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HOT GAS PATH COMPONENT FOR TURBINE SYSTEM

United States Patent Application

20140321994
A1
View the Complete Application at the US Patent & Trademark Office
A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell and one or more porous media having an exterior surface and an interior surface and positioned adjacent the shell. The one or more porous media is configured to include varying permeability in one of an axial direction, a radial direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media is positioned adjacent the shell. The one or more porous media is further configured to control one of an axial, a radial, an axial and a radial, an axial and a circumferential, a radial and a circumferential or an axial, a radial and a circumferential flow of a cooling medium flowing therethrough.
Brzek, Brian Gene (Clifton Park, NY), Morgan, Victor John (Greenville, SC), Lacy, Benjamin Paul (Greer, SC)
General Electric Company (Schenectady NY)
13/ 853,556
March 29, 2013
[0001] This disclosure was made with government support under contract number DE-FC26-05NT42643 awarded by the Department of Energy. The government has certain rights in the disclosure.