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:
- Publication Date:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1179033
- Patent Number(s):
- 9,022,736
- Application Number:
- 13/027,333
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- 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. 2015.
"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 = {},
url = {https://www.osti.gov/biblio/1179033},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue May 05 00:00:00 EDT 2015},
month = {Tue May 05 00:00:00 EDT 2015}
}
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