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Title: 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

References (34)

Radial wafer airfoil construction patent May 1980
Cooled turbine blade patent August 1987
Turbine blade trailing edge cooling construction patent September 1993
Film cooling of turbine airfoil wall using mesh cooling hole arrangement patent December 1994
Internally cooled gas turbine vane patent February 1997
Internal cooling of turbine airfoil wall using mesh cooling hole arrangement patent November 1997
Shear jet cooling passages for internally cooled machine elements patent January 1998
Apparatus for cooling a gas turbine airfoil and method of making same patent May 1998
Reduction of turbomachinery noise patent December 1999
Axial serpentine cooled airfoil patent August 2000
Method and apparatus for cooling a wall within a gas turbine engine patent July 2001
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
Turbine engine component having enhanced heat transfer characteristics and method for forming same patent July 2003
Cooled rotor blade with vibration damping device patent April 2006
Hot gas path component with mesh and impingement cooling patent February 2007
Drillable super blades patent June 2007
Microcircuit cooling for blades patent December 2007
Turbine blade cooling system having multiple serpentine trailing edge cooling channels patent October 2008
Airfoil trailing edge cooling patent October 2008
Airfoil with supplemental cooling channel adjacent leading edge patent January 2009
Turbine airfoil cooling system with bifurcated and recessed trailing edge exhaust channels patent June 2009
Component comprising a multiplicity of cooling passages patent August 2009
Turbine airfoil with serpentine trailing edge cooling circuit patent March 2010
Turbine bladed with tip cooling patent May 2010
Thin turbine rotor blade with sinusoidal flow cooling channels patent July 2010
Turbine airfoil with spiral trailing edge cooling passages patent August 2010
Film-cooling augmentation device and turbine airfoil incorporating the same patent November 2011
Turbine blade patent January 2012
Rotor blades for turbine engines patent April 2012
Trailing Edge Cooling System in a Turbine Airfoil Assembly patent-application March 2013

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