| 摘要 |
<p>A gas turbine engine component (24) has an airfoil that extends from a leading edge (30) to a trailing edge (32), and has a suction side (102) and a pressure side. There are cooling passages extending from a root of the airfoil toward a tip of the airfoil. The cooling passages include a straight passage (34) extending from the root toward the tip and adjacent the leading edge (30). A serpentine passage (36) has at least three connected paths (38, 42, 44) and is spaced from the straight passage (34) toward the trailing edge (32). A cooling circuit (54, 60, 64) is provided between the pressure wall (50) and each of the three serpentine paths (38, 42, 44), and the straight path (34). A cooling circuit (70) is provided between the suction wall (102) and the straight passage (34). There is no cooling between at least a downstream one (44) of the at least three paths of the serpentine passage (36) and the suction wall (102).
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