Hybrid metal fan blade
A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium.
1. A fan blade comprising:
an airfoil portion formed from a first metallic material, having a forward airfoil edge, a first airfoil surface, and a second airfoil surface; and
a sheath portion formed from a second metallic material, the sheath portion having a sheath head section, a first sheath flank and a second sheath flank, both flanks extending chordwise rearwardly from the sheath head section;
wherein the sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge to define a blade leading edge; the first sheath flank covers a portion of the first airfoil surface proximate the forward airfoil edge, jointly defining a blade suction surface; and the second sheath flank covers a portion of the second airfoil surface proximate the forward airfoil edge, jointly defining a blade pressure surface opposite the blade suction surface;
wherein a chordwise dimension of the sheath head section is at least 3% of a chordwise blade dimension in an inner span region, and at least 8% of a chordwise blade dimension in a distal span region; and
wherein the first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium.
2. The blade of claim 1 , wherein the aluminum alloy contains between about 1.0 wt % and about 2.5 wt % of lithium.
3. The blade of claim 2 , wherein the aluminum alloy contains between about 1.5 wt % and about 2.0 wt % of lithium.
4. The blade of claim 1 , wherein the second metallic material is a titanium alloy.
5. The blade of claim 4 , wherein the titanium alloy is a Ti-6A1-4V alloy.
6. The blade of claim 1 , wherein the sheath portion is adhesively bonded to the airfoil portion with an epoxy film.
7. The blade of claim 6 , wherein the blade further comprises a dielectrically protective scrim sheet disposed between layers of adhesive film.
8. The blade of claim 1 , wherein the airfoil contains at least one internal cavity.
9. A fan blade comprising:
a root;
an airfoil connected to the root and formed from a first metallic material having first and second major surfaces, an internal cavity with an opening in the first major surface, a socket around the opening, a cover received in the socket and covering the opening;
an adhesive bond between the cover and the socket; and
a sheath portion formed from a second metallic material, the sheath portion having a sheath head section, a first sheath flank and a second sheath flank, both flanks extending chordwise rearwardly from the sheath head section;
wherein a chordwise dimension of the sheath head section is at least 3% of a chordwise blade dimension in an inner span region, and at least 8% of a chordwise blade dimension in a distal span region;
wherein the first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium.
10. The blade of claim 9 , wherein the aluminum alloy contains between about 1.0 wt % and about 2.5 wt % of lithium.
11. The blade of claim 10 , wherein the aluminum alloy contains between about 1.5 wt % and about 2.0 wt % of lithium.
12. The blade of claim 11 , further comprising a filler material disposed within the cavity between a portion of the cover and the second major surface.
13. The blade of claim 12 , further comprising an adhesive bond between the cover and the filler material.
14. The blade of claim 11 , wherein the adhesive used to form the adhesive bond comprises polyurethane for providing force damping between the cover and the airfoil.
15. The blade of claim 11 , further comprising a plurality of ribs disposed within the cavity extending in the blade thickness direction between the cover and the second major surface.
16. The blade of claim 9 , wherein the sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge to define a blade leading edge; the first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface; and the second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface opposite the blade suction surface.
17. A gas turbine engine comprising:
a turbine section;
a compressor section rotatably driven by the turbine section; and
a fan section rotatably driven by the turbine section, the fan section including a plurality of blades disposed circumferentially around a rotor disc, each blade having at least a root, an airfoil portion, and a sheath portion, the airfoil formed from a first metallic material and extending spanwise from the root, and the sheath portion formed from a second metallic material, the sheath portion having a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise rearwardly from the sheath head section, the sheath portion bonded to the airfoil portion such that the sheath head section covers a forward airfoil edge to define a blade leading edge;
wherein the first sheath flank covers a portion of a first airfoil surface proximate the forward airfoil edge, jointly defining a blade suction surface; and the second sheath flank covers a portion of a second airfoil surface proximate the forward airfoil edge, jointly defining a blade pressure surface opposite the blade suction surface;
wherein a chordwise dimension of the sheath head section is at least 3% of a chordwise blade dimension in an inner span region, and at least 8% of a chordwise blade dimension in a distal span region; and
wherein the first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium.
18. The gas turbine engine of claim 17 , wherein the plurality of fan blades include at least one internal cavity.
19. The gas turbine engine of claim 18 , wherein the at least one internal cavity is defined by an opening in a first major surface of the airfoil, a socket around the opening, and a cover adhesively bonded to at least the socket for covering the opening.
20. The gas turbine engine of claim 17 , wherein the fan section is rotatably driven by the turbine section via a fan drive gear system disposed therebetween.