Fan blade with adhesive fabric stackup
A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.
1. A blade comprising:
an airfoil extending from a trailing edge to a leading edge, said airfoil including a body formed of an aluminum containing material;
a sheath at said leading edge and formed of a titanium containing material, with a sandwich positioned intermediate said sheath and said airfoil body, said sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body;
wherein said fabric layer is a woven fabric layer; and
wherein said woven fabric layer has holes that are less than 0.001 inch on average.
2. The blade as set forth in claim 1 , wherein said woven fabric layer is a fiberglass fabric.
3. The blade as set forth in claim 2 , wherein said woven fabric layer is between 0.005 and 0.010 inch in thickness.
4. The blade as set forth in claim 2 , wherein said inner and outer adhesive layers are epoxy adhesives.
5. The blade as set forth in claim 4 , wherein said inner and outer adhesive layers have an aerial weight of between 0.035 and 0.060 lb/sq ft.
6. The blade as set forth in claim 1 , wherein said blade is a fan blade for a gas turbine engine.
7. The blade as set forth in claim 1 , wherein said fabric layer has holes that are less than 0.0005 inch on average.
8. The blade as set forth in claim 1 , wherein said fabric layer is between 0.005 and 0.010 inch in thickness.
9. A gas turbine engine comprising:
a fan rotor including a plurality of blades, with said fan blades including an airfoil extending from a trailing edge to a leading edge, said airfoil having a body formed of an aluminum containing material;
a sheath at said leading edge formed of a titanium containing material, with a sandwich positioned intermediate said sheath and said airfoil body, said sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body;
wherein said fabric layer is a woven fabric layer; and
wherein said woven fabric layer has holes that are less than 0.001 inch on average.
10. The gas turbine engine as set forth in claim 9 , wherein said woven fabric layer is a fiberglass fabric.
11. The gas turbine engine as set forth in claim 10 , wherein said woven fabric layer is between 0.005 and 0.010 inch in thickness.
12. The gas turbine engine as set forth in claim 9 , wherein said inner and outer adhesive layers are epoxy adhesives.
13. The gas turbine engine as set forth in claim 12 , wherein said inner and outer adhesive layer have an aerial weight between 0.035 and 0.060 lb/sq ft.
14. The gas turbine engine as set forth in claim 9 , wherein said fabric layer has holes that are less than 0.0005 inch on average.
15. The gas turbine engine as set forth in claim 14 , wherein said fabric layer is between 0.005 and 0.010 inch in thickness.
16. The gas turbine engine as set forth in claim 9 , wherein said fabric layer is between 0.005 and 0.010 inch in thickness.