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초음속 터번 익렬 앞전 형상 및 노즐-익렬 간격에 따른 유동 특성에 대한 실험적 연구
조종재,김귀순,김진한,정은환,정호경,Cho Jong-Jae,Kim Kui-Soon,Kim Jin-Han,Jeong Eun-Hwan,Jeong Ho-Kyung 한국추진공학회 2005 한국추진공학회지 Vol.9 No.4
본 연구에서는 초음속 충동형 터빈의 유동특성을 알아보기 위해 소형 초음속 풍동을 설계하였으며 Single pass Schlieren system을 이용하여 유동을 가시화하였다. 실험은 2차원 초음속 노즐과 익렬을 조합하여 블레이드 앞전 형상과 노즐-익렬 간극에 따라 실시하였다. 실험을 통해 충격파를 포함한 복잡한 유동 형태와 노즐-익렬, 충격파-경계층 상호작용 등을 관찰할 수 있었다. In this paper, a small supersonic wind tunnel is designed and built to study the flow characteristics of a supersonic impulse turbine cascade. The flow is visualized by means of a single pass Schlieren system. The supersonic cascade with 2-dimensional supersonic nozzle was tested for various blade leading edge shapes and gaps between the nozzle and cascade. Highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions are observed.
초음속 터빈의 축방향 간격비에 따른 유동 특성에 대한 실험적 연구
조종재(Jong-Jae Cho),김귀순(Kui-Soon Kim),정은환(Eun-Hwan Jeong) 한국항공우주학회 2007 韓國航空宇宙學會誌 Vol.35 No.2
본 연구에서는 초음속 충동형 터빈의 유동특성을 알아보기 위해 소형 초음속 풍동을 설계하였다. 실험은 2차원 초음속 노즐과 익렬을 조합하여 터빈 설계 인자 중의 하나인 터빈 축 간격비에 따라 실시하였으며 단일경로 슐리렌(Schlieren) 시스템을 이용하여 유동을 가시화하였다. 그리고 다채널 압력측정 시스템을 이용하여 터빈 익렬 내의 정압력과 전압력을 측정하였다. 이러한 실험을 통해 충격파를 포함한 복잡한 유동 형태와 유동박리, 충격파-경계층 상호작용 등을 관찰할 수 있었다. A small supersonic wind tunnel was designed and built to study the flow characteristics of a supersonic impulse turbine cascade. The supersonic cascade with a 2-dimensional supersonic nozzle was tested for the axial gap ratio (δ) of the supersonic turbine that is the one of the turbine design parameter. Firstly, the flow was visualized by a single pass Schlieren system. Next, total and static pressure of the cascade were measured by a pressure scanning system. Highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions, flow characteristics of the supersonic turbine were observed.
조종재(Jong-Jae Cho),정수인(Soo-In Jeong),김귀순(Kui-Soon Kim),박창규(Chang-Kyu Park) 대한기계학회 2004 대한기계학회 춘추학술대회 Vol.2004 No.4
In this paper, a small supersonic wind tunnel is designed and built to study the flow characteristics of a supersonic impulse turbine cascade. The flow is visualized by means of a single pass Schlieren system. The supersonic cascade with 3-dimensional supersonic nozzle was tested over a wide range of nozzle installation angle. Highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions are observed.
부분입사형 초음속 터빈의 노즐-로터 상호작용에 관한 3차원 수치적 연구
윤원근,조종재,김귀순,김진한,Yun, Won-Geun,Cho, Jong-Jae,Kim, Kui-Soon,Kim, Jin-Han 항공우주시스템공학회 2007 항공우주시스템공학회지 Vol.1 No.1
In this paper, numerical results for 3-D supersonic turbine flow have been firstly compared with the experimental results to verify results computed by $Fine^{TM}/Turbo$. It was found that $Fine^{TM}/Turbo$ can accurately predict flow characteristics within supersonic turbine. Next, an grid system for 3D turbine flow was optimized selected through grid independency test. Finally, the effect of axial gap between rotor and nozzle and chamfer angle of blade edge on the flow characteristics within 3-D supersonic turbine was analyzed with Frozen Rotor method.
부분입사형 초음속 터빈 익렬내 유동 특성에 관한 수치적 연구
신봉근(Bong-Gun Shin),조종재(Jong-Jae Cho),정수인(Soo-In Jeoung),김귀순(Kui-Soon Kim),이은석(Eun-Seok Lee) 대한기계학회 2004 대한기계학회 춘추학술대회 Vol.2004 No.4
Turbo-pump system, an essential component of liquid rockets and induced weapons, adopts a partial admission axial turbine which drives pump. And the turbine of a turbo-pump system is usually operated at supersonic condition due to its high loading chracteristics. Therefore, reseaches about flow and performance characteristics of a partial admission supersonic turbine must be preceeded to progress the aerospace and defense industries as well as the development of turbo-pump systems. In this study, flow characterisitics within blades of the partial admission supersonic turbine are numerically investigated by using Fine Turbo, a commercial CFD Code. Before performing the numercial analyses, to verify accuracy of the numerical result computed by Fine Turbo, I performed the comparison between the numerical results with J.J.Cho’s experimental results. It is found that the numerical results show good agreement with the experimental results. Computations about the partial admission supersonic turbine have been performed to investigate flow characteristics including shock patterns. It is also found that the flow and performance of partial admission supersonic turbine are largely depend on shocks ocurred in the nozzle and at the leading edge of blades, expansion or compression at exit of nozzle and separations occurred in passage.