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레이저 회절법을 이용한 축대칭 분무 구조의 공간 분포 변환에 관한 실험적 연구
양승연(Seungyeon Yang),이충훈(Choonghwl Lee),구자예(Jayae Koo),정석호(Sukho Chung) 한국자동차공학회 2000 한국 자동차공학회논문집 Vol.8 No.1
Spatially resolved liquid volume fractions from a set of line-of-sight laser diffraction measurements for axisymmetric sprays generated from a pintle-type gasoline injector have been tomographically reconstructed by Abel transforomation, Fourier transformantion and onion peeling method. Spatially resolved liquid volume fractions classified into 32 size groups were translated into number density distributions and equivalent diameters which show well evaporating characteristics of SI engine fuel sprays. These data were also obtained from the phase Doppler measurements for the same sprays. The comparison between laser diffraction measurements and phase Doppler measurements at some spatial measurement points shows that Fourier transformation reconstructs more reasonable spatially resolved characteristics for axisymmentric<br/> sprays as well as for asymmetric sprays.
발사체 인젝터 특별세션 : 액체-액체 모사추진제를 사용한 핀틀 인젝터의 분무 특성
유기정 ( Kijeong Yu ),손민 ( Min Son ),( Kanmaniraja Radhakrishnan ),구자예 ( Jayae Koo ) 한국액체미립화학회 2015 한국액체미립화학회 학술강연회 논문집 Vol.2015 No.-
Spray angle characteristics of a pintle injector using liquid-liquid phases were compared with the characteristics of the injector using liquid-air phases. The spray angles were measured from spray images captured by backlight method using a CMOS camera. The water and air were injected in the pressure range of 0.1 bar - 1.0 bar and pintle opening distances were controlled from 0.2 mm to 1.0 mm. The spray angles of liquid-liquid phase decreased linearly as the momentum ratios increased. While the spray angle characteristics of liquid-liquid phases had similar trend as the characteristics of liquid-gas, break up characteristics were different.
부분입사형 초음속 터빈의 블레이드 표면 온도에 블레이드 앞전 형상이 미치는 영향
이상도(Sangdo Lee),김귀순(Kuisoon Kim),이인철(Inchul Lee),구자예(Jayae Koo),문인상(Insang Mun),이수용(Suyoung Lee) 한국추진공학회 2008 한국추진공학회지 Vol.12 No.4
In this paper, numerical analysis of the surface gas temperature on turbine blades has been performed to investigate the temperature profiles characteristics of a partial admission supersonic turbine driven by high temperature and pressure gas of pyro-starter with two different types of turbine blade edge shape. In order to examine the surface gas temperature on turbine blades at initial starting, computations tlave been carried out at several turbine rotational speeds in the range of 0~10,000 rpm for each type of turbine edge shape. Sharp edge and Round edge types were taken as the turbine edge shape factor. As turbine rotational speed increased, the average temperature of turbine blades was further decreased. It was also found that the surface temperature of turbine blades with a sharp edge was lower than round-type edge turbine blades.