Compressor and Turbine Blade Boundary Layer Separation,
Abstract
Numerous sites on compressor and turbine blades are susceptible to the phenomenon of boundary layer separation. In such situations it is found that the boundary layer is incapable of negotiating a local adverse pressure gradient, which is subsequently relieved as it breaks away from the surface and induces a strong interaction with the inviscid stream. Since losses and heating due to such occurrences can be significant, a need continues to exist for efficient, and reliable prediction techniques for this class of problems. A review is presented for the results of a multiyear, multiphase program aimed at developing and assessing finite difference techniques for a wide range of separation induced problems. Results are given for leading edge bubbles, transonic shock induced separations, cove side bubbles, and trailing-edge, induced wake bubbles. Both the analytical technique and collaborating experimental studies are discussed and directions for future search identified.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1983
- Accession Number
- ADP003077
Entities
People
- M. J. Werle
Organizations
- United Technologies Corporation