Tailoring rotor blade sector configurations 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 arranged circumferentially around and connected to the rotor disk, the bladed rotor configured into a plurality of circumferential sectors about the axis, each of the plurality of circumferential sectors comprising a common number of the plurality of rotor blades that is greater than one, and the plurality of circumferential sectors including a first sector and a second sector;
• the first sector having a first rotor mass and a first rotor geometry;
• and
• the second sector having a second rotor mass and a second rotor geometry, at least one of
• the second rotor mass different than the first rotor mass;
• or
• the second rotor geometry different than the first rotor geometry.

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 bladed rotor having a plurality of circumferential sectors about the axis, each of the plurality of circumferential sectors having a common circumferential length about the axis, and the plurality of circumferential sectors including a first sector and a second sector;
• a section of the rotor disk defined by the first sector having a first disk mass and a first disk geometry;
• a section of the rotor disk defined by the second sector having a second disk mass and a second disk geometry;
• and
• at least one of the second disk mass different than the first disk mass, or the second disk geometry different than the first disk geometry.