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Title: Turbine airfoil having near-wall cooling insert

Abstract

A turbine airfoil is provided with at least one insert positioned in a cavity in an airfoil interior. The insert extends along a span-wise extent of the turbine airfoil and includes first and second opposite faces. A first near-wall cooling channel is defined between the first face and a pressure sidewall of an airfoil outer wall. A second near-wall cooling channel is defined between the second face and a suction sidewall of the airfoil outer wall. The insert is configured to occupy an inactive volume in the airfoil interior so as to displace a coolant flow in the cavity toward the first and second near-wall cooling channels. A locating feature engages the insert with the outer wall for supporting the insert in position. The locating feature is configured to control flow of the coolant through the first or second near-wall cooling channel.

Inventors:
;
Publication Date:
Research Org.:
Siemens Energy, Inc. Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1390172
Patent Number(s):
9,759,073
Application Number:
15/055,003
Assignee:
Siemens Energy, Inc. NETL
DOE Contract Number:
FE0023955
Resource Type:
Patent
Resource Relation:
Patent File Date: 2016 Feb 26
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Martin, Jr., Nicholas F., and Wiebe, David J. Turbine airfoil having near-wall cooling insert. United States: N. p., 2017. Web.
Martin, Jr., Nicholas F., & Wiebe, David J. Turbine airfoil having near-wall cooling insert. United States.
Martin, Jr., Nicholas F., and Wiebe, David J. Tue . "Turbine airfoil having near-wall cooling insert". United States. doi:. https://www.osti.gov/servlets/purl/1390172.
@article{osti_1390172,
title = {Turbine airfoil having near-wall cooling insert},
author = {Martin, Jr., Nicholas F. and Wiebe, David J.},
abstractNote = {A turbine airfoil is provided with at least one insert positioned in a cavity in an airfoil interior. The insert extends along a span-wise extent of the turbine airfoil and includes first and second opposite faces. A first near-wall cooling channel is defined between the first face and a pressure sidewall of an airfoil outer wall. A second near-wall cooling channel is defined between the second face and a suction sidewall of the airfoil outer wall. The insert is configured to occupy an inactive volume in the airfoil interior so as to displace a coolant flow in the cavity toward the first and second near-wall cooling channels. A locating feature engages the insert with the outer wall for supporting the insert in position. The locating feature is configured to control flow of the coolant through the first or second near-wall cooling channel.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Sep 12 00:00:00 EDT 2017},
month = {Tue Sep 12 00:00:00 EDT 2017}
}

Patent:

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