发明名称 Gas turbine components which include chevron film cooling holes, and related processes
摘要 <p>An article is described, including an inner surface (24) which can be exposed to a first fluid; an inlet (30); and an outer surface (26) spaced from the inner surface, which can be exposed to a hotter second fluid. The article further includes at least one row or other pattern of passage holes (28). Each passage hole includes an inlet bore (34) extending through the substrate (20) from the inlet at the inner surface to a passage hole-exit proximate to the outer surface (26), with the inlet bore terminating in a chevron outlet (32) adjacent the hole-exit. The chevron outlet includes a pair of wing troughs (42,44) having a common surface region (46) between them. The common surface region includes a valley (48) which is adjacent the hole-exit; and a plateau (50) adjacent the valley. The article can be an airfoil. Related methods for preparing the passage holes are also described.</p>
申请公布号 EP2390465(A2) 申请公布日期 2011.11.30
申请号 EP20110159625 申请日期 2011.03.24
申请人 GENERAL ELECTRIC COMPANY 发明人 BUNKER, RONALD SCOTT;LACY, BENJAMIN PAUL
分类号 F01D5/18 主分类号 F01D5/18
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