Hybrid structure fan blade

摘要

A hybrid fan blade (10) for a gas turbine engine is provided that includes an airfoil (14) and a composite panel (16). The airfoil (14) has a first side (26) and a second side (28) orientated opposite the first side (26). The first and second sides (26,28) extend between a tip (18), a base (20), a leading edge (22) and a trailing edge (24). The airfoil (14) includes a plurality of cavities (34) disposed in the first side (26) of the airfoil (14), which cavities (34) extend inwardly toward the second side (28). The cavities (34) collectively form an opening (28). At least one rib (40) is disposed between the cavities (34). A shelf (44) is disposed around the opening (38). The composite panel (16) is attached to the shelf first mounting surface (46) and to the rib (40), and is sized to enclose the opening (38). The first composite panel (16) is a load bearing structure operable to transfer loads to the airfoil (14) and receive loads from the airfoil (14).