| 摘要 |
A fan blade for a jet engine, such as a turbo fan jet engine is disclosed. The fan blade includes a root for coupling the fan blade to a rotating hub. The root is connected to a blade portion or an airfoil. The blade includes a leading edge and a trailing edge. The leading edge includes at least one of a protrusion or a recess along the leading edge to enhance the structural characteristics of the blade portion. To ensure that the recess or recesses and/or protrusion or protrusions do not adversely affect the aerodynamic qualities of the fan blade, the leading edge of the blade portion is covered by a protective sheath. The sheath may be fabricated from a titanium alloy and is typically adhered to the blade portion using an adhesive, such as an epoxy. |
