A Numerical Study on Passive Control of Shock Wave/Turbulent Boundary Layer in a Supersonic Compressor Cascade

J. I. Seo ； S. D. Kim ； D. J. Song

《International Journal of Rotating Machinery》 2002卷 (2002/12) Pp. 423-430

https://doi.org/10.1155/S1023621X02000404

摘要

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, Kondoh, and Nagano's two-equation turbulence model showed good agreement with the experimental results near the zone of 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 an increase in viscous loss. The passive control of shockwave interaction with turbulent boundary layer by a cavity reduced total pressure losses and strength of shock waves. A cavity under the shock foot point at 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 total pressure losses even though it increased viscous losses through the formation of shock-wave/turbulent boundary-layer zone.

關鍵字

Shock-wave/turbulent boundary layer interaction ； Transonic/supersonic compressor cascade ； Cavity ； CSCM upwind flux difference splitting algorithm ； Abe et al.'s turbulence model ； Passive control