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Title: Turbine airfoil having near-wall cooling insert

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.
Issue Date:
OSTI Identifier:
Siemens Energy, Inc. NETL
Patent Number(s):
Application Number:
Contract Number:
Resource Relation:
Patent File Date: 2016 Feb 26
Research Org:
Siemens Energy, Inc. Orlando, FL (United States)
Sponsoring Org:
Country of Publication:
United States

Other works cited in this record:

Fluid cooled turbine rotor blade
patent, September 1975

Turbine airfoil with near-wall impingement and vortex cooling
patent, March 2009

Multiple piece turbine airfoil
patent, November 2010

Air cooled turbine airfoil with sequential impingement cooling
patent, May 2012

Spring loaded compliant seal for high temperature use
patent, October 2013

Turbine vane with near wall multiple impingement cooling
patent, December 2013

Flow control insert in cooling passage for turbine vane
patent, October 2014

Turbine Airfoil Vane With An Impingement Insert Having A Plurality Of Impingement Nozzles
patent-application, April 2014

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