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Title: Cooling arrangement for a gas turbine component

Abstract

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.

Inventors:
;
Issue Date:
Research Org.:
Siemens Aktiengesellschaft, Munich, DE (Europe)
Sponsoring Org.:
USDOE
OSTI Identifier:
1169639
Patent Number(s):
8951004
Application Number:
13/657,923
Assignee:
Siemens Aktiengesellschaft (Munich, DE)
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
DOE Contract Number:  
SC0001359
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Lee, Ching-Pang, and Heneveld, Benjamin E. Cooling arrangement for a gas turbine component. United States: N. p., 2015. Web.
Lee, Ching-Pang, & Heneveld, Benjamin E. Cooling arrangement for a gas turbine component. United States.
Lee, Ching-Pang, and Heneveld, Benjamin E. Tue . "Cooling arrangement for a gas turbine component". United States. https://www.osti.gov/servlets/purl/1169639.
@article{osti_1169639,
title = {Cooling arrangement for a gas turbine component},
author = {Lee, Ching-Pang and Heneveld, Benjamin E},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {2}
}

Patent:

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