Patent ID: 9376924
Filing Date: 2016-06-28
CPC Classification: F01D,F02K,F04D,F05D

Claim Text:
1. A fan rotor for use in a gas turbine engine comprising: a rotor body having at least one slot receiving a fan blade; said fan blade formed of a first material, and a sheath positioned at a leading edge of said fan blade, 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 rotating element, said grounding element and said rotating element together forming a ground path from said sheath into said rotor; wherein said rotating element is separate from said rotor and formed of a material that is more electrically conductive than said first material; and wherein said rotating element is a lock ring which secures said fan blade in said rotor, said grounding element contacts said lock ring, and said lock ring contacts said rotor to provide said grounding path.