| 摘要 |
A gas turbine engine component (20) has a leading edge (30) and a trailing edge (32) and a pressure side (36) and a suction side (34). The pressure side (36) and suction side (34) extend between the leading edge (30) and trailing edge (32). One or more cooling passageways extend through the airfoil (22) and comprise a trunk (70) extending from an inlet (50). At the inlet (50), there is an additional passageway (762,74) adjacent the trunk (70) and having at least one edge (134,136) recessed relative to the trunk (70).
Also claimed is 1. a pattern (140) for casting a component (20) having an airfoil (22), the pattern (140) comprising:
a pattern material (144) having an airfoil portion (146); and
a casting core combination (142) at least partially embedded in the pattern material (144) and comprising:
a metallic casting core (162,164) having opposite first and second faces; and
at least one additional casting core (160), the metallic casting core (162,164) and at least one additional casting core (160) extending spanwise into the airfoil (146) of the pattern material (144), wherein:
at least in a portion of the pattern material (144) outside the airfoil (146) of the pattern material (144), an edge portion (184,186) of the metallic casting core (162,164) is recessed relative to the cross-section of an adjacent portion of the at least one additional casting core (160). |
