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Title: Integrated axial and tangential serpentine cooling circuit in a turbine airfoil

Abstract

A continuous serpentine cooling circuit forming a progression of radial passages (44, 45, 46, 47A, 48A) between pressure and suction side walls (52, 54) in a MID region of a turbine airfoil (24). The circuit progresses first axially, then tangentially, ending in a last radial passage (48A) adjacent to the suction side (54) and not adjacent to the pressure side (52). The passages of the axial progression (44, 45, 46) may be adjacent to both the pressure and suction side walls of the airfoil. The next to last radial passage (47A) may be adjacent to the pressure side wall and not adjacent to the suction side wall. The last two radial passages (47A, 48A) may be longer along the pressure and suction side walls respectively than they are in a width direction, providing increased direct cooling surface area on the interiors of these hot walls.

Inventors:
; ; ; ;
Issue Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1179033
Patent Number(s):
9022736
Application Number:
13/027,333
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
Resource Relation:
Patent File Date: 2011 Feb 15
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING

Citation Formats

Lee, Ching-Pang, Jiang, Nan, Marra, John J, Rudolph, Ronald J, and Dalton, John P. Integrated axial and tangential serpentine cooling circuit in a turbine airfoil. United States: N. p., 2015. Web.
Lee, Ching-Pang, Jiang, Nan, Marra, John J, Rudolph, Ronald J, & Dalton, John P. Integrated axial and tangential serpentine cooling circuit in a turbine airfoil. United States.
Lee, Ching-Pang, Jiang, Nan, Marra, John J, Rudolph, Ronald J, and Dalton, John P. Tue . "Integrated axial and tangential serpentine cooling circuit in a turbine airfoil". United States. https://www.osti.gov/servlets/purl/1179033.
@article{osti_1179033,
title = {Integrated axial and tangential serpentine cooling circuit in a turbine airfoil},
author = {Lee, Ching-Pang and Jiang, Nan and Marra, John J and Rudolph, Ronald J and Dalton, John P},
abstractNote = {A continuous serpentine cooling circuit forming a progression of radial passages (44, 45, 46, 47A, 48A) between pressure and suction side walls (52, 54) in a MID region of a turbine airfoil (24). The circuit progresses first axially, then tangentially, ending in a last radial passage (48A) adjacent to the suction side (54) and not adjacent to the pressure side (52). The passages of the axial progression (44, 45, 46) may be adjacent to both the pressure and suction side walls of the airfoil. The next to last radial passage (47A) may be adjacent to the pressure side wall and not adjacent to the suction side wall. The last two radial passages (47A, 48A) may be longer along the pressure and suction side walls respectively than they are in a width direction, providing increased direct cooling surface area on the interiors of these hot walls.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {5}
}