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Title: Turbine airfoil with controlled area cooling arrangement

Abstract

A gas turbine airfoil (10) includes a serpentine cooling path (32) with a plurality of channels (34,42,44) fluidly interconnected by a plurality of turns (38,40) for cooling the airfoil wall material. A splitter component (50) is positioned within at least one of the channels to bifurcate the channel into a pressure-side channel (46) passing in between the outer wall (28) and the inner wall (30) of the pressure side (24) and a suction-side channel (48) passing in between the outer wall (28) and the inner wall (30) of the suction side (26) longitudinally downstream of an intermediate height (52). The cross-sectional area of the pressure-side channel (46) and suction-side channel (48) 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.
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
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 (10) includes a serpentine cooling path (32) with a plurality of channels (34,42,44) fluidly interconnected by a plurality of turns (38,40) for cooling the airfoil wall material. A splitter component (50) is positioned within at least one of the channels to bifurcate the channel into a pressure-side channel (46) passing in between the outer wall (28) and the inner wall (30) of the pressure side (24) and a suction-side channel (48) passing in between the outer wall (28) and the inner wall (30) of the suction side (26) longitudinally downstream of an intermediate height (52). The cross-sectional area of the pressure-side channel (46) and suction-side channel (48) 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 = {2010},
month = {4}
}

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