Skip to Content
Find More Like This
Return to Search

Partially turbulated trailing edge cooling passages for gas turbine nozzles

United States Patent

February 20, 2001
View the Complete Patent at the US Patent & Trademark Office
A plurality of passages are spaced one from the other along the length of a trailing edge of a nozzle vane in a gas turbine. The passages lie in communication with a cavity in the vane for flowing cooling air from the cavity through the passages through the tip of the trailing edge into the hot gas path. Each passage is partially turbulated and includes ribs in an aft portion thereof to provide enhanced cooling effects adjacent the tip of the trailing edge. The major portions of the passages are smooth bore. By this arrangement, reduced temperature gradients across the trailing edge metal are provided. Additionally, the inlets to each of the passages have a restriction whereby a reduced magnitude of compressor bleed discharge air is utilized for trailing edge cooling purposes.
Thatcher; Jonathan Carl (Schenectady, NY), Burdgick; Steven Sebastian (Schenectady, NY)
General Electric Co. (Schenectady, NY)
09/ 312,427
May 14, 1999
This invention was made with Government support under Contract No. DE-FC21-95MC31176 awarded by the Department of Energy. The Government has certain rights in this invention.