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Title: Multi-pass cooling for turbine airfoils

Abstract

An airfoil for a turbine vane of a gas turbine engine. The airfoil includes an outer wall having pressure and suction sides, and a radially extending cooling cavity located between the pressure and suction sides. A plurality of partitions extend radially through the cooling cavity to define a plurality of interconnected cooling channels located at successive chordal locations through the cooling cavity. The cooling channels define a serpentine flow path extending in the chordal direction. Further, the cooling channels include a plurality of interconnected chambers and the chambers define a serpentine path extending in the radial direction within the serpentine path extending in the chordal direction.

Inventors:
 [1]
  1. Palm City, FL
Issue Date:
Research Org.:
Siemens Energy, Inc. (Orlando, FL)
Sponsoring Org.:
USDOE
OSTI Identifier:
1018725
Patent Number(s):
7967567
Application Number:
US Patent Application 11/728,887
Assignee:
Siemens Energy, Inc. (Orlando, FL)
Patent Classifications (CPCs):
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
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. Multi-pass cooling for turbine airfoils. United States: N. p., 2011. Web.
Liang, George. Multi-pass cooling for turbine airfoils. United States.
Liang, George. Tue . "Multi-pass cooling for turbine airfoils". United States. https://www.osti.gov/servlets/purl/1018725.
@article{osti_1018725,
title = {Multi-pass cooling for turbine airfoils},
author = {Liang, George},
abstractNote = {An airfoil for a turbine vane of a gas turbine engine. The airfoil includes an outer wall having pressure and suction sides, and a radially extending cooling cavity located between the pressure and suction sides. A plurality of partitions extend radially through the cooling cavity to define a plurality of interconnected cooling channels located at successive chordal locations through the cooling cavity. The cooling channels define a serpentine flow path extending in the chordal direction. Further, the cooling channels include a plurality of interconnected chambers and the chambers define a serpentine path extending in the radial direction within the serpentine path extending in the chordal direction.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2011},
month = {6}
}

Patent:

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