Skip to Content
Find More Like This
Return to Search

Cooling arrangement for a gas turbine component

United States Patent

February 10, 2015
View the Complete Patent at the US Patent & Trademark Office
A cooling arrangement (82) for a gas turbine engine component, the cooling arrangement (82) having a plurality of rows (92, 94, 96) of airfoils (98), wherein adjacent airfoils (98) within a row (92, 94, 96) define segments (110, 130, 140) of cooling channels (90), and wherein outlets (114, 134) of the segments (110, 130) in one row (92, 94) align aerodynamically with inlets (132, 142) of segments (130, 140) in an adjacent row (94, 96) to define continuous cooling channels (90) with non continuous walls (116, 120), each cooling channel (90) comprising a serpentine shape.
Lee; Ching-Pang (Cincinnati, OH), Heneveld; Benjamin E. (Newmarket, NH)
Siemens Aktiengesellschaft (Munich, DE), Mikro Systems, Inc. (Charlottesville, VA)
13/ 657,923
October 23, 2012
STATEMENT REGARDING FEDERALLY SPONSORED DEVELOPMENT Development for this invention was supported in part by contract Award Number DE-SC0001359 awarded by the United States Department of Energy Office of Science (SBIR) to Mikro Systems, Inc. of Charlottesville, Va. Accordingly, the United States Government may have certain rights in this invention.