Turbine airfoil with controlled area cooling arrangement
Abstract
A gas turbine airfoil includes a serpentine cooling path with a plurality of channels fluidly interconnected by a plurality of turns for cooling the airfoil wall material. A splitter component is positioned within at least one of the channels to bifurcate the channel into a pressure-side channel passing in between the outer wall and the inner wall of the pressure side and a suction-side channel passing in between the outer wall and the inner wall of the suction side longitudinally downstream of an intermediate height. The cross-sectional area of the pressure-side channel and suction-side channel are thereby controlled in spite of an increasing cross-sectional area of the airfoil along its longitudinal length, ensuring a sufficiently high mach number to provide a desired degree of cooling throughout the entire length of the airfoil.
- Inventors:
- Issue Date:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL, (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1176251
- Patent Number(s):
- 7704048
- Application Number:
- 11/639,959
- 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
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2006 Dec 15
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Liang, George. Turbine airfoil with controlled area cooling arrangement. United States: N. p., 2010.
Web.
Liang, George. Turbine airfoil with controlled area cooling arrangement. United States.
Liang, George. Tue .
"Turbine airfoil with controlled area cooling arrangement". United States. https://www.osti.gov/servlets/purl/1176251.
@article{osti_1176251,
title = {Turbine airfoil with controlled area cooling arrangement},
author = {Liang, George},
abstractNote = {A gas turbine airfoil includes a serpentine cooling path with a plurality of channels fluidly interconnected by a plurality of turns for cooling the airfoil wall material. A splitter component is positioned within at least one of the channels to bifurcate the channel into a pressure-side channel passing in between the outer wall and the inner wall of the pressure side and a suction-side channel passing in between the outer wall and the inner wall of the suction side longitudinally downstream of an intermediate height. The cross-sectional area of the pressure-side channel and suction-side channel are thereby controlled in spite of an increasing cross-sectional area of the airfoil along its longitudinal length, ensuring a sufficiently high mach number to provide a desired degree of cooling throughout the entire length of the airfoil.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Apr 27 00:00:00 EDT 2010},
month = {Tue Apr 27 00:00:00 EDT 2010}
}