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Title: Cooling arrangement for a gas turbine component

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.
Authors:
;
Publication Date:
OSTI Identifier:
1169639
Report Number(s):
8,951,004
13/657,923
DOE Contract Number:
SC0001359
Resource Type:
Patent
Research Org:
Siemens Aktiengesellschaft, Munich, DE (Europe)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS