Multi-pass cooling for turbine airfoils
Patent
·
OSTI ID:1018725
- Palm City, FL
An airfoil for a turbine vane of a gas turbine engine. The airfoil includes an outer wall having pressure and suction sides, and a radially extending cooling cavity located between the pressure and suction sides. A plurality of partitions extend radially through the cooling cavity to define a plurality of interconnected cooling channels located at successive chordal locations through the cooling cavity. The cooling channels define a serpentine flow path extending in the chordal direction. Further, the cooling channels include a plurality of interconnected chambers and the chambers define a serpentine path extending in the radial direction within the serpentine path extending in the chordal direction.
- Research Organization:
- Siemens Energy, Inc. (Orlando, FL)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42644
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- Patent Number(s):
- 7,967,567
- Application Number:
- US Patent Application 11/728,887
- OSTI ID:
- 1018725
- Country of Publication:
- United States
- Language:
- English
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