Grounding for fan blades on an underblade spacer

A gas turbine engine comprising:

• a fan section, a compressor section, a combustor section, and at least one turbine rotor, said at least one turbine rotor driving a compressor rotor, and said at least one turbine rotor also driving a fan rotor of said fan section through a gear reduction;
• said fan blade having an outer surface, at least at some areas, formed of a first material and having an airfoil extending from a dovetail, said dovetail received in said slot;
• a spacer positioned radially inwardly of a radially inner face of said dovetail, and biasing said fan blade against said slot, said spacer including a grounding element;
• and
• the grounding element in contact with a portion of said dovetail formed of a second material that is more electrically conductive than said first material, and said grounding element being in contact with a rotating element that rotates with said rotor, said rotating element being formed of a third material, and said first material being less electrically conductive than said third material, said grounding element and said rotating element together forming a ground path from said portion of said dovetail into said rotor.