Casting core for a cooling arrangement for a gas turbine component

Lee, Ching-Pang; Heneveld, Benjamin E

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A - human necessities
A01 - agriculture
A21 - baking
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A24 - tobacco
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A42 - headwear
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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
B05 - spraying or atomising in general
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B62 - land vehicles for travelling otherwise than on rails
B63 - ships or other waterborne vessels
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Title: Casting core for a cooling arrangement for a gas turbine component

Abstract

A ceramic casting core, including: a plurality of rows (162, 166, 168) of gaps (164), each gap (164) defining an airfoil shape; interstitial core material (172) that defines and separates adjacent gaps (164) in each row (162, 166, 168); and connecting core material (178) that connects adjacent rows (170, 174, 176) of interstitial core material (172). Ends of interstitial core material (172) in one row (170, 174, 176) align with ends of interstitial core material (172) in an adjacent row (170, 174, 176) to form a plurality of continuous and serpentine shaped structures each including interstitial core material (172) from at least two adjacent rows (170, 174, 176) and connecting core material (178).

Inventors:: Lee, Ching-Pang; Heneveld, Benjamin E

Issue Date:: Tue Jan 20 00:00:00 EST 2015

Research Org.:: Siemens Aktiengesellschaft, Munchen, DE (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1167465

Patent Number(s):: 8936067

Application Number:: 13/658,045

Assignee:: Siemens Aktiengesellschaft (Munchen, DE)

Patent Classifications (CPCs):: B - PERFORMING OPERATIONS B22 - CASTING B22C - FOUNDRY MOULDING

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

Show more

B - PERFORMING OPERATIONS B22 - CASTING B22C - FOUNDRY MOULDING
B22C9/10 - Cores

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/186 - {Film cooling
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
F05D2230/21 - by casting
F05D2230/211 - by precision casting, e.g. microfusing or investment casting

Show less

DOE Contract Number:: SC0001359

Resource Type:: Patent

Country of Publication:: United States

Language:: English

Subject:: 42 ENGINEERING

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                    Lee, Ching-Pang, and Heneveld, Benjamin E. Casting core for a cooling arrangement for a gas turbine component.  United States: N. p., 2015. 
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                    Lee, Ching-Pang, & Heneveld, Benjamin E. Casting core for a cooling arrangement for a gas turbine component.  United States.

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                    Lee, Ching-Pang, and Heneveld, Benjamin E. Tue .  
        "Casting core for a cooling arrangement for a gas turbine component".  United States.  https://www.osti.gov/servlets/purl/1167465.

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@article{osti_1167465,

  title        = {Casting core for a cooling arrangement for a gas turbine component},

  author       = {Lee, Ching-Pang and Heneveld, Benjamin E},

  abstractNote = {A ceramic casting core, including: a plurality of rows (162, 166, 168) of gaps (164), each gap (164) defining an airfoil shape; interstitial core material (172) that defines and separates adjacent gaps (164) in each row (162, 166, 168); and connecting core material (178) that connects adjacent rows (170, 174, 176) of interstitial core material (172). Ends of interstitial core material (172) in one row (170, 174, 176) align with ends of interstitial core material (172) in an adjacent row (170, 174, 176) to form a plurality of continuous and serpentine shaped structures each including interstitial core material (172) from at least two adjacent rows (170, 174, 176) and connecting core material (178).},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {Tue Jan 20 00:00:00 EST 2015},

  month        = {Tue Jan 20 00:00:00 EST 2015}

}

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Hess, W. Graig
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patent, July 2001

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

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Triple circuit turbine blade
patent, January 2006

Lee, Ching-Pang; Brassfield, Steven Robert; Prakash, Chander
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patent, June 2007

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Similar Records

Title: Casting core for a 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

Investment casting using core with integral wall thickness control means patent, March 1994

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

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

Triple circuit turbine blade patent, January 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 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

High effectiveness cooled turbine blade patent, December 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 blade with multiple metering trailing edge cooling holes patent, August 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

Turbine airfoil ceramic core with strain relief slot patent, September 2012

Crossflow Turbine Airfoil patent-application, December 2009

Radial wafer airfoil construction
patent, May 1980

Cooled turbine blade
patent, August 1987

Turbine blade trailing edge cooling construction
patent, September 1993

Investment casting using core with integral wall thickness control means
patent, March 1994

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

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

Triple circuit turbine blade
patent, January 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 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

High effectiveness cooled turbine blade
patent, December 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 blade with multiple metering trailing edge cooling holes
patent, August 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

Turbine airfoil ceramic core with strain relief slot
patent, September 2012

Crossflow Turbine Airfoil
patent-application, December 2009