Cooling arrangement for a gas turbine component

Lee, Ching-Pang; Heneveld, Benjamin E

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A - human necessities
A01 - agriculture
A21 - baking
A22 - butchering
A23 - foods or foodstuffs
A24 - tobacco
A41 - wearing apparel
A42 - headwear
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A44 - haberdashery
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B - performing operations
B01 - physical or chemical processes or apparatus in general
B02 - crushing, pulverising, or disintegrating
B03 - separation of solid materials using liquids or using pneumatic tables or jigs
B04 - centrifugal apparatus or machines for carrying-out physical or chemical processes
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B62 - land vehicles for travelling otherwise than on rails
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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:: Lee, Ching-Pang; Heneveld, Benjamin E

Issue Date:: Tue Feb 10 00:00:00 EST 2015

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 F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES

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

Show more

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/187 - {Convection cooling}

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
F05D2250/185 - serpentine-like
F05D2260/22141 - using fins or ribs

Show less

DOE Contract Number:: SC0001359

Resource Type:: Patent

Country of Publication:: United States

Language:: English

Subject:: 33 ADVANCED PROPULSION SYSTEMS

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                    Lee, Ching-Pang, and Heneveld, Benjamin E. Cooling arrangement for a gas turbine component.  United States: N. p., 2015. 
        Web.

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                    Lee, Ching-Pang, & Heneveld, Benjamin E. Cooling arrangement for a gas turbine component.  United States.

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                    Lee, Ching-Pang, and Heneveld, Benjamin E. Tue .  
        "Cooling arrangement for a gas turbine component".  United States.  https://www.osti.gov/servlets/purl/1169639.

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@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         = {Tue Feb 10 00:00:00 EST 2015},

  month        = {Tue Feb 10 00:00:00 EST 2015}

}

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Similar Records

Title: Cooling arrangement for a gas turbine component

Abstract

Citation Formats

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

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
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Microcircuit cooling for blades
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Turbine blade cooling system having multiple serpentine trailing edge cooling channels
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Airfoil trailing edge cooling
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Airfoil with supplemental cooling channel adjacent leading edge
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Turbine airfoil cooling system with bifurcated and recessed trailing edge exhaust channels
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Thin turbine rotor blade with sinusoidal flow cooling channels
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Film-cooling augmentation device and turbine airfoil incorporating the same
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