Cooling arrangement for a gas turbine component
Patent
·
OSTI ID:1169639
A cooling arrangement (82) for a gas turbine engine component, the cooling arrangement (82) having a plurality of rows (92, 94, 96) of airfoils (98), wherein adjacent airfoils (98) within a row (92, 94, 96) define segments (110, 130, 140) of cooling channels (90), and wherein outlets (114, 134) of the segments (110, 130) in one row (92, 94) align aerodynamically with inlets (132, 142) of segments (130, 140) in an adjacent row (94, 96) to define continuous cooling channels (90) with non continuous walls (116, 120), each cooling channel (90) comprising a serpentine shape.
- Research Organization:
- Siemens Aktiengesellschaft, Munich, DE (Europe)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- SC0001359
- Assignee:
- Siemens Aktiengesellschaft (Munich, DE)
- Patent Number(s):
- 8,951,004
- Application Number:
- 13/657,923
- OSTI ID:
- 1169639
- Country of Publication:
- United States
- Language:
- English
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