| 摘要 |
A blade or vane for a gas turbine engine includes a primary cooling system (42) with a series of medial passages (44, 46a, 46b, 46c, 48) and an auxiliary cooling system (92) with a series of cooling conduits (94). The primary cooling system (42) comprises at least one radially extending medial passage (44, 46a, 46b, 46c, 48) bounded at least in part by the peripheral wall (16), and the auxiliary cooling system (92) comprises at least one cooling conduit (94) disposed in the wall between the medial passage and the external surface. The conduit has a chordwise dimension (C) and a lateral dimension (H), and the chordwise dimension (C) is no more than about three times the distance from the conduit (94) to the external surface (28). <IMAGE> |
