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ISSN Online: 2377-424X

ISBN Print: 1-56032-797-9

International Heat Transfer Conference 11
August, 23-28, 1998, Kyongju, Korea

A NUMERICAL STUDY ON A SUPERSONIC COMPRESSOR CASCADE USING R-ε TURBULENCE CLOSURE

Get access (open in a dialog) DOI: 10.1615/IHTC11.1280
pages 541-546

Resumo

A finite-difference method based on upwind flux difference splitting has been used to predict the performance of supersonic axial compressor cascades and to examine the complex physical flow phenomena. The prediction with Abe et als two-equation turbulence model showed good agreement with the experimental results near the zone of the shock-wave/turbulent boundary-layer interaction at different exit-inlet pressure ratios. The increase in exit-inlet pressure ratio caused slight reduction in shock loss but increase in viscous loss. The passive control of shock-wave interaction with turbulent boundary layer by a cavity reduced total pressure losses and the strength of shock-waves. A cavity under the shock foot point at the suction surface of the blades was used as a passive control. The effect of cavity length and depth on total pressure loss was studied. The proper size of cavities could reduce the total pressure losses even though it increased the viscous losses through the formation of shock-wave/turbulent boundary-layer zone of the cascade flowfield.