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Urea-SCR 시스템 적용을 위한 스월 인젝터의 분무특성
홍정구(Junggoo Hong),구건우(Kunwoo Ku),김성열(Sungryoul Kim),이충원(Choongwon Lee),강명권(Myungkweon Kang),김경남(Kyungnam Kim),김재경(Jaekyoung Kim) 한국자동차공학회 2011 한국자동차공학회 지부 학술대회 논문집 Vol.2011 No.4
In this study, a swirl hollow cone injector, which has a good atomization performance at the low injection pressure relatively, was designed to apply the Urea-SCR. In order to investigate the spray pattern and SMD of a swirl injector, the spray visualization was conducted by using the simple swirl injector, and the images of the axial of stance from the nozzle exit. The shape of the spray was converted from the hollow cone to solid cone along the distance from the injector exit. The spray angle is increased and the SMD is decreased with increasing injection pressure respectively.
Urea-SCR 시스템 적용을 위한 스월 인젝터의 분무특성
홍정구(Junggoo Hong),구건우(Kunwoo Ku),김성열(Sungyoul Kim),이충원(Choongwon Lee),강명권(Myungkweon Kang),김경남(Kyungnam Kim),김재경(Jaekyoung Kim) 한국자동차공학회 2011 한국자동차공학회 부문종합 학술대회 Vol.2011 No.4
??In this study, a swirl hollow cone injector, which has a good atomization performance at the low injection pressure relatively, was designed to apply the Urea-SCR. In order to investigate the spray pattern and SMD of a swirl injector, the spray visualization was conducted by using the simple swirl injector, and the images of the spray cross-section were obtained from a sheet beam of Nd-Yag laser and CCD camera. The SMD of the swirl injector was measured with the axial of stance from the nozzle exit. The shape of the spray was converted from the hollow cone to solid cone along the distance from the injector exit. The spray angle is increased and the SMD is decreased with increasing injection pressure respectively.
하이브리드 로켓에서 초음파 센서를 이용한 고체 연료 후퇴율 측정 기법
박종원(JongWon Park),이충원(ChoongWon Lee),구건우(KunWoo Ku),윤명원(MyungWon Yoon) 한국유체기계학회 2006 유체기계 연구개발 발표회 논문집 Vol.- No.-
Hybrid rocket had many advantage with compared to solid and liquid rockets. In this study, swirl flow hybrid motor was designed and manufactured. And the methods of regression rate improvement were considered. Thrust was calculated with pressure of the combustion chamber and the regression rate was measured by using ultrasonic sensor technique in entire firing conditions. In this study, PMMA fuel and HTPB solid fuel were used in firing test.