishing a design procedure. Combustion performance of the liquid rocket engine was studied by combustion tests for the effect of combustion chamber characteristic length. As a result of hot fire tests, combustion efficiency was measured from 90 to 95 percentage by various characteristic lengths from 0.41m to 1.07m. Also, it showed optimum performance over 0.76m characteristic length, whereas characteristic length of the propellant combinations is recommended from 1.02m to 1.27m.