Turbine airfoil with ambient cooling system
Abstract
A turbine airfoil usable in a turbine engine and having at least one ambient air cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels configured to receive ambient air at about atmospheric pressure. The ambient air cooling system may have a tip static pressure to ambient pressure ratio of at least 0.5, and in at least one embodiment, may include a tip static pressure to ambient pressure ratio of between about 0.5 and about 3.0. The cooling system may also be configured such that an under root slot chamber in the root is large to minimize supply air velocity. One or more cooling channels of the ambient air cooling system may terminate at an outlet at the tip such that the outlet is aligned with inner surfaces forming the at least one cooling channel in the airfoil to facilitate high mass flow.
- Inventors:
- Publication Date:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1255970
- Patent Number(s):
- 9,359,902
- Application Number:
- 13/930,479
- Assignee:
- Siemens Energy, Inc. (Orlando, FL
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2013 Jun 28
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Campbell, Jr, Christian X., Marra, John J., and Marsh, Jan H. Turbine airfoil with ambient cooling system. United States: N. p., 2016.
Web.
Campbell, Jr, Christian X., Marra, John J., & Marsh, Jan H. Turbine airfoil with ambient cooling system. United States.
Campbell, Jr, Christian X., Marra, John J., and Marsh, Jan H. 2016.
"Turbine airfoil with ambient cooling system". United States. https://www.osti.gov/servlets/purl/1255970.
@article{osti_1255970,
title = {Turbine airfoil with ambient cooling system},
author = {Campbell, Jr, Christian X. and Marra, John J. and Marsh, Jan H.},
abstractNote = {A turbine airfoil usable in a turbine engine and having at least one ambient air cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels configured to receive ambient air at about atmospheric pressure. The ambient air cooling system may have a tip static pressure to ambient pressure ratio of at least 0.5, and in at least one embodiment, may include a tip static pressure to ambient pressure ratio of between about 0.5 and about 3.0. The cooling system may also be configured such that an under root slot chamber in the root is large to minimize supply air velocity. One or more cooling channels of the ambient air cooling system may terminate at an outlet at the tip such that the outlet is aligned with inner surfaces forming the at least one cooling channel in the airfoil to facilitate high mass flow.},
doi = {},
url = {https://www.osti.gov/biblio/1255970},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Jun 07 00:00:00 EDT 2016},
month = {Tue Jun 07 00:00:00 EDT 2016}
}
Works referenced in this record:
Hollow cooled vane or blade for a gas turbine engine
patent, January 1976
- Redman, Robert Frederick; Sharpe, Michael
- US Patent Document 3,930,748
Cooling system for a gas turbine engine
patent, September 1978
- Lee, Richard M.; Szema, Li-Chieh
- US Patent Document 4,113,406
Air cooled turbine vanes
patent, May 1979
- Leogrande, John A.; Levine, Richard
- US Patent Document 4,153,386
Airfoil with nested cooling channels
patent, June 1988
- Levengood, James L.; Auxier, Thomas A.
- US Patent Document 4,753,575
Cooled turbine vane
patent, June 1990
- North, William E.; Entenmann, David T.; Donlan, John P.
- US Patent Document 4,930,980
Turbine engine having combustor air precooler
patent, May 1991
- Speer, Stephen R.
- US Patent Document 5,012,646
Air cycle machine with heat isolation having back-to-back turbine and compressor rotors
patent, October 1993
- Merritt, Brent J.; Dziorny, Paul J.
- US Patent Document 5,249,934
Turbine blade composite cooling circuit
patent, February 1995
- Thomas, Jr,, Theodore T.; Lee, Ching-Pang
- US Patent Document 5,387,085
Self bleeding rotor blade
patent, January 1996
- Wadia, Aspi Rustom; Mielke, Mark Joseph
- US Patent Document 5,480,284
Cooled airfoils for a gas turbine engine
patent, December 1997
- Moore, Robert P.
- US Patent Document 5,702,232
Cooled blades for a gas turbine engine
patent, February 1998
- Sellers, Robert; Soechting, Friedrich; Huber, Frank W.
- US Patent Document 5,720,431
Turbine blade with enhanced cooling and profile optimization
patent, November 1999
- Barry, Vincent Anthony; Gregory, Brent Allan; Abuaf, Nesim
- US Patent Document 5,980,209
Reduction of turbomachinery noise
patent, December 1999
- Waitz, Ian A.; Brookfield, John M.; Sell, Julian
- US Patent Document 6,004,095
Methods and apparatus for supplying cooling air to turbine engines
patent, June 2003
- Coffinberry, George A.
- US Patent Document 6,578,362
Turbine blade airfoil
patent, August 2004
- Parker, David; Taylor, Jeffrey S.; Johnston, Christopher
- US Patent Document 6,769,878
Turbine blade having a vortex forming cooling system for a trailing edge
patent, August 2005
- Liang, George
- US Patent Document 6,932,573
Rotor blade system with reduced blade-vortex interaction noise
patent, September 2005
- Leishman, John G.; Han, Yong Oun
- US Patent Document 6,948,906
Dust resistant platform blade
patent, July 2007
- Lee, Ching-Pang; Zatorski, Darek Tomasz; Norton, Brian
- US Patent Document 7,244,101
Parallel serpentine cooled blade
patent, November 2007
- Lee, Ching-Pang; Wadia, Aspi Rustom; Brassfield, Steven Robert
- US Patent Document 7,296,973
Turbine blade cooling system with bifurcated mid-chord cooling chamber
patent, August 2008
- Liang, George
- US Patent Document 7,413,407
Cooling arrangement
patent, March 2009
- Kopmels, Michiel; Jago, Michael; Sadler, Keith
- US Patent Document 7,507,071
Multiple cooling schemes for turbine blade outer air seal
patent, November 2009
- Lutjen, Paul M.; Grogg, Gary L.; Joe, Christopher R.
- US Patent Document 7,621,719
Turbine last stage blade with forced vortex driven cooling air
patent, March 2010
- Brostmeyer, Joseph D.; Wilson, Jr., Jack W.
- US Patent Document 7,677,048
Trailing edge cooling for turbine blade airfoil
patent, January 2012
- Liang, George
- US Patent Document 8,096,770
Turbine blade with cooling air inlet holes
patent, January 2014
- Liang, George
- US Patent Document 8,622,702
Cooled aerofoil for a gas turbine engine
patent-application, October 2010
- Tibbott, Ian
- US Patent Application 12/706386; 20100254801
Ambient Air Cooling Arrangement Having A Pre-Swirler For Gas Turbine Engine Blade Cooling
patent-application, June 2013
- Lee, Ching-Pang; Tham, Kok-Mun; Schroeder, Eric
- US Patent Application 13/766909; 20130156579