Cooling system having reduced mass pin fins for components in a gas turbine engine
Abstract
A cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil.
- Inventors:
- Issue Date:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL, USA
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1126792
- Patent Number(s):
- 8668453
- Application Number:
- 13/027,323
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- 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
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Lee, Ching-Pang, Jiang, Nan, and Marra, John J. Cooling system having reduced mass pin fins for components in a gas turbine engine. United States: N. p., 2014.
Web.
Lee, Ching-Pang, Jiang, Nan, & Marra, John J. Cooling system having reduced mass pin fins for components in a gas turbine engine. United States.
Lee, Ching-Pang, Jiang, Nan, and Marra, John J. Tue .
"Cooling system having reduced mass pin fins for components in a gas turbine engine". United States. https://www.osti.gov/servlets/purl/1126792.
@article{osti_1126792,
title = {Cooling system having reduced mass pin fins for components in a gas turbine engine},
author = {Lee, Ching-Pang and Jiang, Nan and Marra, John J},
abstractNote = {A cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2014},
month = {3}
}
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Works referenced in this record:
Vane for a gas turbine engine having means for impingement cooling thereof
patent, August 1978
- Dodd, Alec G.
- US Patent Document 4,105,364
Curved turbulator configuration for airfoils and method and electrode for machining the configuration
patent, April 2003
- Lee, Ching-Pang; Wei, Bin; Johnson, Robert Alan
- US Patent Document 6,554,571