Tailoring rotor blade coating to tune gas turbine engine bladed rotor

An apparatus for a gas turbine engine, comprising:

• a bladed rotor rotatable about an axis, the bladed rotor including a rotor disk and a plurality of rotor blades projecting radially out from the rotor disk;
• each of the plurality of rotor blades including an airfoil and a coating over the airfoil;
• the plurality of rotor blades arranged circumferentially around the rotor disk into a plurality of blade groupings including a plurality of first blade groupings and a plurality of second blade groupings, each of the plurality of first blade groupings disposed circumferentially between a respective circumferentially neighboring pair of the plurality of second blade groupings, and each of the plurality of second blade groupings disposed circumferentially between a respective circumferentially neighboring pair of the plurality of first blade groupings;
• the coating of each of the plurality of rotor blades in each of the plurality of first blade groupings having a first configuration;
• and
• the coating of each of the plurality of rotor blades in each of the plurality of second blade groupings having a second configuration that is different than the first configuration.

An apparatus for a gas turbine engine, comprising:

• a bladed rotor rotatable about an axis, the bladed rotor including a rotor disk and a plurality of rotor blades arranged circumferentially around and connected to the rotor disk;
• the plurality of rotor blades including a first rotor blade, a second rotor blade and a third rotor blade arranged circumferentially between and neighboring the first rotor blade and the second rotor blade;
• the first rotor blade comprising a first coating;
• the second rotor blade comprising a second coating that is different than the first coating;
• and
• the third rotor blade comprising a third coating that is identical to the first coating.