FAN BLADE ASSEMBLY
The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A nonconductive ceramic coating is applied to a sheath receiving surface of the airfoil before it is bonded to the sheath.
1 . A fan blade assembly, comprising:
a conductive airfoil including a sheath receiving surface, the sheath receiving surface coated with a nonconductive material;
a conductive sheath; and
an adhesive disposed on at least a portion of the nonconductive material to bond the conductive sheath to the conductive airfoil at the sheath receiving surface.
2 . The fan blade assembly of claim 1 , wherein the adhesive comprises a nonconductive adhesive.
3 . The fan blade assembly of claim 1 , wherein the adhesive comprises a conductive adhesive.
4 . The fan blade assembly of claim 1 , wherein the conductive airfoil is formed from an aluminum alloy.
5 . The fan blade assembly of claim 1 , wherein the conductive sheath is formed from a material selected from the group consisting of: titanium and titanium alloy.
6 . The fan blade assembly of claim 1 , wherein:
the conductive airfoil further includes an airfoil forward edge, a pressure side and a suction side;
the conductive sheath further includes a sheath head section and first and second flanks extending from the sheath head section; and
wherein the conductive sheath covers at least a portion of the airfoil forward edge, the first flank covers at least a portion of the suction side, and the second flank covers at least a portion of the pressure side.
7 . The fan blade assembly of claim 1 , wherein the nonconductive material comprises a ceramic.
8 . The fan blade assembly of claim 1 , wherein the conductive sheath covers substantially the entire forward airfoil edge.
9 . The fan blade assembly of claim 1 , wherein
the conductive airfoil comprises a first metal;
the conductive sheath comprises a second metal; and
the first metal is different than the second metal.
10 . The fan blade assembly of claim 9 , wherein the first metal comprises an aluminum alloy.
11 . The fan blade assembly of claim 9 , wherein the second metal comprises a material selected from the group consisting of: titanium and titanium alloy.
12 . A gas turbine engine, comprising in serial flow communication:
a fan section including a fan blade assembly, the fan blade assembly comprising:
a conductive airfoil including a sheath receiving surface, the sheath receiving surface coated with a nonconductive material;
a conductive sheath; and
an adhesive disposed on at least a portion of the nonconductive material to bond the conductive sheath to the conductive airfoil at the sheath receiving surface;
a compressor section;
a combustor section; and
a turbine section.
13 . The gas turbine engine of claim 12 , wherein the conductive airfoil is formed from an aluminum alloy.
14 . The gas turbine engine of claim 12 , wherein the conductive sheath is formed from a material selected from the group consisting of: titanium and titanium alloy.
15 . The gas turbine engine of claim 12 , wherein:
the conductive airfoil further includes an airfoil forward edge, a pressure side and a suction side;
the conductive sheath further includes a sheath head section and first and second flanks extending from the sheath head section; and
wherein the conductive sheath covers at least a portion of the airfoil forward edge, the first flank covers at least a portion of the suction side, and the second flank covers at least a portion of the pressure side.
16 . The gas turbine engine of claim 12 , wherein the nonconductive material comprises a ceramic.
17 . The gas turbine engine of claim 12 , wherein the conductive sheath covers substantially the entire forward airfoil edge.
18 . The gas turbine engine of claim 12 , wherein
the conductive airfoil comprises a first metal;
the conductive sheath comprises a second metal; and
the first metal is different than the second metal.
19 . The gas turbine engine of claim 18 , wherein the first metal comprises an aluminum alloy.
20 . The gas turbine engine of claim 18 , wherein the second metal comprises a material selected from the group consisting of: titanium and titanium alloy.