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Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements

United States Patent

9,039,371
May 26, 2015
View the Complete Patent at the US Patent & Trademark Office
A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.
Lee; Ching-Pang (Cincinnati, OH), Heneveld; Benjamin E. (Newmarket, NH), Brown; Glenn E. (West Palm Beach, FL), Klinger; Jill (Charlottesville, VA)
SIEMENS AKTIENGESELLSCHAFT (Munchen, DE), MIKRO SYSTEMS, INC. (Charlottesville, VA)
14/ 068,070
20150118034
October 31, 2013
STATEMENT REGARDING FEDERALLY SPONSORED DEVELOPMENT Development for this invention was supported in part by Contract No. SC0001359 awarded by the United States Department of Energy. Accordingly, the United States Government may have certain rights in this invention.