Turbine airfoil with outer wall thickness indicators
Abstract
A turbine airfoil usable in a turbine engine and including a depth indicator for determining outer wall blade thickness. The airfoil may include an outer wall having a plurality of grooves in the outer surface of the outer wall. The grooves may have a depth that represents a desired outer surface and wall thickness of the outer wall. The material forming an outer surface of the outer wall may be removed to be flush with an innermost point in each groove, thereby reducing the wall thickness and increasing efficiency. The plurality of grooves may be positioned in a radially outer region of the airfoil proximate to the tip.
- Inventors:
- Publication Date:
- Research Org.:
- Siemens Energy, Inc. (Orlando, FL)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1089419
- Patent Number(s):
- 8,500,411
- Application Number:
- 12/794,972
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Marra, John J, James, Allister W, and Merrill, Gary B. Turbine airfoil with outer wall thickness indicators. United States: N. p., 2013.
Web.
Marra, John J, James, Allister W, & Merrill, Gary B. Turbine airfoil with outer wall thickness indicators. United States.
Marra, John J, James, Allister W, and Merrill, Gary B. 2013.
"Turbine airfoil with outer wall thickness indicators". United States. https://www.osti.gov/servlets/purl/1089419.
@article{osti_1089419,
title = {Turbine airfoil with outer wall thickness indicators},
author = {Marra, John J and James, Allister W and Merrill, Gary B},
abstractNote = {A turbine airfoil usable in a turbine engine and including a depth indicator for determining outer wall blade thickness. The airfoil may include an outer wall having a plurality of grooves in the outer surface of the outer wall. The grooves may have a depth that represents a desired outer surface and wall thickness of the outer wall. The material forming an outer surface of the outer wall may be removed to be flush with an innermost point in each groove, thereby reducing the wall thickness and increasing efficiency. The plurality of grooves may be positioned in a radially outer region of the airfoil proximate to the tip.},
doi = {},
url = {https://www.osti.gov/biblio/1089419},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Aug 06 00:00:00 EDT 2013},
month = {Tue Aug 06 00:00:00 EDT 2013}
}
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Works referenced in this record:
Blade tip cooling groove
patent, January 2012
- Paauwe, Corneil S.; Spangler, Brandon W.
- US Patent Document 8,092,179
Near wall cooling for a highly tapered turbine blade
patent, March 2011
- Liang, George
- US Patent Document 7,901,182
Hollow turbine blade
patent, December 2010
- Ahmad, Fathi; Dankert, Michael
- US Patent Document 7,845,905