skip to main content

SciTech ConnectSciTech Connect

Title: Near-wall serpentine cooled turbine airfoil

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