Airfoil cooling with internal cavity displacement features
A turbine airfoil including a central cavity defined by an outer wall including pressure and suction sides extending between and joined at leading and trailing edges, and a chordal axis extends generally centrally between the pressure and suction sides. Rib structures located in the central cavity define radial central channels extending across the chordal axis. Radial near wall passages are defined between the rib structures and each of the pressure and suction sides of the outer wall. The radial near wall passages are each open to an adjacent central channel along a radial extent of both the near wall passages and the adjacent central channel to define a radial flow pass associated with each central channel. The flow passes are connected in series to form a serpentine cooling path extending in the direction of the chordal axis.
- Research Organization:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42644
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- Patent Number(s):
- 10,428,686
- Application Number:
- 15/128,492
- OSTI ID:
- 1576251
- Resource Relation:
- Patent File Date: 2014 May 08
- Country of Publication:
- United States
- Language:
- English
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