| 摘要 |
A hollow core fan blade for a gas turbine engine, having stitched composite skins and substructure, is fabricated using a resin transfer molding approach which results in a damage tolerant and cost-efficient structure. The fan blade is comprised of a stitched composite cover that is in-turn stitched to a spar and rib-like substructure made of similar carbon fiber materials. A titanium leading edge, root section, and tip closeout member are added to the stitched carbon fibers and placed inside a forming die. Resin is infused, after which the blade assembly, having predetermined design characteristics, is cured by heating the forming die and pressurizing the part internally with a set of inflatable bladders which ultimately yields a rigid fan blade component.
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