Compressor and Turbine Blade Boundary Layer Separation,
UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT
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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.