Proceedings of the Korean Society of Propulsion Engineers Conference (한국추진공학회:학술대회논문집)

  • 2004.03a
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  • Pages.839-847
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  • 2004
  • /
  • 1975-342X(pISSN)
The Korean Society of Propulsion Engineers (한국추진공학회)
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A Study on The Performance of Supersonic Cascade with The Nozzle Inlet Boundary

  • Shin, Bong-Gun (The graduate school of Aerospace Engineering department of Pusan National University) ;
  • Jeong, Soo-In (The graduate school of Aerospace Engineering department of Pusan National University) ;
  • Kim, Kui-Soon (Department of Aerospace Engineering, Pusan National University) ;
  • Lee, Eun-seok (Korea Aerospace Research Institute)
  • Published : 2004.03.01
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Abstract

In this study, the flow characteristics within supersonic cascades are numerically investigated by using Fine Turbo, a commercial CFD code. Cascade flows are computed for three different inlet conditions. : a uniform supersonic inlet condition, a linear nozzle and a converging-diverging nozzle located in front of cascades. The effect of inlet conditions is compared and flow characteristics including shock patterns and shock-boundary layer interaction are analyzed. Also the effect of design parameters such as pitch-chord ratio, blade angle and blade surface curvature on the flow within supersonic cascades are studied.

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