Radial turbine rotor for gas turbine engine

A radial turbine rotor associated with an engine, comprising:

• a disk;
• a plurality of blades spaced apart about a perimeter of the disk, each blade of the plurality of blades including a forward end, an aft end and a root;
• a plurality of sectors, with each sector of the plurality of sectors coupled to the root of a respective blade of the plurality of blades, each sector of the plurality of sectors defines a first surface configured to contact a working fluid and a second surface configured to be coupled to the disk, each sector of the plurality of sectors having a first side, a second side opposite the first side and defining a first pocket between the first surface and the second surface proximate the forward end that extends toward the aft end along the first side, a second pocket between the first surface and the second surface proximate a leading end that extends toward a trailing end along the second side, the second side opposite the first side;
• and
• a feather seal slot defined between adjacent ones of the plurality of sectors proximate the first surface,
• wherein the radial turbine rotor is an axially split radial turbine rotor with a first radial turbine rotor coupled to a second radial turbine rotor, the first radial turbine rotor includes the disk, the plurality of blades and the plurality of sectors, the second radial turbine rotor includes a second disk, a plurality of second blades spaced apart about a perimeter of the second disk and a plurality of second sectors, with each second sector of the plurality of second sectors coupled to a respective second blade of the plurality of second blades and a second feather seal slot is defined between adjacent second sectors of the plurality of second sectors.

A radial turbine rotor associated with an engine, comprising:

• a disk having a first side opposite a second side;
• a plurality of blades spaced apart about a perimeter of the disk, each blade of the plurality of blades including a forward end, an aft end and a root;
• a plurality of sectors, with each sector of the plurality of sectors coupled to the root of a respective blade of the plurality of blades, each sector of the plurality of sectors defines a first surface configured to contact a working fluid and a second surface configured to be coupled to the disk, each sector of the plurality of sectors defining at least one pocket between the first surface and the second surface proximate the forward end that extends toward the aft end;
• a plurality of stress relief holes, with each stress relief hole of the plurality of stress relief holes defined through the disk to extend from the first side to the second side and associated with a respective one of the plurality of sectors, and the at least one pocket is defined between the first surface and a respective one of the plurality of stress relief holes;
• and
• a feather seal slot defined between adjacent sectors of the plurality of sectors proximate the first surface.