International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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An Experimental Study on the Flow Characteristics ofa Supersonic Turbine Cascade as Pressure Ratio

  • Cho, Jong-Jae (Department of Aerospace Engineehng,Pusan Nation University) ;
  • Jeong, Soo-In (Department of Aerospace Engineehng,Pusan Nation University) ;
  • Kim, Kui-Soon (Department of Aerospace Engineehng,Pusan Nation University) ;
  • Lee, Eun-Seok (Korea Aerosoace Research Institute)
  • Published : 2004.12.31
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Abstract

In this paper, a small supersonic wind tunnel was designed and built to studythe flow characteristics of a supersonic impulse turbine cascade by experiment. Theflow was visualized by means of a single pass Schlieren system. The supersoniccascade with 3-dimensional supersonic nozzle was tested over a wide range ofpressure ratio. Highly complicated flow patterns including shocks, nozzle-cascadeinteraction and shock boundary layer interactions were observed.

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References

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