Determination of Aerodynamically Adequate Fillet Geometry in Turbocompressor Blade Rows
Abstract
A method for determining the fillet radius likely to prevent separation of the corner flow at the intersection of an airfoil and a hub or shroud where no relative motion or gap is present is described. A computer program was written which, from the physical dimensions of the blading and the flow characteristics at the blading entrance and exit, calculates the corner boundary layer parameters allowing the prediction of the required fillet radius. An incompressible turbulent flow, with the influence of endwall boundary layer secondary flow on the development of the corner boundary layer, is considered.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1981
- Accession Number
- ADA102170
Entities
People
- Lucien L. Debruge
Organizations
- Wright Laboratory