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Method of joining a vane cavity insert to a nozzle segment of a gas turbine

United States Patent

September 24, 2002
View the Complete Patent at the US Patent & Trademark Office
An insert containing apertures for impingement cooling a nozzle vane of a nozzle segment in a gas turbine is inserted into one end of the vane. The leading end of the insert is positioned slightly past a rib adjacent the opposite end of the vane through which the insert is inserted. The end of the insert is formed or swaged into conformance with the inner margin of the rib. The insert is then brazed or welded to the rib.
Burdgick; Steven Sebastian (Schenectady, NY)
General Electric Company (Schenectady, NY)
09/ 547,933
April 11, 2000
This invention was made with Government support under Contract No. DE-FC21-95MC311876 awarded by the Department of Energy. The Government has certain rights in this invention.