Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements
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United States of America Patent
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May 26, 2015
Grant Date -
Apr 30, 2015
app pub date -
Oct 31, 2013
filing date -
Oct 31, 2013
priority date (Note) -
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status (Latency Note)
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Abstract
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.
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