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

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.
Authors:
; ; ; ;
Publication Date:
OSTI Identifier:
1179033
Report Number(s):
9,022,736
13/027,333
DOE Contract Number:
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2011 Feb 15
Research Org:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING