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Title: Near-wall serpentine cooled turbine airfoil

Abstract

A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters (56) an end of the airfoil, flows into a span-wise channel (54A), then flows forward (54B) over the inner surface of the pressure side wall, then turns behind the leading edge (26), and flows back along a forward part of the suction side wall, then follows a loop (54E) forward and back around an inner wall (52), then flows along an intermediate part of the suction side wall, then flows into an aft channel (54G) between the pressure and suction side walls, then exits the trailing edge (28). This provides cooling matched to the heating topography of the airfoil, minimizes differential thermal expansion, revives the coolant, and minimizes the flow volume needed.

Inventors:
Publication Date:
Research Org.:
Siemens Energy, Inc. (Orlando, FL)
Sponsoring Org.:
USDOE
OSTI Identifier:
1093556
Patent Number(s):
8,535,006
Application Number:
12/836,060
Assignee:
Siemens Energy, Inc. (Orlando, FL) NETL
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Lee, Ching-Pang. Near-wall serpentine cooled turbine airfoil. United States: N. p., 2013. Web.
Lee, Ching-Pang. Near-wall serpentine cooled turbine airfoil. United States.
Lee, Ching-Pang. Tue . "Near-wall serpentine cooled turbine airfoil". United States. https://www.osti.gov/servlets/purl/1093556.
@article{osti_1093556,
title = {Near-wall serpentine cooled turbine airfoil},
author = {Lee, Ching-Pang},
abstractNote = {A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters (56) an end of the airfoil, flows into a span-wise channel (54A), then flows forward (54B) over the inner surface of the pressure side wall, then turns behind the leading edge (26), and flows back along a forward part of the suction side wall, then follows a loop (54E) forward and back around an inner wall (52), then flows along an intermediate part of the suction side wall, then flows into an aft channel (54G) between the pressure and suction side walls, then exits the trailing edge (28). This provides cooling matched to the heating topography of the airfoil, minimizes differential thermal expansion, revives the coolant, and minimizes the flow volume needed.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Sep 17 00:00:00 EDT 2013},
month = {Tue Sep 17 00:00:00 EDT 2013}
}

Patent:

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