Two methods are commonly used to control the secondary/separated flows (and associated losses) in supersonic turbines: endwall contouring and airfoil stacking. In the current investigation the flow path between the first-stage vanes and rotors, and the stacking of the first-stage vanes were varied in an effort to improve turbine performance. The geometric variations have been studied by performing a series of unsteady three-dimensional numerical simulations for the two-stage turbine.
Effects of Endwall Geometry and Stacking on Two-Stage Supersonic Turbine Performance
2002 AIAA Aerospace Sciences Meeting
2002-01-01
Preprint
Keine Angabe
Englisch
TECHNICAL NOTES - Effects of End Wall Geometry and Stacking on Supersonic Turbine Performance
Online Contents | 2002
|AIAA | 1975
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