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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:
;
Publication Date:
Research Org.:
Siemens Aktiengesellschaft, Munich, DE (Europe)
Sponsoring Org.:
USDOE
OSTI Identifier:
1169639
Patent Number(s):
8,951,004
Application Number:
13/657,923
Assignee:
Siemens Aktiengesellschaft (Munich, DE)
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. 2015. "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 = {},
url = {https://www.osti.gov/biblio/1169639}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Feb 10 00:00:00 EST 2015},
month = {Tue Feb 10 00:00:00 EST 2015}
}

Works referenced in this record:

Cooled turbine blade
patent, August 1987


Turbine blade trailing edge cooling construction
patent, September 1993


Internally cooled gas turbine vane
patent, February 1997


Reduction of turbomachinery noise
patent, December 1999


Axial serpentine cooled airfoil
patent, August 2000


Article surface with metal wires and method for making
patent, June 2002


Method and apparatus for cooling a wall within a gas turbine engine
patent, June 2002


Turbine blade wall section cooled by an impact flow
patent, August 2002


Article having turbulation and method of providing turbulation on an article
patent, October 2002


Blade for gas turbines with choke cross section at the trailing edge
patent, November 2002


Drillable super blades
patent, June 2007


Microcircuit cooling for blades
patent, December 2007


Airfoil trailing edge cooling
patent, October 2008


Airfoil with supplemental cooling channel adjacent leading edge
patent, January 2009


Component comprising a multiplicity of cooling passages
patent, August 2009


Turbine blade
patent, January 2012


Rotor blades for turbine engines
patent, April 2012