| 摘要 |
An airfoil (12) for a gas turbine engine in which the airfoil (12) includes an internal cooling system (10) formed in part by a segmented internal wall (54) that distributes mechanical loads is disclosed. The segmented internal wall (54) may include a plurality of connected segments (62). In one embodiment, at least a portion of the plurality of connected segments (62) may be non-parallel to a camber line (66) of the generally elongated hollow airfoil (32). In another embodiment, all of the plurality of connected segments (62) may be non-parallel to the camber line (66) of the generally elongated hollow airfoil (32). In a further embodiment, the plurality of connected segments (62) may be angled in an alternating fashion with respect to the camber line (66) of the generally elongated hollow airfoil (32). |
