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- The drive towards high-work turbines has led to designs which can be compact, transonic, supersonic, counter rotating, or use a dense drive gas. These aggressive designs can lead to strong secondary flows and airfoil flow separation. In many cases the secondary and separated flows can be minimized by contouring the hub/shroud endwalls and/or modifying the airfoil stacking. In this study, three-dimensional unsteady Navier-Stokes simulations were performed to study three different endwall shapes between the first-stage vanes and rotors, as well as two different stackings for the first-stage vanes. The predicted results indicate that changing the stacking of the first-stage vanes can significantly impact endwall separation (and turbine performance) in regions where the endwall profile changes.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 20030003812.
AIAA Paper 2002-0078.
40th AIAA Aerospace Sciences Meeting and Exhibit; 14-17 Jan. 2002; Reno, NV; United States.
- Copyright, Distribution as joint owner in the copyright.
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