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}
}
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Works referenced in this record:
Cooled turbine blade
patent, August 1987
- Clifford, Rodney J.; Charters, Ian J.
- US Patent Document 4,684,322
Turbine blade trailing edge cooling construction
patent, September 1993
- Hall, Kenneth B.; Auxier, Thomas A.
- US Patent Document 5,246,341
Film cooling of turbine airfoil wall using mesh cooling hole arrangement
patent, December 1994
- Lee, Ching-Pang
- US Patent Document 5,370,499
Internally cooled gas turbine vane
patent, February 1997
- Okpara, Nnawuihe; Henry, Chester L.; Bischoff, Michael K.
- US Patent Document 5,601,399
Internal cooling of turbine airfoil wall using mesh cooling hole arrangement
patent, November 1997
- Lee, Ching-Pang
- US Patent Document 5,690,472
Shear jet cooling passages for internally cooled machine elements
patent, January 1998
- Lee, Ching-Pang
- US Patent Document 5,704,763
Apparatus for cooling a gas turbine airfoil and method of making same
patent, May 1998
- Kennedy, Mark
- US Patent Document 5,752,801
Reduction of turbomachinery noise
patent, December 1999
- Waitz, Ian A.; Brookfield, John M.; Sell, Julian
- US Patent Document 6,004,095
Axial serpentine cooled airfoil
patent, August 2000
- Manning, Robert Francis; Acquaviva, Paul J.; Demers, Daniel Edward
- US Patent Document 6,099,252
Method and apparatus for cooling a wall within a gas turbine engine
patent, July 2001
- LaFleur, Ronald S.
- US Patent Document 6,254,334
Article surface with metal wires and method for making
patent, June 2002
- Lee, Ching-Pang; Hasz, Wayne Charles; Abuaf, Nesim
- US Patent Document 6,399,217
Method and apparatus for cooling a wall within a gas turbine engine
patent, June 2002
- Kvasnak, William S.; LaFleur, Ronald S.; Soechting, Friedrich
- US Patent Document 6,402,470
Turbine blade wall section cooled by an impact flow
patent, August 2002
- Anderson, Gordon; Ferber, Jorgen; Hocker, Rainer
- US Patent Document 6,439,846
Article having turbulation and method of providing turbulation on an article
patent, October 2002
- Hasz, Wayne Charles; Johnson, Robert Alan; Lee, Ching-Pang
- US Patent Document 6,468,669
Blade for gas turbines with choke cross section at the trailing edge
patent, November 2002
- Beeck, Alexander; Ferber, Jorgen; Nagler, Christoph
- US Patent Document 6,481,966
Turbine engine component having enhanced heat transfer characteristics and method for forming same
patent, July 2003
- Hasz, Wayne Charles; Abuaf, Nesim; Johnson, Robert Alan
- US Patent Document 6,589,600
Cooled rotor blade with vibration damping device
patent, April 2006
- Gregg, Shawn J.
- US Patent Document 7,033,140
Hot gas path component with mesh and impingement cooling
patent, February 2007
- Bunker, Ronald Scott; Lee, Ching-Pang
- US Patent Document 7,182,576
Drillable super blades
patent, June 2007
- Draper, Samuel David; Kvasnak, William S.
- US Patent Document 7,232,290
Microcircuit cooling for blades
patent, December 2007
- Cunha, Frank J.; Abdel-Messeh, William
- US Patent Document 7,311,498
Turbine blade cooling system having multiple serpentine trailing edge cooling channels
patent, October 2008
- Liang, George
- US Patent Document 7,435,053
Airfoil trailing edge cooling
patent, October 2008
- Albert, Jason Edward; Cunha, Frank J.
- US Patent Document 7,438,527
Airfoil with supplemental cooling channel adjacent leading edge
patent, January 2009
- Cunha, Frank J.; Pietraszkiewicz, Edward F.; Kontrovitz, David M.
- US Patent Document 7,478,994
Turbine airfoil cooling system with bifurcated and recessed trailing edge exhaust channels
patent, June 2009
- Liang, George
- US Patent Document 7,549,844
Component comprising a multiplicity of cooling passages
patent, August 2009
- Walters, Sean; Moss, Daniel P.; Mitchell, Mark T.
- US Patent Document 7,572,103
Turbine airfoil with serpentine trailing edge cooling circuit
patent, March 2010
- Liang, George
- US Patent Document 7,670,113
Thin turbine rotor blade with sinusoidal flow cooling channels
patent, July 2010
- Liang, George
- US Patent Document 7,753,650
Turbine airfoil with spiral trailing edge cooling passages
patent, August 2010
- Liang, George
- US Patent Document 7,785,071
Film-cooling augmentation device and turbine airfoil incorporating the same
patent, November 2011
- Draper, Samuel David
- US Patent Document 8,052,378
Rotor blades for turbine engines
patent, April 2012
- Amaral, Sergio Daniel Marques; Sullivan, Michael Adelbert; Zhang, Xiuzhang James
- US Patent Document 8,157,504
Trailing Edge Cooling System in a Turbine Airfoil Assembly
patent-application, March 2013
- Lee, Ching-Pang
- US Patent Application 13/228567; 20130064681