Wavy flow cooling concept for turbine airfoils
Abstract
An airfoil including an outer wall and a cooling cavity formed therein. The cooling cavity includes a leading edge flow channel located adjacent a leading edge of the airfoil and a trailing edge flow channel located adjacent a trailing edge of the airfoil. Each of the leading edge and trailing edge flow channels define respective first and second flow axes located between pressure and suction sides of the airfoil. A plurality of rib members are located within each of the flow channels, spaced along the flow axes, and alternately extending from opposing sides of the flow channels to define undulating flow paths through the flow channels.
- Inventors:
-
- Palm City, FL
- Issue Date:
- Research Org.:
- Siemens Energy, Inc. (Orlando, FL)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1013611
- Patent Number(s):
- 7785070
- Application Number:
- 11/728,884
- 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
Citation Formats
Liang, George. Wavy flow cooling concept for turbine airfoils. United States: N. p., 2010.
Web.
Liang, George. Wavy flow cooling concept for turbine airfoils. United States.
Liang, George. Tue .
"Wavy flow cooling concept for turbine airfoils". United States. https://www.osti.gov/servlets/purl/1013611.
@article{osti_1013611,
title = {Wavy flow cooling concept for turbine airfoils},
author = {Liang, George},
abstractNote = {An airfoil including an outer wall and a cooling cavity formed therein. The cooling cavity includes a leading edge flow channel located adjacent a leading edge of the airfoil and a trailing edge flow channel located adjacent a trailing edge of the airfoil. Each of the leading edge and trailing edge flow channels define respective first and second flow axes located between pressure and suction sides of the airfoil. A plurality of rib members are located within each of the flow channels, spaced along the flow axes, and alternately extending from opposing sides of the flow channels to define undulating flow paths through the flow channels.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2010},
month = {8}
}
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