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Sequential cooling insert for turbine stator vane

United States Patent

9,611,745
April 4, 2017
View the Complete Patent at the US Patent & Trademark Office
A sequential flow cooling insert for a turbine stator vane of a small gas turbine engine, where the impingement cooling insert is formed as a single piece from a metal additive manufacturing process such as 3D metal printing, and where the insert includes a plurality of rows of radial extending impingement cooling air holes alternating with rows of radial extending return air holes on a pressure side wall, and where the insert includes a plurality of rows of chordwise extending second impingement cooling air holes on a suction side wall. The insert includes alternating rows of radial extending cooling air supply channels and return air channels that form a series of impingement cooling on the pressure side followed by the suction side of the insert.
Jones; Russel B (North Palm Beach, FL)
Florida Turbine Technologies, Inc. (Jupitor, FL)
14/ 511,211
October 10, 2014
FEDERAL RESEARCH STATEMENT This invention was made with Government support under contract number DE-FE-0006696 awarded by Department of Energy. The Government has certain rights in the invention.