Accession Number : ADP003077

Title :   Compressor and Turbine Blade Boundary Layer Separation,

Corporate Author : UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT

Personal Author(s) : Werle,M. J.

Report Date : SEP 1983

Pagination or Media Count : 13

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.

Descriptors :   *Boundary layer flow, *Flow separation, Bubbles, Compressor blades, Turbine blades, Finite difference theory, Inviscid flow, Pressure gradients, Adverse conditions, Transonic flow, Shock waves, Wake, Leading edges, Trailing edges

Distribution Statement : APPROVED FOR PUBLIC RELEASE