Hybrid structure fan blade

Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Laminated – embedded member or encased material

Reexamination Certificate

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C416S22900R, C416S232000, C416S233000, C416S24100B

Reexamination Certificate

active

08083489

ABSTRACT:
A hybrid fan blade for a gas turbine engine is provided that includes an airfoil and a composite panel. The airfoil has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The airfoil includes a plurality of cavities disposed in the first side of the airfoil, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The composite panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

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