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Title: Four-wall turbine airfoil with thermal strain control for reduced cycle fatigue

Abstract

A turbine airfoil (20B) with a thermal expansion control mechanism that increases the airfoil camber (60, 61) under operational heating. The airfoil has four-wall geometry, including pressure side outer and inner walls (26, 28B), and suction side outer and inner walls (32, 34B). It has near-wall cooling channels (31F, 31A, 33F, 33A) between the outer and inner walls. A cooling fluid flow pattern (50C, 50W, 50H) in the airfoil causes the pressure side inner wall (28B) to increase in curvature under operational heating. The pressure side inner wall (28B) is thicker than walls (26, 34B) that oppose it in camber deformation, so it dominates them in collaboration with the suction side outer wall (32), and the airfoil camber increases. This reduces and relocates a maximum stress area (47) from the suction side outer wall (32) to the suction side inner wall (34B, 72) and the pressure side outer wall (26).

Inventors:
Publication Date:
Research Org.:
Siemens Energy, Inc. (Orlando, FL)
Sponsoring Org.:
USDOE
OSTI Identifier:
1093557
Patent Number(s):
8,535,004
Application Number:
12/732,386
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

Cambell, Christian X. Four-wall turbine airfoil with thermal strain control for reduced cycle fatigue. United States: N. p., 2013. Web.
Cambell, Christian X. Four-wall turbine airfoil with thermal strain control for reduced cycle fatigue. United States.
Cambell, Christian X. Tue . "Four-wall turbine airfoil with thermal strain control for reduced cycle fatigue". United States. https://www.osti.gov/servlets/purl/1093557.
@article{osti_1093557,
title = {Four-wall turbine airfoil with thermal strain control for reduced cycle fatigue},
author = {Cambell, Christian X},
abstractNote = {A turbine airfoil (20B) with a thermal expansion control mechanism that increases the airfoil camber (60, 61) under operational heating. The airfoil has four-wall geometry, including pressure side outer and inner walls (26, 28B), and suction side outer and inner walls (32, 34B). It has near-wall cooling channels (31F, 31A, 33F, 33A) between the outer and inner walls. A cooling fluid flow pattern (50C, 50W, 50H) in the airfoil causes the pressure side inner wall (28B) to increase in curvature under operational heating. The pressure side inner wall (28B) is thicker than walls (26, 34B) that oppose it in camber deformation, so it dominates them in collaboration with the suction side outer wall (32), and the airfoil camber increases. This reduces and relocates a maximum stress area (47) from the suction side outer wall (32) to the suction side inner wall (34B, 72) and the pressure side outer wall (26).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2013},
month = {9}
}

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