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스윕과 린을 적용한 부분흡입형 초음속 터빈의 성능 특성에 관한 수치적 연구
권태운(Taeun Kwon),정수인(Sooin Jeong),조종재(Jongjae Cho),김귀순(Kuisoon Kim),정은환(Eunhwan Jeong) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.11
본 논문에서는 스윕과 린의 각도에 따른 부분흡입형 초음속 터빈의 성능 특성을 분석하기 위하여 유동해석을 실시하였다. 유동해석은 스윕과 린의 3가지 각도(5°, 10°, 15°)에 대해 수행되었다. 해석결과, 전반적으로 스윕 각도에 커질수록 효율이 증가하였다. 다만, 스윕 각도가 5°일 때에는 기본익형 보다 효율이 더 떨어졌다. 린 각도가 커질수록 전압력 손실은 줄어들었지만 정효율은 감소하였다. The present study deals with numerical flow analysis to investigate the effect of sweep and lean on the performance characteristics of a partial admission supersonic turbine. The flow analysis was performed for three different angles. The angles of sweep and lean are 5°, 10°, 15°. The results of the flow analysis showed that the efficiency is improved as the sweep angle is increased. However, a sweep angle of 5° was less effective in comparison with the baseline model. The total pressure loss was reduced as the lean angle is increased, but the total to static efficiency was decreased.
스윕과 린을 적용한 부분흡입형 초음속 터빈의 성능 특성에 관한 수치적 연구
권태운(Taeun Kwon),정수인(Sooin Jeong),조종재(Jongjae Cho),김귀순(Kuisoon Kim),정은환(Eunhwan Jeong) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.2
The present study deals with numerical flow analysis to investigate the effect of sweep and lean on the performance characteristics of a partial admission supersonic turbine. The flow analysis was performed for three different angles. The angles of sweep and lean are 5°, 10°, 15°. The results of the flow analysis showed that the efficiency is improved as the sweep angle is increased. However, a sweep angle of 5° was less effective in comparison with the baseline model. The total pressure loss was reduced as the lean angle is increased, but the total to static efficiency was decreased.
노즐 형상에 따른 부분 흡입형 초음속 터빈의 성능특성에 관한 수치적 연구
조종재(Jongjae Cho),권태운(Taeun Kwon),김귀순(Kuisoon Kim),정은환(Eunhwan Jeong),박편구(Pyungoo Park) 한국추진공학회 2010 한국추진공학회지 Vol.14 No.3
A supersonic nozzle specially is one of the important part in a supersonic turbine usually adapted the impulse type, because the flow acceleration in the turbine theoretically is done only in the nozzle. The present study deals with numerical flow analysis to investigate the effect of nozzle shapes on the performance characteristics of a partial admission supersonic turbine. The flow analysis was performed for four different nozzle shapes. The shapes of the nozzles are circular, square, straight rectangular and bent rectangular nozzles. The results of the flow analysis showed that the aerodynamic loss of turbine is highly affected by the nozzle shapes, and the partial admission loss is also highly depended on nozzle shapes. Specially, bent rectangular nozzle had the best performance among the nozzle shapes.