Patent ID: 8876482

Claim:
A blade for use in a gas turbine engine comprising: an airfoil including a leading edge and a trailing edge, a sheath positioned at the leading edge, said sheath being secured to said airfoil by a first adhesive formed of a first material, said sheath being formed of a second material that is distinct from said first material, said first material being less electrically conductive than said second material; a grounding element in contact with said sheath, and said grounding element being in contact with a forward portion of a main body of said airfoil, said main body of said airfoil being formed of a third material that is more electrically conductive than said first material, said grounding element and said main body of said airfoil together forming a ground path from said sheath into said airfoil; and said airfoil extending outwardly to define a radial dimension, and said airfoil extending between suction and pressure sides to define a lateral dimension, and said grounding element disposed at a location between said sheath and said forward portion of the main body of said airfoil, the grounding element being positioned both laterally and radially inward of portions of said first adhesive to isolate said grounding element from liquids.