The Aerodynamic Significance of Fillet Geometry in Turbocompressor Blade Rows

[+] Author and Article Information
L. L. Debruge

Air Force Aero Propulsion Laboratory, Wright-Patterson AFB, OH 45433

J. Eng. Power 102(4), 984-993 (Oct 01, 1980) (10 pages) doi:10.1115/1.3230371 History: Received December 10, 1979; Online September 28, 2009


This paper describes a theoretical investigation of the influence of fillet radius on the aerodynamic behavior of turbocompressors. The fillet is that found at the intersection of an airfoil and a hub or shroud where no relative motion or gap is present. A modified power law velocity is used in conjunction with experimental estimates of the three-dimensional corner boundary layer extent to obtain values of the interference displacement and friction coefficient for the 90 deg corner flow which are in fair agreement with Gersten’s experimental results. Likewise, interference displacement and friction coefficient are obtained in the case of a corner flow in a dihedral > 150 deg for which experimental data is unavailable but where the low curvature of the stream surfaces allows the three-dimensional boundary layer extent to be calculated from Bertotti’s integral momentum equation. The boundary layer characteristics thus obtained are then applied, by means of a polyhedral approximation, in the evaluation of the influence of 90 deg corner fillet on corner flow separation. Some guidelines are provided relating the fillet radius to physical dimensions of the blading.

Copyright © 1980 by ASME
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