• Title/Summary/Keyword: schlieren system

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Experimental Study on the Wall Jet Flow Induced by Impinging Circular Jet on Arotating Disk (충돌제트로 인한 회전원판 위의 벽제트유동에 관한 실험적 연구)

  • 강형석;유정열
    • Transactions of the Korean Society of Mechanical Engineers
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    • v.18 no.12
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    • pp.3386-3394
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    • 1994
  • An experimental study has been performed on the flow over a rotating disk, where the diameter of the disk is 500 mm and the maximum vertical deviation of the upper surface is $50 \mu{m}$ for the whole range of the angular velocity up to 3400 rpm. The flow visualization experiment for the wall jet flow induced by impinging circular jet is carried out using schlieren system and measurements are made by 3-hole and 5-hole pitot tubes. Schlieren photographs show that as the rotating speed increases the wall jet flow becomes more stable and the size of the largest eddies becomes smaller. Measurements for impinging jet flow on the stationary disk verify the accuracy of the present experiment, and those for free rotating disk flow display the existence of transition region from laminar to turbulent flows. Measurements for impinging jet flow on the rotating disk exhibit the interaction between the wall jet and the viscous pumping effect, which explains the decay in size of turbulent eddies illustrated by the schlieren photographs.

An experimental study on the flow characteristics of a supersonic turbine cascade as the leading edge shape and the nozzle-cascade gap (초음속 터빈 익렬 앞전 형상 및 노즐-익렬 간격에 따른 유동 특성에 대한 실험적 연구)

  • Cho Jong-Jae;Kim Kui-Soon;Kim Jin-Han;Jeong Eun-Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.349-354
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    • 2005
  • 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.

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An Experimental Study on the Flow Characteristics of a Supersonic Turbine Cascde as Nozzle Installation Angle (노즐 설치각에 따른 초음속 터빈 익렬의 유동 특성에 대한 실험적 연구)

  • Cho Jong-Jae;Jeong Soon-In;Kim Kui-Soon;Park Chang-Kyu
    • Journal of the Korean Society of Propulsion Engineers
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    • v.8 no.4
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    • pp.1-8
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    • 2004
  • 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 sin91e 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.

An experimental study on the flow characteristics of a supersonic turbine cascade with the leading edge chamfer angle (초음속 터빈의 익렬 앞전 모서리각에 따른 유동 특성에 대한 실험적 연구)

  • Cho Jong-Jae;Kim Kui-Soon;Jeong Eun-Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.05a
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    • pp.361-366
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    • 2006
  • 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 leading edge chamfer angle $(\gamma)$ 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. Finally, highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions, flow characteristics of the supersonic turbine were observed.

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An experimental study on the expansion loss of a supersonic turbine with the cascade position (익렬 위치에 따른 초음속 터빈의 확산 손실에 대한 실험적 연구)

  • Cho, Jong-Jae;Kim, Kui-Soon;Jeong, Eun-Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.387-392
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    • 2006
  • A small supersonic wind tunnel was designed and built to study the flow characteristics of a supersonic impulse turbine cascade. Experiments are performed to find flow characteristics of supersonic turbine with the cascade positions and to find factor of expansion loss. The supersonic cascade with a 2-dimensional supersonic nozzle was tested with the cascade positions. Firstly, the flow was visualized by Z-type Schlieren system. Finally, highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions, flow characteristics of the supersonic turbine were observed.

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Behavior of 2-Stage Injection on Diesel Spray (2단분사 디젤분무의 거동)

  • Park, B.D.;Kwon, S.I.;Oh, J.G.;Kim, S.J.
    • Journal of ILASS-Korea
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    • v.5 no.4
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    • pp.33-39
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    • 2000
  • The behavior of the 2-stage spray was studied by using the schlieren method with the high pressure common-rail injection system. The spray injected 2 times with the interval of $0.3ms{\sim}1.5ms$ between the 1st and the 2nd spray in a modeled combustion chamber of constant volume bomb. In this case, the quantity of injected fuel of 1st and 2nd also changed. The schlieren photograph shows that the 2nd spray goes further away than the 1st spray when the quantity of the 1st spray is less than that of the 2nd spray. The dispersion of the vapour to the combustion chamber is not affect in a 10% of 1st spray quantity. When the 1st spray quantity is more than the 2nd spray, the vapour scattering of spray is good.

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Experimental Study on the Flow Characteristics of Supersonic Turbine with the Axial Gap Ratios (초음속 터빈의 축방향 간격비에 따른 유동 특성에 대한 실험적 연구)

  • Cho, Jong-Jae;Kim, Kui-Soon;Jeong, Eun-Hwan
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.2
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    • pp.136-142
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    • 2007
  • 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 (${\delta}$) 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.

An experimental study on the flow characteristics of a supersonic turbine as the axial gap (초음속 터빈의 축방향 간격에 따른 유동 특성에 대한 실험적 연구)

  • Cho Jong-Jae;Kim Kui-Soon;Kim Jin-Han;Jeong Eun-Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2005.11a
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    • pp.100-105
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    • 2005
  • 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 is tested for various gaps between the nozzle and cascade. By the experiment, the flow is visualized and static pressure of the cascade was measured. And highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions, flow characteristics of the supersonic turbine are observed.

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An Experimental Study on the flow Characteristics of a Supersonic Turbine Cascade as the Leading Edge Shape and the Nozzle-Cascade Cap (초음속 터번 익렬 앞전 형상 및 노즐-익렬 간격에 따른 유동 특성에 대한 실험적 연구)

  • Cho Jong-Jae;Kim Kui-Soon;Kim Jin-Han;Jeong Eun-Hwan;Jeong Ho-Kyung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.9 no.4
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    • pp.66-72
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    • 2005
  • 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.